US Pat. No. 9,854,707

INTEGRATED PIPE HEAT EXCHANGER

ROSEMOUNT AEROSPACE INC.,...

1. A heat exchanger system comprising: a base having a mounting apparatus configured to secure the base in a substantially
fixed position with respect to a first heat source; a first heat generator attachment site formed in the base and conducts
heat to the base, the first heat generator attachment site configured to be positioned in thermal communication with a first
heat source; a dissipation member configured to conduct heat away from the base; a second heat generator attachment site formed
in the base and configured to be positioned in thermal communication with a second heat source and conduct heat to the base,
a third heat generator attachment site formed in the base and configured to be positioned in thermal communication with a
third heat source and conduct heat to the base, wherein the first heat generator attachment site comprises an integrated heat
pipe clamp attachment, the second heat generator attachment site comprises a bolt-on heat pipe attachment, the third heat
generator member comprises fins and troughs, wherein each of the troughs is oriented perpendicular to the first heat generator
attachment site, and wherein each of the troughs comprises a radiused end whereby the profile of each trough is shallower
near the integrated heat pipe clamp attachment and deeper extending away from the integrated heat pipe clamp attachment; and
wherein the heat exchanger system is a unitary piece of material.

US Pat. No. 9,227,833

VIBRATION ISOLATED MEMS STRUCTURES AND METHODS OF MANUFACTURE

ROSEMOUNT AEROSPACE INC.,...

1. A sensor device comprising:
a suspension frame defining at least one sensitive axis and at least one other axis;
at least one bearing operatively connected to the suspension frame;
a printed circuit board operatively connected to the suspension frame and the at least one bearing, wherein the at least one
bearing is configured and adapted to allow the printed circuit board to be compliant about the at least one other axis and
rigid about the at least one sensitive axis; and

a microstructure device operatively connected to the printed circuit board.

US Pat. No. 9,096,323

WINDOW CONTAMINATION SENSOR FOR OPTICAL DETECTION SYSTEMS

Rosemount Aerospace Inc.,...

1. A system for detecting contamination of a window of an optical system, the system comprising:
a polarizing beamsplitter configured to receive a laser beam having a first polarization and reflect the laser beam having
the first polarization to the window;

a photodetector configured to sense a magnitude of reflections of the laser beam from the window having a second polarization
orthogonal to the first polarization, wherein the polarizing beamsplitter passes the reflections of the laser beam from the
window having the second polarization to the photodetector; and

a processor configured to determine a contamination level of the window based upon the magnitude of the reflections of the
laser beam from the window.

US Pat. No. 9,423,315

DUPLEX PRESSURE TRANSDUCERS

Rosemount Aerospace Inc.,...

7. A duplex pressure transducer comprising:
a transducer baseplate including:
a base with a protrusion extending from the base along a longitudinal axis, wherein the base has a cross-sectional perimeter
in a plane perpendicular to the longitudinal axis;

a pair of transducer receptacles defined within the protrusion, wherein the transducer receptacles are opposed from one another
across the longitudinal axis, wherein the transducer receptacles are in fluid and operational isolation from one another,
wherein the receptacles each have a width parallel to the longitudinal axis, and wherein the combined widths of the receptacles,
when oriented in a common plane perpendicular to the longitudinal axis, are too large to fit within the cross-sectional perimeter
of the base; and

a pair of pressure plena separated by a plenum wall, wherein one plenum is in fluid communication with each receptacle, respectively,
and each plenum is in fluid connection with an area external to the protrusion through a respective pressure line, wherein
the pressure lines provide a direct fluid path to their respective receptacles;

a separate high temperature absolute pressure capsule secured in each receptacle, wherein the high temperature absolute pressure
capsules are fluidly isolated from one another;

circuitry operatively connected to an end surface of the protrusion each in electronic communication with a separate high
temperature pressure capsule; and

a transducer housing sealed over at least the transducer receptacles, high temperature pressure capsules, and circuitry.

US Pat. No. 9,488,534

SUPERCRITICAL TOTAL AIR TEMPERATURE SENSORS

Rosemount Aerospace Inc.,...

1. A total air temperature sensor comprising:
a supercritical airfoil body extending from an airfoil base to an opposed airfoil tip along a longitudinal axis, wherein the
supercritical airfoil body defines an interior flow passage with an inlet for fluid communication of fluid into the interior
flow passage and an outlet for exhausting fluid out from the interior flow passage; and

a temperature probe mounted within the interior flow passage for measuring temperature of flow through the interior flow passage
to determine total air temperature.

US Pat. No. 9,297,714

AIR DATA PROBES

Rosemount Aerospace Inc.,...

1. An air data probe comprising:
a probe head, the probe head defining a longitudinal axis with a forward tip and a probe head surface; and
a raised portion defined in the probe head surface aft of the forward tip, wherein the raised portion is raised radially relative
to the probe head surface, wherein the raised portion is configured and adapted to trip a fluid boundary layer passing over
the probe head to transition from laminar to turbulent for reducing boundary layer separation for consistent readings at high
altitudes and high mach numbers, wherein the raised portion includes curved transitions between a top surface of the raised
portion and a side of the raised portion.

US Pat. No. 9,207,253

ICE RESISTANT PITOT TUBE

ROSEMOUNT AEROSPACE INC.,...

1. A pitot tube comprising:
a substantially cylindrical body portion; and
a tip portion extending along a pitot tube axis from the body portion, the tip portion including:
an inlet opening;
a radially tapering outer surface extending from the body portion toward the inlet opening;
an interior portion having a fluid flow passage; and
a heating element arranged along the flow passage, the heating element defining a heating zone configured and disposed to
be directly fluidically exposed to fluid flowing along the fluid flow passage.

US Pat. No. 9,285,386

INDUCTIVE ROTATIONAL SPEED SENSORS

Rosemount Aerospace Inc.,...

1. A method of converting an electrical signal to a rotational speed comprising:
converting an alternating electrical input to an alternating magnetic field using a transmitter coil of a first PCB;
receiving the alternating magnetic field with a resonance coil of a second PCB rotating relative to the first PCB;
emitting a modulating position signal from the resonance coil of the second PCB;
receiving the modulating position signal with a receiver coil of the first PCB;
outputting a signal indicative of rotational speed from the first PCB; and
converting the output signal to an angular frequency ?=360°/nT, where ? is an angular speed in degrees per second, n is a
number of receiver coil pole pairs on the first PCB, and T is a period of the outputted signal.

US Pat. No. 9,655,262

HEADER SUB-ASSEMBLIES

Rosemount Aerospace Inc.,...

1. A dielectric header sub-assembly comprising:
a header body including opposed first and second surfaces defining a header axis extending therebetween, a side wall extending
from the first surface to the second surface, wherein the second surface includes a tapered portion,

and a sensor die mounted to the first surface of the header body opposite of the second surface, wherein the surface area
of the first surface is greater than the surface area of a non-tapered portion of the second surface.

US Pat. No. 9,431,713

CIRCULARLY-POLARIZED PATCH ANTENNA

Rosemount Aerospace Inc.,...

1. A patch antenna comprising:
a conductive ground plane layer;
a conductive circular patch layer comprising a plurality of voids;
a dielectric layer disposed between and contacting each of the ground plane layer and the circular patch layer;
a grounding connection extending from the ground plane layer through the dielectric layer and contacting the circular patch
layer at a grounding location of the circular patch layer;

a RF feed extending through the ground plane layer and the dielectric layer and contacting the circular patch layer at an
electrical feed location of the circular patch layer; and

a tuning portion that extends along a portion of an outer periphery of the circular patch layer;
wherein the electrical feed location is offset from a central axis of the circular patch layer;
wherein the plurality of voids are disposed symmetrically about the grounding location;
wherein a first axis extending through each of the plurality of voids and a second axis extending perpendicular to the first
axis define four quadrants of the circular patch layer;

wherein the tuning portion extends along an outer periphery of a first quadrant of the four quadrants; and
wherein the RF feed location is disposed within a second quadrant of the four quadrants, the second quadrant opposite the
second axis and adjacent the first quadrant.

US Pat. No. 9,341,533

AIR DATA PROBES

Rosemount Aerospace Inc.,...

1. An air data probe comprising:
a probe head, the probe head defining a longitudinal axis with a forward tip;
a turbulence inducing surface defined in the probe head aft of the forward tip, wherein the turbulence inducing surface is
configured and adapted to trip a fluid boundary layer passing over the probe head to transition from laminar to turbulent
for reducing boundary layer separation for consistent readings at high altitudes; and

a first static port proximate the forward tip and a second static port aft the first static port, wherein the turbulence inducing
surface is defined therebetween, and wherein the turbulence inducing surface is a single annular depression around the probe
head.

US Pat. No. 9,239,338

VANE DEVICE FOR A DYNAMIC FLOW ANGLE MEASUREMENT

ROSEMOUNT AEROSPACE INC.,...

1. A gust sensing vane having a cropped-delta shape and for being coupled to a rotary hub, wherein the gust sensing vane comprises:
a forward portion tapering to a straight leading edge that has a length along an axis perpendicular to the rotary hub, wherein
a cross-sectional area of the forward portion has a triangular shape; and

an aft portion having a first trailing edge and a second trailing edge, wherein a cross-sectional area of the aft portion
has two substantially parallel sides;

wherein the gust sensing vane is configured to be coupled to, and extend away from, the rotary hub;
wherein the leading edge of the forward portion is swept rearward and is symmetrical about a bisecting axis that extends away
from the rotary hub; and

wherein the gust sensing vane aligns to a fluid flow direction.

US Pat. No. 9,207,053

HARMONIC SHUTTERED SEEKER

ROSEMOUNT AEROSPACE INC.,...

11. An imager for detecting and decoding image data and laser data having a predetermined PRF, the imager comprising:
a focal plane array; and
the imager configured to:
control said focal plane array to decode the image data and the laser data;
divide a pulse interval of the predetermined PRF into a plurality of subintervals;
expose alternating ones of said plurality of subintervals;
determine whether two or more received pulses are received in one of said subintervals; and
identify said one of said subintervals of said pulse interval, thereby detecting and decoding said received pulses of said
one of said subintervals as having the predetermined PRF.

US Pat. No. 9,658,117

TOTAL AIR TEMPERATURE PROBES FOR REDUCING DEICING HEATER ERROR

Rosemount Aerospace Inc.,...

1. A total air temperature probe comprising:
a probe head having an airflow inlet, a main airflow outlet, a main probe head wall extending from the airflow inlet to the
main airflow outlet, and a flow separation bend wall positioned between the airflow inlet and the main airflow outlet, the
flow separation bend wall being opposite the main probe head wall across a primary flow passage defined through the probe
head from the airflow inlet to the main airflow outlet;

opposed sidewalls, each sidewall connecting between the main probe head wall and the flow separation bend wall; and
a flow separation trip feature defined on an interior surface of the main probe head wall for tripping a boundary layer flow
separation in flow in the primary flow passage, wherein the flow separation trip feature spans the main probe head wall from
one of the opposed sidewalls to the other, and, wherein the flow separation trip feature has a leading notch edge spaced inward
from the airflow inlet.

US Pat. No. 9,279,684

AIR DATA PROBE SENSE PORT REPAIR

Rosemount Aerospace Inc.,...

1. A method of repairing an air data probe sense port comprising:
inserting a plug into a sense port in an air data probe, wherein inserting a plug includes inserting a cylindrical plug with
an enlarged portion, wherein the enlarged portion remains outside the sense port and prevents over insertion of the plug;

forming a joint joining the plug to the air data probe;
dressing the joint to be flush with adjacent air data probe surface; and
forming a new sense port in the air data probe.

US Pat. No. 9,163,905

DUAL-MODE SAL/IR IMAGING

Rosemount Aerospace Inc.,...

1. A dual-mode SAL/IR imaging seeker comprising:
a focal plane array (FPA);
an objective optical assembly providing a common optical path to the FPA for incident laser radiation of a first wavelength
band and incident ambient radiation of a second wavelength band non-overlapping with the first wavelength band;

a first optical filter operable to selectively pass the incident laser radiation of the first wavelength band to the FPA in
a transmissive mode and selectively block the incident laser radiation of the first wavelength band from the FPA in a non-transmissive
mode, wherein the first wavelength band is from 10 nm to 20 nm wide within a wavelength range from 700 nm to 1700 nm; and

a second optical filter operable to selectively pass the incident ambient radiation of the second wavelength band to the FPA
in a transmissive mode and selectively block the incident ambient radiation from the FPA in a non-transmissive mode, wherein
the second wavelength band includes wavelengths in the range from 700 nm to 1700 nm not included in the first wavelength band.

US Pat. No. 9,473,710

VIDEO SIGNAL TERMINATION DETECTION CIRCUIT

Rosemount Aerospace Inc.,...

1. A video signal termination detection system, comprising:
an input configured to connect to a video driver that produces a video signal having a driver video signal type;
an output configured to connect to a video receiver that operates with a receiver video signal type;
a detection circuit connected between the input and the output and configured to detect the receiver video signal type of
the video receiver and to output a detection signal;

a conversion circuit configured to receive the video signal from the video driver and to convert the driver video signal type
to the receiver video signal type of the video receiver if the driver video signal type is different from the receiver video
signal type of the video receiver;

a video interrupt switch configured to interrupt the video signal;
a test voltage supply for supplying a test voltage to the system when the video signal is interrupted by the video interrupt
switch, the supplying of the test voltage being controlled by at least one test voltage switch; and

a controller configured to control at least one of the video interrupt switch, the test voltage switch, and the conversion
circuit based on the detection signal received from the detection circuit;

wherein the controller is configured to shut off the input, switch on the test voltage, determine the receiver video signal
type, disconnect the test voltage, and reconnect the input to supply the receiver video signal type to the video receiver.

US Pat. No. 9,347,790

POWER SUPPLY SYSTEM WITH AT LEAST A PRIMARY POWER SOURCE AND AN AUXILIARY POWER SOURCE FOR POWERING AN ELECTRONIC FLIGHT BAG DEPENDING ON AN WHETHER AN AIRCRAFT IS IN A FLIGHT CONDITION

Rosemount Aerospace Inc.,...

10. An electronic flight bag control system, comprising:
a power switching component coupled to a primary power source and an auxiliary power source,
wherein the power switching component is connected to the primary power source by a primary feed line in and to the auxiliary
power source by an auxiliary feed line in; and

at least one electronic flight bag device coupled to each of the the primary power source and the auxiliary power source via
the power switching component through a corresponding primary feed and a corresponding auxiliary feed,

wherein the power switching component is operative and configured to selectively apply electrical power from at least one
of the the primary power source and the auxiliary power source to the at least one electronic flight bag device based upon
whether said aircraft is in a flight or non-flight condition,

whereby when said aircraft is in a flight condition said power switching component is operative and configured to couple said
electronic flight bag only to the primary power source and decouple from the auxiliary power source without interruption of
electrical power supply through the power switching component to the electronic flight bag device.

US Pat. No. 9,395,604

CAMERA ADJUSTMENT TOOL AND METHOD

Rosemount Aerospace Inc.,...

1. A camera adjustment mechanism comprising:
a first portion comprising:
a first end;
a second end; and
a first wall extending between and connecting the first end and the second end, wherein the first wall is sloped such that
an inner diameter of the first end is greater than an inner diameter of the second end; and

a second portion comprising:
a third end, the third end connected to the second end;
a fourth end;
a second wall extending between and connecting the third end and the fourth end;
a shoulder disposed circumferentially about an outer edge of the second wall; and
a plurality of engagement openings extending circumferentially about the fourth end.

US Pat. No. 9,429,482

TOTAL AIR TEMPERATURE PROBE WITH LOW FRONTAL PROJECTED AREA

ROSEMOUNT AEROSPACE INC.,...

1. A total air temperature (TAT) probe comprising:
a mounting surface extending in a longitudinal direction from a forward end to an aft end of the TAT probe;
a primary airflow passage through the TAT probe;
a primary airflow outlet defining an outlet to the primary airflow passage;
a sensor flow passage in fluid communication with the primary airflow passage;
an airflow inlet defining an inlet to the primary airflow passage and having a first surface extending in a direction that
is within four degrees of a direction of an airflow received by the airflow inlet and within four degrees of the longitudinal
direction of the mounting surface and a second surface inclined relative to the first surface such that the first surface
and the second surface converge from the airflow inlet towards sensor flow passage; and

a total air temperature sensor assembly disposed within the sensor flow passage,
wherein the first surface is positioned nearer to the mounting surface than the second surface.

US Pat. No. 9,261,425

HIGH TEMPERATURE PRESSURE SENSOR

ROSEMOUNT AEROSPACE INC.,...

1. A pressure sensor assembly, comprising:
a pressure sensor having a pressure sensing transducer connected to a plurality of electrode pins for transmitting an electrical
signal, the pressure sensing transducer being connected to the electrode pins via a plurality of electrode pads disposed on
the pressure sensing transducer via a wire bond;

an inner casing configured to hold the pressure sensor in a sensor pocket having a pocket volume larger than the sensor volume,
the inner casing further including a plurality of inner casing electrode pin channels having the electrode pins disposed therein,
the inner casing electrode pin channels defined in a first inner casing side and a fluid port defined in a second inner casing
side;

an outer casing holding the inner casing therein including:
a capsule header having a plurality of capsule header electrode pin channels defined therein, wherein the capsule header receives
the first inner casing side, the capsule header electrode pin channels including a ceramic seal disposed therein such that
the capsule header electrode pin channels engage the electrode pins in an insulating sealed relationship;

an isolator plate disposed over the second inner casing side and in contact with the capsule header, the isolator plate including
an isolator plate fluid port defined therein; and

a pressure isolator disposed on the isolator plate and configured to deflect in response to a change in ambient pressure;
a fluid volume defined by a total remaining volume inside the inner casing and the outer casing combined; and
a pressure transmitting fluid disposed in the fluid volume.

US Pat. No. 9,476,968

SYSTEM AND METHOD FOR MONITORING OPTICAL SUBSYSTEM PERFORMANCE IN CLOUD LIDAR SYSTEMS

Rosemount Aerospace Inc.,...

1. A method of detecting optical subsystem failures, comprising:
emitting a pulsed light beam from a laser through an external window towards a cloud;
receiving a reflection signal indicative of a portion of the beam reflected by the external window and a portion of the beam
reflected by the cloud;

comparing the reflection signal to an expected signal to monitor for at least one of degradation of an optical component and
presence of the cloud; and

detecting degradation of the optical component and presence of the cloud based on the comparison;
wherein the comparing and detecting are performed by a processor operatively coupled to a memory.

US Pat. No. 9,383,249

METHOD TO DETECT ANGLE SENSOR PERFORMANCE DEGRADATION THROUGH DITHER MONITORING

Rosemount Aerospace Inc.,...

1. A computer-implemented method for detecting sensor performance degradation in a fluid flow angular measurement device,
the method comprising the steps of:
monitoring oscillation characteristics due to vortex shedding of fluid flow angular measurement device a computer processor,
wherein the oscillation characteristics include amplitude or frequency; and

determining if the fluid flow measure device is physically damaged based upon referenced sensor dither characteristics for
the fluid flow measurement device as determined by a computer processor based upon the monitored oscillation characteristics
of a fluid flow measurement device.

US Pat. No. 9,382,015

SINGLE AISLE MOUNT

ROSEMOUNT AEROSPACE INC.,...

1. A single aisle mount system comprising:
a device mount having a bent flange defining a pin acceptance aperture and having a device affixment interface adapted to
mechanically interface with an electronic device;

a structural support adapted to mechanically interface with an aircraft cockpit window ledge;
a pin; and
an articulating base disposed between the device mount and the structural support, defining a pin aperture and having a blind
fitting tab adapted to constrain the bent flange of the device mount such that the pin acceptance aperture and the pin aperture
are aligned and each are able to receive the pin in response to the blind fitting tab interfacing with the bent flange and
comprising an axis member adapted to provide an axis of rotation, wherein the articulating base retains the device mount in
mechanical communication with the structural support and permits rotation of the device mount about the axis of rotation,

wherein the articulating base includes:
a base plate comprising a bent piece having two parallel flanges each defining an aperture through which the axis member is
configured to extend,

an articulation guide configured to guide articulation of the device mount about the axis of rotation and having an axis aperture
configured to accept the axis member and an angle stop extending outward from a center of the articulation guide and configured
to contact the base plate to limit annular rotation of the articulation guide to a predetermined angle about the axis of rotation,
and

a tightening system configured to exert a dampening force to prevent unwanted articulation of the device mount about the axis
of rotation.

US Pat. No. 9,719,820

HYBRID MATERIAL PITOT TUBE

GOODRICH AEROSPACE SERVIC...

1. A pitot tube comprising:
a substantially cylindrical body portion having an interior defining a flow passage; and
a tip portion extending along a pitot tube axis from the body portion, the tip portion including:
a disk;
a tip cover; and
a high thermal conductive insert disposed between the disk and the tip cover and in thermal contact with both.

US Pat. No. 9,658,337

LARGE DROPLET DETECTION BY STATISTICAL FLUCTUATIONS IN LIDAR BACKSCATTER

Rosemount Aerospace Inc.,...

1. A method of optically detecting the presence of a bimodal droplet size distribution in the atmosphere, the method comprising:
monitoring statistical fluctuations in a backscattered signal received from a series of pulsed laser light beams having wavelengths
of 905 nm and 1550 nm directed into a cloud; and

analyzing the statistics of the fluctuations of the backscattered signals to identify the presence of larger diameter droplets,
wherein analyzing includes:

examining fluctuations in space and time simultaneously using a wavelet transformation; and
calculating a characteristic magnitude of fluctuations of the backscattered signal and identifying fluctuations of backscattered
signals greater than those typical for a single-mode small droplet cloud to determine whether there is bimodal droplet size
distribution within the cloud.

US Pat. No. 9,568,583

ASYNCHRONOUS PULSE DETECTION THROUGH SEQUENTIAL TIME SAMPLING OF OPTICALLY SPREAD SIGNALS

ROSEMOUNT AEROSPACE INC.,...

1. A system for asynchronous pulse detection comprising:
a converter array;
an optical system configured to pass laser energy at a predetermined band of wavelengths to said converter array, wherein
said optical system is further configured to spread said predetermined band of wavelengths across a predetermined area; and

a read out integrated circuit (ROIC) that scans said predetermined area of said array at an exposure rate that matches a predetermined
PRF to thereby decode said predetermined band of wavelengths spread by said optical systems across said predetermined area
of said array.

US Pat. No. 9,541,394

MEMS GYROS WITH QUADRATURE REDUCING SPRINGS

Rosemount Aerospace Inc.,...

1. A spring set for a MEMS device comprising:
a) a plurality of springs connecting a first mass to a seconds mass, wherein the first and second masses define orthogonal
x, y, and z-axes and are configured for relative oscillation about the z-axis, each spring having a spring element anchored
to the first mass at a first anchor point and anchored to the second mass at a second anchor point, wherein the first and
second anchor points of each spring element are located on a respective common vector that is oblique with respect to the
orthogonal axes defined by the first and second masses, wherein the respective common vector is non-radial with respect to
the z-axis.

US Pat. No. 9,464,950

CAPACITIVE PRESSURE SENSORS FOR HIGH TEMPERATURE APPLICATIONS

Rosemount Aerospace Inc.,...

1. A capacitive pressure sensor, comprising:
a substrate wafer defining a main substrate recess and having a first electrode;
a diaphragm wafer defining a main diaphragm recess and having a second electrode;
one of the substrate and diaphragm wafers defining an independent via recess, wherein the diaphragm wafer is bonded to the
substrate wafer such that the substrate and diaphragm recesses form a height differentiated pressure chamber, and the via
recess forms a via chamber,

wherein a depth of the via recess is less than a depth of the corresponding main recess in the same wafer.

US Pat. No. 9,316,463

MULTIMODE SHORT WAVELENGTH INFRARED AND RADIO-FREQUENCY SEEKER

Rosemount Aerospace Inc.,...

9. A sensor for use on a flight body, the sensor comprising:
a patch antenna that transmits and receives radio-frequency radiation;
a short wavelength infrared detector that receives short wavelength infrared radiation, wherein the patch antenna is transparent
to the short wavelength infrared radiation, and wherein the short wavelength radiation propagates through the patch antenna
to the short wavelength infrared detector; and

sensor electronics that control the flight body based upon data received from the patch antenna and the short wavelength infrared
detector.

US Pat. No. 9,631,960

ICE RESISTANT PITOT TUBE

ROSEMOUNT AEROSPACE INC.,...

1. A pitot tube comprising:
a substantially cylindrical body portion having an interior defining a flow passage; and
a tip portion extending along a pitot tube axis from the body portion, the tip portion including:
an inlet opening;
a radially tapered outer surface extending from the body portion toward the inlet opening;
one or more bulkheads disposed at the interior to limit travel of particles ingested into the interior;
at least one drain opening disposed directly adjacent to one of the one or more bulkheads; and
one or more electrical coils comprising one or more coil wraps disposed at an interior of the pitot tube, the one or more
coil wraps establishing a variable watt density along the interior of the pitot tube, the one or more coil wraps also establishing
a variable watt density downstream of one or more of the one or more bulkheads.

US Pat. No. 9,754,914

METHOD TO PROVIDE DIE ATTACH STRESS RELIEF USING GOLD STUD BUMPS

Rosemount Aerospace Inc.,...

1. An attachment feature for an integrated circuit on a substrate that provides a controlled stand-off height, comprising:
a plurality of stud bumps on the substrate; and
a plurality of silicone adhesive dots covering the stud bumps;
wherein the plurality of stud bumps and the plurality of silicone adhesive dots on the substrate are configured to attach
the integrated circuit to the substrate at the controlled stand-off height determined only by heights of the stud bumps upon
pressing down of the integrated circuit on the silicone adhesive dots to achieve physical contact in contact locations between
the integrated circuit and the stud bumps, the silicone adhesive dots being heated and thermally cured around the contact
locations after pressing down of the integrated circuit to adhere the integrated circuit to the substrate.

US Pat. No. 9,696,187

DEVICE FOR MEASURING TOTAL PRESSURE OF FLUID FLOW

ROSEMOUNT AEROSPACE INC.,...

1. A device for measuring total pressure of a fluid flow, comprising:
a tubular member having a central longitudinal axis, comprising
an inlet chamber having an inlet opening at a first end of the tubular member, the inlet opening having a first diameter transverse
to the longitudinal axis,

an outlet chamber having an outlet opening at a second end of the tubular member, the outlet opening having a second diameter
transverse to the longitudinal axis, wherein the ratio of the first diameter to the second diameter is from 3:1 to 10:1, and

a transitional chamber between the inlet chamber and the outlet chamber, the transitional chamber having a third diameter
transverse to the longitudinal axis at an end toward the inlet chamber, and a fourth diameter, smaller than the third diameter,
transverse to the longitudinal axis at an end toward the outlet chamber; and

a total pressure sensor in communication with the inlet chamber.

US Pat. No. 9,590,497

SYSTEMS AND METHODS FOR CAPACITOR CHARGE EXTRACTION

Rosemount Aerospace Inc.,...

1. A system for providing electrical power to a load comprising:
a boost converter with an input and an output;
a storage device operatively connected between the output of the boost converter and a ground node, wherein the energy storage
device is a super capacitor;

a first switch operatively connected between a first input node and the output of the boost converter, the switch having a
first state connecting the energy storage device to the output of the boost converter and a second state connecting the energy
storage device to supply input voltage to the input of the boost converter;

a charge decision controller operatively connected to the first input node to detect voltage of the energy storage device,
wherein the charge decision controller is operatively connected to detect voltage at a second input node selectively connected
to the input of the boost converter;

a second switch operatively connected between the second input node and the input of the boost converter, the second switch
having a first state connecting the boost converter to the second input node to receive power from a power source, and a second
state disconnecting the boost converter from the second input node, wherein the charge decision controller is operatively
connected to command the first and second switches into their respective second states upon detection of voltage below a first
predetermined limit at the input node and voltage of the capacitor below a second predetermined limit.

US Pat. No. 9,518,807

PROJECTILE CONTROL SYSTEMS AND METHODS

Rosemount Aerospace Inc.,...

9. A projectile control system, comprising:
a processor operatively connected to a memory, wherein has instructions recorded thereon that, when read by the processor,
cause the processor to:

initiate an execution mode if a roll control authority parameter is outside of a pre-determined operating range, wherein the
execution mode includes bypassing a guidance command, and sending a modified command to execute a coning maneuver for improved
control response of a projectile; and

a projectile operatively connected to the processor, wherein the projectile includes at least one control surface configured
to rotate about its respective control surface axis to generate control forces and moments.

US Pat. No. 9,435,613

SEMI-ACTIVE LASER SEEKER SYNCHRONIZATION

Rosemount Aerospace Inc.,...

1. A system for semi-active laser seeker synchronization, the system comprising:
a laser target designator configured to emit a laser pulse signal;
a seeker configured to detect the emitted signal from the laser target designator, wherein the laser target designator and
the seeker are operatively connected to synchronize the emission of the laser pulse signal and the detection of the seeker;
and

a launch platform configured to synchronize the laser target designator and the seeker, wherein, prelaunch, the laser target
designator and the seeker are located on the launch platform.

US Pat. No. 9,611,031

FLUTTER CONTROL ACTUATOR

ROSEMOUNT AEROSPACE INC.,...

1. A method of controlling an angular parameter between a base member and a control surface of an aircraft, comprising:
obtaining an estimate of an angular rate of the control surface with respect to an inertial frame using a rate sensor;
determining, via a summing unit, a residual angular rate that is a difference between a commanded angular rate and the estimate
of the angular rate of the control surface; and

using the residual angular rate to control the base member to control the angular parameter of the control surface; and
wherein determining the residual angular rate further comprises subtracting a set rate related to an extremum limit of the
estimated angle between the control surface and the base member from the commanded angular rate of the control surface.

US Pat. No. 9,631,985

TOTAL AIR TEMPERATURE SENSORS

Rosemount Aerospace Inc.,...

1. A total air temperature probe comprising:
a probe body extending from a probe base to an opposed probe tip along a longitudinal axis and defining a leading edge and
opposed trailing edge;

an interior flow passage aligned with the longitudinal axis defined in the probe body with an inlet defined on the probe tip
for fluid communication of fluid into the interior flow passage, and an outlet for exhausting fluid out from the interior
flow passage;

a sloped surface on an exterior of the probe tip extending from the leading edge to the trailing edge, wherein the sloped
surface is flush with the leading edge and set in from the trailing edge with respect to the longitudinal axis to define a
lip proximate the trailing edge, wherein the sloped surface and the lip are configured to create a high pressure region proximate
the inlet of the interior flow passage; and

a temperature sensor mounted within the interior flow passage for measuring temperature of flow through the interior flow
passage to determine total air temperature.

US Pat. No. 9,335,405

ENHANCED RF DETECTION SYSTEM

ROSEMOUNT AEROSPACE INC.,...

1. A radio frequency (RF) obstacle detection system of a vehicle, the system comprising:
an RF radar module coupled to the vehicle and configured to transmit an initial RF signal having a first signal strength and
to receive at least one reflected RF signal having a second signal strength based on the initial RF signal;

a radar reflector module coupled to the vehicle and disposed at a first distance remotely located from the RF radar module,
the radar reflector module configured to receive the RF signal generated by the RF radar module and efficiently retroreflect
the RF signal to generate a reflected signal having a second signal strength back to the RF radar module; and

a control module coupled to the vehicle and configured to determine a second distance between the radar reflector module and
at least one obstacle remotely located from the vehicle based on the reflected signal provided by the radar reflector module
and a received signal induced by the at least one obstacle.

US Pat. No. 9,811,138

POWER SUPPLY SYSTEM FOR AN ELECTRONIC FLIGHT BAG

Rosemount Aerospace Inc.,...

1. A control system for providing electrical power to an electronic flight bag device on an aircraft, the control system comprising
a power switching component coupled to a plurality of power source and at least one electronic flight bag device,
wherein the control system is coupled to the at least on electronic flight bag device by a primary feed, wherein the primary
feed is coupled only to a primary power source;

wherein the control system is coupled to the at least one electronic flight bag device by an auxiliary feed, wherein the auxiliary
feed is coupled only to a secondary power source; and

wherein the power switching component is operative and configured to selectively apply electrical power from at least one
of the plurality of power sources base upon a condition of the aircraft.

US Pat. No. 9,797,702

CONTROL SURFACE SKEW DETECTION SYSTEMS

Rosemount Aerospace Inc.,...

1. A skew detection system for an aircraft control system comprising:
a control surface including opposed first and second ends;
a first drive mechanism operatively connected to the first end of the control surface by a first rack and pinion assembly
and a second drive mechanism operatively connected to the second end of the control surface by a second rack and pinion assembly,
wherein each rack and pinion assembly includes a respective sensor package operatively connected to sense rotation of the
pinion thereof, the sensor package comprising:

a stack of separated printed circuit boards including:
a first position target printed board;
a second printed circuit board having a rotary sensor; and
a third printed circuit board having power supply components; and
a processing component operatively connected to both sensor packages to determine presence of skew in the control surface
based on rotation of the pinions.

US Pat. No. 9,771,171

AIRCRAFT WING DEFORMATION MONITORING AND ANALYSIS SYSTEM

ROSEMOUNT AEROSPACE INC.,...

1. A wing deformation monitoring and analysis system, comprising:
at least one image sensor installed on an aircraft and at a separate location from at least one wing of the aircraft, the
at least one image sensor configured to output at least one image signal representing a captured wing image of the at least
one wing of the aircraft, the at least one image sensor arranged on a same plane of the at least one wing such that the at
least one image and the at least one wing are co-planar with one another;

an electronic deformation controller in electrical communication with the at least one image sensor, the electronic deformation
controller configured to compare the captured wing image to a nominal wing image arranged on a reference plane, to determine
a deformation differential based on an amount of deflection the at least one wing deflects upwards or downwards with respect
to the reference plane, and to determine a deformation of the at least one wing based on the comparison,

wherein an upper deflection threshold is located an upward distance from the reference plane defined by the nominal wing image
and a lower deflection threshold is located a downward distance from the reference plane defined by the nominal wing image,
and wherein the electronic deformation controller determines a deformation of the at least one wing in response to a captured
wing deflection included in the captured wing image exceeding at least one of the upper deflection threshold and the lower
deflection threshold.

US Pat. No. 9,933,290

ADDITIVELY MANUFACTURED FLOW MEASUREMENT SENSOR

Rosemount Aerospace Inc.,...

1. A flow measurement sensing device comprising:a first venturi comprising a first shield portion;
an elongated portion connected to an outer surface of the first venturi;
a second venturi housed within the first venturi, the second venturi comprising:
a second shield portion; and
at least one air inlet; and
a first integral passageway extending from the at least one air inlet through the elongated portion, the first integral passageway comprising a first segment having a first cross-sectional shape and a second segment having a second cross-sectional shape.

US Pat. No. 9,702,783

AIR DATA PROBE WITH FLUID INTRUSION SENSOR

Rosemount Aerospace Inc.,...

1. An air data probe comprising:
a stationary housing assembly including a mounting plate secured over an opening in a housing to define a probe cavity;
an air data measurement unit rotatable about a longitudinal axis of the air data probe, relative to the stationary housing
assembly;

a fluid sensing unit disposed proximate to an interface between the housing assembly and the air data measurement unit, the
fluid sensing unit comprising:

a first electrically conductive sensing surface; and
a second electrically conductive sensing surface physically and dielectrically spaced from the first sensing surface; and
a combination ring fastened to an inner side of the mounting plate, the combination ring including a dielectric substrate
portion having a first side with a conductive metal ring portion formed concentrically between inner and outer edges of the
dielectric substrate;

wherein the combination ring is fastened with the first side facing the inner side of the mounting plate and such that only
the dielectric substrate portion contacts the inner side of the mounting plate, for dielectrically spacing the conductive
metal ring portion from the first sensing surface.

US Pat. No. 9,606,137

ENHANCEMENTS FOR DIFFERENTIAL-PRESSURE-DRIVEN FLUID FLOWS

Rosemount Aerospace Inc.,...

1. A pitot tube comprising:
a wall extending longitudinally along an axis, wherein the wall defines:
an inlet aperture at a longitudinal end of the wall;
an outlet aperture opposite the inlet aperture;
an interior cavity extending from the inlet aperture to an outlet aperture, wherein the inlet aperture places the interior
cavity in communication with a space exterior to the wall;

a passage extending through and perpendicular to the wall having an outlet along an exterior surface of the wall; and
an augmenting feature configured to reduce a static pressure at the outlet of the passage.

US Pat. No. 9,587,782

DISPLAY DEVICE HOLDER

Rosemount Aerospace Inc.,...

1. An apparatus for holding a display device, the apparatus comprising:
a plate comprising a rear face and a front face opposite the rear face;
a plurality of engaging members disposed around a periphery of the plate and extending from the plate in a direction from
the rear face to the front face to define an outer boundary of a retention space configured to accept the display device,
the plurality of engaging members including a rotatable engaging member configured to rotate between an engagement position
configured to secure the display device within the retention space and a disengagement position configured to allow removal
of the display device from the retention space;

one or more tensioned guide bearings secured to the rear face of the plate adjacent the rotatable engaging member;
wherein the rotatable engaging member is connected to each of the one or more tensioned guide bearings;
wherein the each of the one or more tensioned guide bearings includes a tensioning element configured to pull the rotatable
engaging member in a direction toward the engagement position;

wherein the each of the one or more tensioned guide bearings are configured to allow movement of the rotatable engaging member
along an axis of the plate between a first position corresponding to the engagement position and a second position corresponding
to the disengagement position;

wherein the tensioning element is configured to pull the rotatable engaging member in the direction toward the engagement
position by being configured to pull the rotatable engaging member toward the first position and to resist movement of the
rotatable engaging member in a direction toward the second position;

wherein the rotatable engaging member is rotatable between the engagement position and the disengagement position that allows
removal of the display device when the rotatable engaging member is in the second position

wherein at least one of the one or more tensioned guide bearings includes a lug extending from the tensioned guide bearing
into a path of the rotatable engaging member between the first position and the second position; and

wherein the rotatable engaging member includes at least one tab configured to engage the lug to prevent rotation of the rotatable
engaging member when the rotatable engaging member is in the disengagement position and maintain the rotatable engaging member
in the disengagement position.

US Pat. No. 9,857,145

TARGET-DESIGNATION DETECTION USED TO SHUTTER CAMERA IMAGES FOR LOCATING TARGET

Rosemount Aerospace Inc.,...

1. A seeker for a Semi-Active Laser (SAL) guided missile, the seeker comprising:
a Short-Wave Infra-Red (SWIR) camera comprising:
a focal plane array having an imaging region comprising a plurality of pixels; and
an optical lens stack configured to receive SWIR light from a scene aligned along an optical axis of the optical lens stack
and further configured to focus at least a portion of the received SWIR light onto the imaging region of the focal plane array
thereby forming an image of the aligned scene, the image comprising pixel intensity data generated by the plurality of pixels;
and

a Pulse Timing Logic (PTL) detector comprising:
a SWIR photo detector aligned parallel to the optical axis so as to be operable to detect a sequence of SWIR pulses generated
by a SAL target designator and reflected by the aligned scene; and

a pulse timer configured to identify a sequence pattern of the detected sequence of SWIR pulses, and further configured to
predict a timing of a next SWIR pulse in the identified sequence pattern so as to synchronize the SWIR camera exposure to
capture a next image of the aligned scene at the predicted timing of the next SWIR pulse.

US Pat. No. 9,567,097

SYSTEM AND METHOD FOR REAL-TIME AIRCRAFT PERFORMANCE MONITORING

Rosemount Aerospace Inc.,...

1. A system for controlling an aircraft:
a memory;
an electronic flight bag processor disposed in communication with said memory, said memory having instruction stored therein
that, when read by said processor, cause the processor to:

receive, at said electronic flight bag processor, real-time aircraft data from aircraft sensors communicative with said electronic
flight bag processor during aircraft flight;

process, by said electronic flight bag processor, said real-time data to determine real-time aircraft mass data;
calculate, by said electronic bag processor, a real-time fuel mileage performance for the aircraft based upon determined aircraft
mass data,

automatically adjust, by an auto-pilot control of the aircraft communicative with said electronic flight bag processor, at
least one of an altitude and a cruise speed of the aircraft based on the calculated real-time fuel mileage performance

determine degradation of fuel mileage performance according a trend in the calculated real-time fuel mileage performance;
and

perform maintenance on the aircraft when the degradation of fuel mileage performance falls below a predetermined threshold.

US Pat. No. 9,783,411

ALL SILICON CAPACITIVE PRESSURE SENSOR

Rosemount Aerospace Inc.,...

1. A capacitive pressure sensor comprising:
a backing wafer;
a sensing wafer comprising:
a support portion bonded to the backing wafer, and
a sensing portion, the sensing portion configured to detect pressure; and
an electrode assembly comprising:
a first silicon layer comprising:
an attachment portion bonded to the sensing wafer; and
a sensing node, the sensing node centered over the sensing portion of the sensing wafer, wherein the sensing node is isolated
from the sensing portion of the sensing wafer by a gap, and wherein the sensing node is isolated from the attachment portion
of the first silicon layer by a separation area;

an insulating layer bonded to the first silicon layer opposite the sensing wafer; and
a second silicon layer bonded to the insulating layer opposite the first silicon layer, the second silicon layer comprising:
a first electrical contact electrically connected with the sensing wafer; and
a second electrical contact electrically connected with the sensing node.

US Pat. No. 9,683,877

PNEUMATIC FILTER

Rosemount Aerospace Inc.,...

1. A modular tuned sensor system comprising:
a main body having a tuned path in fluidic communication with a pressure inlet port;
an enclosing member having a planar structure defining a portion of the tuned path of the main body and sealing the tuned
path from leaking; and the pressure inlet port having an aperture disposed in the enclosing member; and

a sensor terminus having an aperture defined through the main body and in fluidic communication with the tuned path, the sensor
terminus disposed at an opposite end of the tuned path from the pressure inlet port,

wherein the pressure inlet port is configured to be aligned to at least one of an opening in an external surface of an aircraft
and an opening in a propulsion system surface.

US Pat. No. 9,975,647

FLIGHT DECK DOOR SURVEILLANCE AND LOCK CONTROL

Rosemount Aerospace Inc.,...

1. A method comprising:capturing, by a camera system including at least one camera device positioned within an aircraft, image data of an interior of the aircraft;
determining, by a processing device positioned within the aircraft, that one or more alert criteria are satisfied;
outputting, by the processing device in response to determining that the one or more alert criteria are satisfied, at least a portion of the captured image data of the interior of the aircraft for transmission to a ground-based computing device via a wireless communications network;
receiving, by the processing device from the ground-based computing device via the wireless communications network, a lock override command configured to cause the processing device to unlock an electronically-controlled door lock of a flight deck door of the aircraft; and
unlocking, by the processing device in response to receiving the lock override command from the ground-based computing device, the electronically-controlled door lock of the flight deck door;
wherein determining that the one or more alert criteria are satisfied comprises determining that a user-activated unlock override command is active; and
wherein the user-activated unlock override command is activated via an interface located within a flight deck of the aircraft.

US Pat. No. 9,759,621

PSEUDO DIFFERENTIAL PRESSURE SENSING BRIDGE CONFIGURATION

Rosemount Aerospace Inc.,...

1. A pseudo differential pressure sensor comprising:
a first absolute pressure sensor; and
a second absolute pressure sensor,
wherein each of the first and the second absolute pressure sensors comprises:
an elastically deformable membrane configured to deform in response to exposure to an environment having a pressure;
a first piezoresistor located on the elastically deformable membrane at a first region where increasing the pressure of the
environment produces an increasing tensile strain in the first piezoresistor; and

a second piezoresistor located on the elastically deformable membrane at a second region where increasing the pressure of
the environment produces an increasing compressive strain in the second piezoresistor, and

wherein the first and the second piezoresistors of both the first and the second absolute pressure sensors are electrically
connected as a Wheatstone bridge having a first voltage divider leg and a second voltage divider leg, the first voltage divider
leg including the first piezoresistor of the first absolute pressure sensor series connected to the first piezoresistor of
the second absolute pressure sensor at a first output node, the second voltage divider leg including the second piezoresistor
of the first absolute pressure sensor series connected to the second piezoresistor of the second absolute pressure sensor
at a second output node.

US Pat. No. 10,101,174

AIR DATA AIDED INERTIAL MEASUREMENT UNIT

Rosemount Aerospace Inc.,...

1. An inertial measurement unit (IMU) comprising:an inertial sensor assembly comprising:
a plurality of accelerometers, each of the plurality of accelerometers configured to sense acceleration of the IMU along one of a plurality of axes;
a plurality of rate gyroscopes, each of the plurality of rate gyroscopes configured to sense rotational rate of the IMU along one of the plurality of axes; and
a plurality of temperature sensors configured to sense temperature of an operating environment of the plurality of accelerometers and the plurality of rate gyroscopes;
an inertial sensor compensation and correction module configured to apply a set of error compensation values to acceleration sensed by the plurality of accelerometers and to rotational rate sensed by the plurality of rate gyroscopes to produce a compensated acceleration and a compensated rotational rate of the IMU, wherein the set of error compensation values comprises temperature-dependent error compensation values, and wherein the inertial sensor compensation and correction module is configured to apply the set of error compensation values by determining the temperature-dependent error compensation values based on sensed temperature from each of the plurality of temperature sensors; and
a Kalman estimator module configured to:
determine a change in integrated acceleration of the IMU over a time interval based on the compensated acceleration and the compensated rotational rate of the IMU;
determine a set of error correction values based on a difference between the change in the integrated acceleration of the IMU and a change in true airspeed of the IMU; and
provide the set of error correction values to the inertial sensor compensation and correction module;
wherein the inertial sensor compensation and correction module is further configured to:
apply the set of error correction values to each of the compensated acceleration and the compensated rotational rate to produce an error-corrected acceleration and an error-corrected rotational rate; and
output the error-corrected acceleration and the error-corrected rotational rate.

US Pat. No. 9,835,511

HIGH TEMPERATURE FLEXURAL MODE PIEZOELECTRIC DYNAMIC PRESSURE SENSOR

ROSEMOUNT AEROSPACE INC.,...

1. A method for forming a flexural mode pressure sensor comprising:
forming a lower substrate having a cavity formed therein;
forming a sapphire membrane on top of the lower substrate and over the cavity to form a base;
forming a lower electrode on top of the membrane;
forming a piezoelectric material layer on an upper surface of the lower electrode, the piezoelectric material layer being
formed of aluminum nitride (AIN);

forming at least one upper electrode on an upper surface of the piezoelectric material layer; and
direct bonding the membrane to the lower substrate at a temperature greater than 900° C.;
wherein the lower substrate has a particular orientation;
wherein forming the sapphire membrane includes disposing the membrane over the cavity in the same orientation as the lower
substrate; and

wherein forming the lower electrode includes depositing a layer of platinum at a temperature greater than 500° C.

US Pat. No. 9,976,882

METHOD OF FORMING AN ICE RESISTANT PITOT TUBE

ROSEMOUNT AEROSPACE INC.,...

1. A method of forming a pitot tube comprising:forming a substantially cylindrical body portion including an outer surface, a tip portion having an inlet opening, and an interior defining a flow passage;
radially tapering the outer surface from the body portion toward the inlet opening;
disposing at least one electrical coil that includes one or more coil wraps along the flow passage of the pitot tube;
positioning at least one bulkhead along the flow passage to limit travel of particles ingested into the pitot tube; and
arranging at least one of the one or more coil wraps along the flow path downstream of the at least one bulkhead.

US Pat. No. 9,841,304

AIR DATA SYSTEM

Rosemount Aerospace Inc.,...

1. An air data system, comprising:
an avionics system;
a plurality of sensors associated with the avionics system, each of the sensors providing a signal indicative of a parameter
used by the avionic system to determine the flight status of the aircraft;

first and second air data probes, each being pneumatically independent, electronically coupled to the avionics system, and
electronically connected to each other; and

at least one pitot static probe coupled to a pressure transducer through pneumatic tubing, the pressure transducer electronically
coupled to the avionics system.

US Pat. No. 9,759,560

FAULT ISOLATING ALTITUDE SPLITS

Rosemount Aerospace Inc.,...

1. A method of fault isolating an altitude split in a plurality of altitude sensors comprising:
receiving a static pressure reading from a first altitude sensor;
receiving a static pressure reading from a second altitude sensor;
comparing each of the static pressure readings with an expected static pressure value to determine which of the altitude sensors
is the source of a split in altitude readings of the altitude sensors;

providing output indicative of which altitude sensor is the source of the split; and
inspecting only the altitude sensor that is the source of the split in altitude readings.

US Pat. No. 9,689,755

TEMPERATURE SENSORS

Rosemount Aerospace Inc.,...

1. A temperature sensor comprising:
a sensor body extending from a sensor base to an opposed sensor tip along a longitudinal axis and defining a leading edge
and opposed trailing edge, wherein the sensor body defines an interior flow passage with an inlet for fluid communication
of fluid into the interior flow passage and an outlet for exhausting fluid out from the interior flow passage; and

a wedge extension defined on the sensor body between the sensor tip and the sensor base on the leading edge of the sensor
body, wherein the wedge extension is positioned to move a low pressure region aft relative to respective forward low pressure
regions inboard and outboard of the wedge extension along the longitudinal axis, wherein at least a portion of the outlet
is downstream of at least a portion of the wedge extension, relative to the leading edge and the trailing edge, proximate
the low pressure region for increasing airflow from the inlet, through the interior flow passage, to the outlet.

US Pat. No. 10,093,426

SUPER-COOLED WATER-DROPLET SIZE INDICATOR

Rosemount Aerospace Inc.,...

1. A system for indicating a maximum size of super-cooled water droplets in an airstream of an aircraft, the system comprising:a housing having a convex exterior surface on a forward end and having stabilizers projecting from an aft end;
a sequence of indices on the convex exterior surface extending from a leading index at a leading edge of the convex exterior housing through a sequence of increasingly-aft indices, each of the sequence of indices being visible in the absence of ice accretion; and
a gimballed mounting mechanism configured to attach the housing to an aircraft while permitting the housing to freely pitch and yaw with respect to the aircraft, wherein, in response to the airstream engaging the stabilizers, the housing aligns with a direction of the engaging airstream;
wherein ice accretes on an ice-accretion portion of the convex exterior surface, in response to the housing engaging an airstream containing super-cooled water droplets,
wherein an aft-extent of the ice-accretion portion measured from the leading edge is indicative of the maximum size of the super-cooled water droplets, the indices on an ice-free portion of the convex exterior surface indicating the maximum size of the super-cooled water droplets.

US Pat. No. 10,006,813

TEMPERATURE SENSORS

Rosemount Aerospace Inc.,...

6. A temperature sensor comprising:an airfoil body extending from an airfoil base to an opposed airfoil tip along a longitudinal axis, the airfoil body including a wedge extension integral to the airfoil body defined between the airfoil tip and the airfoil base, the airfoil body and wedge extension defining the leading edge of the airfoil body, wherein the airfoil body defines a trailing edge opposed to the leading edge and an interior flow passage with an inlet for fluid communication of fluid into the interior flow passage and an outlet for exhausting fluid out from the interior flow passage, wherein the wedge extension has a wedge angle and position relative to the airfoil body, wherein at least a portion of the outlet is downstream of at least a portion of the wedge extension, relative to the leading edge and the trailing edge, to increase a pressure differential between the inlet and the outlet at Mach numbers 0.55 Mach or higher.

US Pat. No. 9,878,904

MEMS SENSOR WITH ELECTRONICS INTEGRATION

Rosemount Aerospace Inc.,...

1. A microelectromechanical sensor device comprising:
a backing wafer;
a sensing wafer attached to the backing wafer;
a topping wafer attached to the sensing wafer opposite the backing wafer;
a connection layer attached on a surface of the topping wafer opposite the sensing wafer, the connection layer comprising:
a first dielectric layer attached to the surface of the topping wafer opposite the sensing wafer;
a first metal trace layer attached to the first dielectric layer opposite the topping wafer; and
a second dielectric layer attached to the first metal trace layer opposite the first dielectric layer, wherein the second
dielectric layer contains one or more openings configured to provide electrical connection;

at least one integrated circuit component, the at least one integrated circuit component bonded to the connection layer and
electrically connected to the first metal trace layer;

one or more bonds connecting the at least one integrated circuit component to the sensing wafer; and
a housing, wherein the backing wafer is attached to the housing.

US Pat. No. 10,065,853

OPTIMIZED EPOXY DIE ATTACH GEOMETRY FOR MEMS DIE

Rosemount Aerospace Inc.,...

1. A differential pressure sensor comprising:a body with a first end, a second end and a header wall therebetween, wherein the first end and the second end comprise first and second isolator diaphragms connected to first and second process fluid inlets, respectively;
a MEMS pressure sensor including a pressure sensing diaphragm with first and second sides mounted on a hollow cylindrical pedestal that is adhesively attached to an annular bottom of a cylindrical cavity in the header wall, wherein the first side of the pressure sensing diaphragm is coupled to the first isolator diaphragm by a first fill fluid volume, and the second side of the pressure sensing diaphragm is coupled to the second isolator diaphragm through an interior of the hollow pedestal by a second fill fluid volume, the first and second fill fluid volumes being separated by an adhesive seal between the bottom of the cylindrical cavity and a bottom of the hollow pedestal, wherein the cylindrical cavity is defined by a first cylindrical wall portion with a first diameter in contact with the annular bottom, a second cylindrical wall portion with a second diameter larger than the first diameter, and a frustoconical portion in contact with the first cylindrical wall portion and the second cylindrical wall portion, and situated between the first and second cylindrical wall portions, and wherein the first diameter is greater than an outer diameter of the hollow cylindrical pedestal, such that a first radial gap separates the hollow cylindrical pedestal from the first cylindrical wall portion, and a second radial gap wider than the first radial gap separates the hollow cylindrical portion from the second cylindrical wall portion; and
at least one sensor element on the pressure sensing diaphragm configured to provide an indication of pressure differences between the first and second process fluids.

US Pat. No. 9,906,300

OPTICALLY POWERED TRANSDUCER MODULE

Rosemount Aerospace Inc.,...

1. A sensor assembly comprising:
a remote data concentrator (RDC) disposed to transmit a first set of optical pulses and a third optical pulse along an optical
fiber remote from the RDC, wherein:

the first set of optical pulses includes a parameter request signal; and
the third optical pulse comprises an unmodulated energy transmission; and
an optically powered transducer module (OPTM) connected to the optical fiber, and comprising:
a photodiode disposed to receive the first set of optical pulses and the third optical pulse;
an energy storage device configured to be charged by the photodiode from the first set of optical pulses and the third optical
pulse;

a first sensor powered by discharging the energy storage device once the energy storage device is adequately charged, and
disposed to generate first sensor data by sensing a parameter specified by the parameter request signal;

a processor powered by discharging the energy storage device and configured to generate a signal packet from output of the
first sensor; and

a laser powered by discharging the energy storage device and configured to transmit a second set of optical pulses along the
optical fiber to the RDC after the first set of optical pulses is received, the second set of optical pulses including a first
part of the first sensor data, and further configured to transmit a second part of the first data to the RDC after the third
optical pulse, using capacitor charge accumulated from the third optical pulse.

US Pat. No. 10,012,668

TRIPLE-REDUNDANT AIR DATA SYSTEM ARCHITECTURE

Rosemount Aerospace Inc.,...

1. A system comprising:a first multi-function probe (MFP) comprising a first plurality of pressure sensing ports for sensing pressure of an oncoming airflow about an aircraft exterior, the first MFP having a first electronics channel and a second electronics channel;
a first static pressure sensor configured to sense static pressure of the oncoming airflow about the aircraft exterior and electrically coupled with the first electronics channel of the first MFP to form a first air data system providing first aircraft air data parameter outputs;
a second MFP comprising a second plurality of pressure sensing ports for sensing the pressure of the oncoming airflow about the aircraft exterior, the second MFP having a first electronics channel and a second electronics channel; and
a second static pressure sensor configured to sense the static pressure of the oncoming airflow about the aircraft exterior and electrically coupled with the first electronics channel of the second MFP to form a second air data system providing second aircraft air data parameter outputs;
wherein the second electronics channel of the first MFP is electrically coupled with the second electronics channel of the second MFP to form a third air data system providing third aircraft air data parameter outputs.

US Pat. No. 9,829,395

AIR TEMPERATURE SENSOR ARRANGEMENT FOR A VEHICLE AND METHOD OF MEASURING AIR TEMPERATURE

ROSEMOUNT AEROSPACE INC.,...

1. An air temperature sensor arrangement for a vehicle comprising:
a temperature sensor housing having a base portion, an inlet and an outlet;
a main flow path defined by a non-porous continuously curvilinear wall, the main flow path extending from the inlet to the
outlet for separating particulate matter from an inlet airflow; and

a temperature sensor disposed within an internal cavity of the temperature sensor housing wherein the internal cavity is cylindrical
in shape and the internal cavity is positioned perpendicular to the main flow path, wherein the non-porous continuously curvilinear
wall is a solid, non-vented non-porous continuously curvilinear wall; and

an opening in the non-vented non-porous continuously curvilinear wall leading to the internal cavity, the opening having a
diameter equal to a diameter of the internal cavity.

US Pat. No. 9,804,048

PSEUDO DIFFERENTIAL PRESSURE SENSING BRIDGE CONFIGURATION

Rosemount Aerospace Inc.,...

1. A pseudo differential pressure sensor comprising:
a first absolute pressure sensor; and
a second absolute pressure sensor,
wherein each of the first and the second absolute pressure sensors comprises:
an elastically deformable membrane configured to deform in response to exposure to an environment having a pressure;
a first piezoresistor located on the elastically deformable membrane at a first region where increasing the pressure of the
environment produces an increasing tensile strain in the first piezoresistor; and

a second piezoresistor located on the elastically deformable membrane at a second region where increasing the pressure of
the environment produces an increasing compressive strain in the second piezoresistor, and

wherein the first and the second piezoresistors of both the first and the second absolute pressure sensors are electrically
connected as a Wheatstone bridge having a first voltage divider leg and a second voltage divider leg, the first voltage divider
leg including the first piezoresistor of the first absolute pressure sensor series connected to the first piezoresistor of
the second absolute pressure sensor at a first output node, the second voltage divider leg including the second piezoresistor
of the first absolute pressure sensor series connected to the second piezoresistor of the second absolute pressure sensor
at a second output node.

US Pat. No. 10,124,900

AUTOMATED SUPER-COOLED WATER-DROPLET SIZE DIFFERENTIATION USING AIRCRAFT ACCRETION PATTERNS

Rosemount Aerospace Inc.,...

1. A super-cooled water-droplet size measurement system comprising:an ice detector configured to detect ice accretion at a plurality of test locations within a testing region of an exterior surface of an aircraft, wherein ice accretes, in conductive conditions, on at least an ice-accretion portion of the testing region; and
a boundary locator configured to determine a specific one of the plurality of test locations within the testing region of the exterior surface of the aircraft, the determined specific one of the plurality of test locations corresponding to a boundary that separates the ice-accretion portion of the testing region and an ice-free portion of the testing region in conditions that include the atmosphere having super-cooled water droplets up to a predetermined maximum size.

US Pat. No. 10,020,897

PHASED ARRAY TUNING FOR INTERFERENCE SUPPRESSION

Rosemount Aerospace Inc.,...

1. A method for suppressing interference at a critical sensor situated within a system having a plurality of transmission-capable nodes, the method comprising:three-dimensionally mapping the system;
estimating phase shifts for transmissions from the nodes to produce net destructive interference at the critical sensor, based on the three-dimensional mapping of the system;
sensing aggregate electromagnetic signal from the nodes at the critical sensor; and
adjusting the phase shifts based on the sensed aggregate electromagnetic signal.

US Pat. No. 10,012,477

COORDINATING MULTIPLE ORDNANCE TARGETING VIA OPTICAL INTER-ORDNANCE COMMUNICATIONS

Rosemount Aerospace Inc.,...

1. A system configured to be carried by a guided ordnance for in-flight target coordination with other guided ordnances, the system comprising:a forward-pointing optical imager configured to capture in-flight images of a scene aligned with an ordnance axis in a forward direction of ordnance travel, each of the captured images comprising a two-dimensional array of pixel data;
an aft-pointing optical emitter configured to emit a first optical beacon in an aft direction of ordnance travel, thereby communicating to trailing guided ordnances;
an image processor configured to identify, within the captured images, a second optical beacon emitted by a leading guided ordnance; and
a Guidance, Navigation, and Control (GNC) module configured to chart a trajectory of the leading guided ordnance.

US Pat. No. 9,793,046

ROTATING TRANSFORMERS FOR ELECTRICAL MACHINES

Rosemount Aerospace Inc.,...

1. A wound field synchronous machine, comprising:
a rotating transformer, comprising:
a stator printed circuit board (PCB) arranged along a rotation axis;
a rotary PCB axially separated from the stator PCB by a gap and supported for relative rotation about the rotation axis relative
to the stator PCB, a coil surface of the rotary PCB axially opposing a coil surface of the stator PCB across the gap;

a ferromagnetic core connected to a core surface of the stator PCB on a side of the stator PCB axially opposite the coil surface;
a ferromagnetic core connected to a core surface of the rotary PCB on a side of the rotary PCB axially opposite the coil surface;
and

conductors fixed to the coil surfaces of the stator PCB and the rotor PCB, each conductor including, first and second spiral
coils configured to transfer electrical energy between the stator PCB and the rotary PCB, the second spiral coil circumferentially
offset from the first spiral coil about the rotation axis;

a bridge segment extending through the PCB electrically connecting the second spiral coil with the first spiral coil, wherein
the first and second spiral coils are arranged on only one side of the respective PCB such that the first and second spiral
coils of rotary PCB conductor and the first and second spiral coils of the stator PCB conductor are wholly disposed within
the gap;

a main field rotating power converter connected to the rotary PCB of the rotating transformer;
a control power module connected to the stator PCB of the rotating transformer,
wherein the control power module is electromagnetically connected by the stator PCB and the rotary PCB of the rotating transformer
to the main field rotating power converter.

US Pat. No. 10,031,059

CONTROLLED SAMPLING VOLUME OF CLOUDS FOR MEASURING CLOUD PARAMETERS

Rosemount Aerospace Inc.,...

1. A system for measuring cloud parameters, the system comprising:a laser diode configured to transmit the generated a pulse of optical energy;
a first optical fiber configured to transmit the generated pulse of optical energy and to divergently project, from a projection end, the transmitted pulse of optical energy over a first field-of-view determined by a first numerical aperture of the projection end;
a collimating lens aligned within a subfield of the first field-of-view, the collimating lens configured to collimate a narrow-field portion of the divergently projected pulse of optical energy refracted by the collimating lens into a narrow-field projection volume of a cloud atmosphere, a wide-field projection volume of the cloud atmosphere corresponding to a portion of the projected pulse not collimated by the collimating lens;
a second optical fiber having a reception end aligned proximate and substantially parallel to the transmission end of the first optical fiber, the second optical fiber configured to receive a portion of the projected pulse of optical energy reflected by the cloud atmosphere from within a second field of view determined by a second numerical aperture of the reception end, wherein the second field-of-view includes narrow-field and wide-field reception volumes of the cloud atmosphere, the narrow-field reception volume corresponding to locations within the cloud atmosphere from which optical energy is capable of being directed through the collimating lens and received by the second optical fiber, the wide-field reception volume corresponding to locations within the cloud atmosphere from which optical energy is capable of being received by the second optical fiber not through the collimating lens; and
a detector configured to detect and generate a signal indicative of the portion of the projected pulse of optical energy backscattered by the cloud atmosphere and received by the second optical fiber.

US Pat. No. 9,983,112

CONTROLLED SAMPLING VOLUME OF CLOUDS FOR MEASURING CLOUD PARAMETERS

Rosemount Aerospace Inc.,...

1. A system for calculating a metric of Super-cooled Large Droplets (SLDs) in a cloud atmosphere, the system comprising:an optical source configured to divergently project first and second pulses of optical energy about an optical axis;
an optical control module configured to receive at least a portion of each of the first and second divergently projected pulses of optical energy and to direct the received portion of each of the first and second divergently projected pulses within a projection range;
a collimator lens located within the projection range of the optical control module and configured to collimate a portion of each of the first and second pulses of optical energy directed by the optical control module therethrough into a cloud atmosphere;
an optical window located within the projection range of the optical control module and configured to transmit an uncollimated portion of each of the first and second pulses of optical energy directed by the optical control module therethrough into a cloud atmosphere;
an optical detector configured to detect and to generate first and second signals indicative of each of the first and second pulses of optical energy, respectively, backscattered by the cloud atmosphere, wherein a difference between a first ratio and a second ratio of the collimated to the uncollimated portions corresponding to each of the first and second pulses of optical energy is greater than 0.10; and
a processor configured to calculate, based on the generated first and second signals, a metric of SLDs in the cloud atmosphere.

US Pat. No. 9,932,127

SYNTHETIC AIR DATA OUTPUT GENERATION

Rosemount Aerospace Inc.,...

1. A method comprising:receiving, over an aircraft data communications bus, a plurality of non-pneumatic inputs corresponding to aircraft operational parameters;
processing the plurality of non-pneumatic inputs through an artificial intelligence network to generate an air data output value; and
outputting the air data output value to a consuming system for use when a pneumatic-based air data output value is determined to be unreliable;
wherein the artificial intelligence network comprises an artificial neural network having at least one internal layer of neurons that apply one or more weights, biases, or transfer functions to each of the plurality of non-pneumatic inputs to generate the air data output value;
wherein the artificial neural network is pre-trained to determine the one or more weights, biases, or transfer functions; and
wherein processing the plurality of non-pneumatic inputs through the artificial intelligence network to generate the air data output value comprises processing the plurality of non-pneumatic inputs through the artificial neural network without changing the one or more weights, biases, or transfer functions.

US Pat. No. 9,624,787

TOTAL AIR TEMPERATURE SENSORS

Rosemount Aerospace Inc.,...

1. A total air temperature sensor comprising:
an airfoil body extending from an airfoil base to an opposed airfoil tip along a longitudinal axis and defining a leading
edge and opposed trailing edge, wherein the airfoil body defines a high pressure surface and an opposed low pressure surface
each extending longitudinally from the airfoil base to the airfoil tip, wherein the airfoil body defines an interior flow
passage with an inlet for fluid communication of fluid into the interior flow passage and an outlet for exhausting fluid out
from the interior flow passage, and wherein the airfoil body defines a plurality of bleed passages through the airfoil body
between the leading edge and the interior flow passage, wherein each bleed passage has an inlet in the high pressure surface
and an outlet in the low pressure surface; and

a temperature probe mounted within the interior flow passage for measuring temperature of flow through the interior flow passage
to determine total air temperature.

US Pat. No. 10,203,253

TOTAL AIR TEMPERATURE PROBE WITH EFFICIENT PARTICLE PASS THROUGH

Rosemount Aerospace Inc.,...

1. A total air temperature probe comprising:a strut;
a housing defining an airflow passage, the housing having an inlet, an outlet, and an inertial separation bend, a lower end of the housing being connected to the strut;
an airflow inlet channel positioned within a first section of the housing and having a first end at the inlet and a second end at the inertial separation bend downstream of the inlet, the airflow inlet channel including:
an upper wall; and
a lower wall having a first end connected to the inlet and a second end connected to the inertial separation bend;
a sensor flow channel positioned at a lower end of the inertial separation bend and extending to exit ports; and
a main air exit channel positioned within a second section of the housing downstream from the first section and having a first end at the inertial separation bend and a second end at the outlet, the main air exit channel including:
an upper exit channel wall having a first end connected to the upper wall of the airflow inlet channel and a second end connected to the outlet; and
a lower exit channel wall having a first end connected to a rear wall of the sensor flow channel and a second end connected to the outlet;
wherein the upper wall and the lower wall of the airflow inlet channel are configured to be substantially parallel, and an upper portion of the inertial separation bend remains substantially flat with respect to the lower wall; and
wherein a cross-sectional area defined by the upper exit channel wall and the lower exit channel wall decreases in the direction of the outlet.

US Pat. No. 9,981,756

TOTAL AIR TEMPERATURE SENSORS

Rosemount Aerospace Inc.,...

1. A total air temperature sensor comprising:a probe head having an airflow inlet and an airflow outlet;
a strut defining a leading edge and an opposed trailing edge extending along a longitudinal axis, the strut connecting between the probe head and an opposed probe mount; and
a serrated surface defined in the strut aft the leading edge configured to reduce acoustic noise emission from the total air temperature sensor, wherein the serrated surface includes a series of connecting serrations at opposing angles, wherein the serrations have a generally constant geometry repeated through the series, wherein the serrated surface is defined more proximate to the leading edge than to the trailing edge.

US Pat. No. 9,815,569

SYSTEM AND METHOD FOR REAL-TIME AIRCRAFT PERFORMANCE MONITORING

Rosemount Aerospace Inc.,...

1. A system for controlling an aircraft, comprising:
aircraft sensors;
an aircraft interface device comprising an electronic flight bag (EFB) disposed in communication with the aircraft sensors,
the EFB including:

a memory;
a display; and
a processor disposed in communication with said memory and display, said memory having instructions stored therein that, when
read by said processor, cause the processor to:

receive real-time aircraft data from the aircraft sensors during aircraft flight;
process said real-time aircraft data to determine real-time aircraft mass data that accounts for weight decrease due to fuel
burn over time;

calculate a real-time fuel mileage performance for the aircraft based upon determined aircraft mass data and at least one
parameter selected from a group of parameters including an environmental parameter and a performance parameter including speed
data, altitude data, temperature data, pressure data, and angle of attack data,

wherein the real-time data comprises aircraft laden weight, thrust, drag, lift, speed, altitude, and atmospheric conditions
that an aircraft is traveling through; and

transmit the real-time fuel mileage performance to said display of the EFB.

US Pat. No. 10,096,256

METHOD AND SYSTEM FOR AIRCRAFT TAXI STRIKE ALERTING

Rosemount Aerospace Inc.,...

1. A system for calculating position values and/or range data of object(s) in a scene external to an aircraft, the system comprising:a light projector mounted at a projector location on the aircraft and configured to project a collimated beam of light in a controllable direction onto the scene external to the aircraft, the light projector further configured to control an intensity of the projected collimated beam of light, based on the controllable direction of the collimated beam of light;
a camera mounted at a camera location on the aircraft and configured to receive a portion of the collimated beam reflected by the scene, and further configured to focus the received portion onto a focal plane array comprising a plurality of light-sensitive pixels, thereby forming an image of the scene, the image comprising pixel data generated by the plurality of light-sensitive pixels; and
an image processor configured to identify pixel coordinates corresponding to a subset of the plurality of light-sensitive pixels upon which the received portion of the collimated beam reflected by the scene is focused, the image processor further configured to use triangulation, based on the projector location, the camera location, and the identified pixel coordinates, to calculate the position values and/or range data of object(s) in the scene by which the collimated beam of light is reflected.

US Pat. No. 10,043,404

METHOD AND SYSTEM FOR AIRCRAFT TAXI STRIKE ALERTING

Rosemount Aerospace Inc.,...

1. An aircraft collision alerting system comprising:one or more light projectors mounted at one or more projector locations on an aircraft and configured to project spatially-patterned light from the one or more light projectors onto a scene external to the aircraft, thereby illuminating a spatially-patterned portion of the scene;
one or more cameras mounted at one or more camera locations on the aircraft, respectively, each of the one or more cameras configured to receive light reflected from the scene, and further configured to focus the received light onto a focal plane array comprising a plurality of light-sensitive pixels, thereby forming an image of the scene, the image comprising pixel data generated by the plurality of light-sensitive pixels; and
an image processor configured to identify pixel coordinates corresponding to a subset of the plurality of light-sensitive pixels upon which the spatially-patterned light projected by the one or more light projectors and reflected from the spatially-patterned portion of the scene is focused, the image processor further configured to use triangulation, based on the one or more projector locations of the one or more light projectors, the one or more camera locations of the one or more cameras and the identified pixel coordinates, to calculate position values and range data of object(s) in the scene from which the spatially-patterned light projected by the light projector is reflected.

US Pat. No. 10,121,091

IMU-AIDED IMAGE REGISTRATION

Rosemount Aerospace Inc.,...

1. A method comprising:receiving first image data that is captured at a first time by an imager device disposed on a moving body;
receiving second image data that is captured by the imager device at a second time that is subsequent to the first time;
receiving inertial measurement data sensed by an inertial measurement unit (IMU) disposed on the moving body, the inertial measurement data corresponding to sensed motion of the moving body between the first time and the second time;
registering the first image data to the second image data based on the received inertial measurement data to produce first registered image data;
in response to identifying that image features are common to both the first registered image data and the second image data:
registering the first registered image data to the second image data based on the identified features that are common to both the first registered image data and the second image data to produce second registered image data; and
outputting the second registered image data as output registered image data; and
outputting the first registered image data as the output registered image data in response to determining that no image features are common to both the first registered image data and the second image data;
identifying a target within the second image data and the output registered image data;
determining a line-of-sight vector from the imager device to the target based on pixel locations of the identified target within the second image data and the output registered image data; and
providing the line-of-sight vector to a guidance control system configured to control motion of the moving body; and
modifying a trajectory of the moving body based on the line-of-sight vector provided to the guidance control system.

US Pat. No. 10,048,288

ANGLE OF ATTACK VANE WITH DIFFERENTIAL PRESSURE VALIDATION

Rosemount Aerospace Inc.,...

1. An angle of attack sensing system comprising:a rotatable vane comprising a first surface and a second surface opposite the first surface;
a first pressure sensing port disposed in the first surface;
a second pressure sensing port disposed in the second surface;
a vane position sensor configured to output a rotational position signal of the rotatable vane; and
a fault detector configured to output an indication of a rotational fault condition based on a difference between a first sensed pressure from the first pressure sensing port and a second sensed pressure from the second pressure sensing port;
wherein the fault detector is configured to output the indication of the rotational fault condition in response to determining that the difference between the first sensed pressure and the second sensed pressure exceeds a threshold deviation from a baseline pressure difference.

US Pat. No. 10,352,185

FLUSH-MOUNT COMBINED STATIC PRESSURE AND TEMPERATURE PROBE

Rosemount Aerospace Inc.,...

1. A gas turbine engine extending along an axis comprising:a fan section comprising a plurality of rotor cascades and a plurality of stator cascades;
a splitter downstream of the fan section, the splitter including an inner side, an outer side, and an inside surface;
a compressor section downstream of the splitter;
a combustor section downstream of the compressor section;
a first turbine section downstream of the combustor section, the first turbine section being connected to the compressor section;
a second turbine section downstream of the first turbine section, the second turbine section being connected to the fan section; and
a probe assembly comprising:
a probe tip including a sensor face;
a pressure channel extending into the probe tip through the sensor face; and
a temperature channel extending into the probe tip through the sensor face;
a pressure sensor in fluid communication with a pressure channel; and
a temperature sensor in fluid communication with the temperature channel;
wherein:
the temperature channel is substantially parallel to the pressure channel; and
the sensor face is substantially flush with the inner side of the splitter.

US Pat. No. 10,135,159

BOARD-TO-BOARD CONNECTORS AND MOUNTING STRUCTURE

Rosemount Aerospace Inc.,...

1. A method of assembling a circuit card assembly, the method comprising:forming a first three dimensional trace by layer-by-layer additive manufacturing, wherein the first three dimensional trace comprises a first end and a second end;
forming a support structure and a fixture, wherein the support structure is connected to the first three dimensional trace and the fixture is connected to the support structure;
attaching the first three dimensional trace to a first printed wiring board with a first receiving feature by inserting the first end of the first three dimensional trace into the first receiving feature; and
attaching a second printed wiring board to the first three dimensional trace by receiving the second end of the first three dimensional trace in a second receiving feature of the second printed wiring board.

US Pat. No. 10,126,193

COMPACT OR MINIATURE HIGH TEMPERATURE DIFFERENTIAL PRESSURE SENSOR CAPSULE

Rosemount Aerospace Inc.,...

1. A differential pressure sensor comprising:a header with an upper end, a lower end, a side wall, and an interior cavity including an upper cavity portion and a lower cavity portion;
a pedestal attached to a bottom of the lower cavity portion and extending into the upper cavity portion;
a MEMS pressure sensor mounted to an upper end of the pedestal and positioned in the upper cavity portion, the MEMS pressure sensor including a sensor diaphragm containing sensor elements and having a top surface and a bottom surface;
a chamber positioned in the upper cavity portion and surrounding the MEMS pressure sensor;
a spacer positioned on the chamber and within the upper cavity portion;
an upper isolator plate mounted on the upper end of the header;
an upper isolator diaphragm mounted on the upper isolator plate;
a lower isolator plate mounted on the lower end of the header;
a lower isolator diaphragm mounted on the lower isolator plate;
an upper central axial passage through the upper isolator plate and the spacer; and
a lower central axial passage through the lower isolator plate, the header, and the pedestal to define a fluid connection between the lower isolator diaphragm and the bottom surface of the sensor diaphragm; wherein the upper and lower central axial passages are coaxially aligned.

US Pat. No. 10,109,939

FLEX CIRCUIT CONNECTOR CONFIGURATION

Rosemount Aerospace Inc.,...

1. A flexible circuit connector for connecting first and second circuit boards of an airborne device, the flexible circuit connector comprising:a first connector configured to connect to the first circuit board, wherein the first circuit board is positioned within a first compartment of the airborne device;
a second connector configured to connect to the second circuit board, wherein the second circuit board is positioned within a second compartment of the airborne device;
a spiral portion connected between the first and second connectors, wherein the spiral portion comprises a circumferential portion that extends around the second connector, and wherein the entirety of the spiral portion is in a common plane with the second connector during an operational state; and
a middle portion connected between the first connector and the spiral portion, wherein the common plane is configured perpendicular to the middle portion during the operational state;
wherein the first compartment is detachable from the second compartment, and wherein the spiral portion is configured to pull out of the common plane when the first and second compartments are detached and pulled apart from one another.

US Pat. No. 10,151,641

TOTAL AIR TEMPERATURE PROBES FOR REDUCING DEICING HEATER ERROR

Rosemount Aerospace Inc.,...

1. A total air temperature probe comprising:a probe head having an airflow inlet, a main airflow outlet, a main probe head wall extending from the airflow inlet to the main airflow outlet, and a flow separation bend wall positioned between the airflow inlet and the main airflow outlet, the flow separation bend wall being opposite the main probe head wall across a primary flow passage defined through the probe head from the airflow inlet to the main airflow outlet;
opposed sidewalls, each sidewall connecting between the main probe head wall and the flow separation bend wall;
a flow separation trip feature defined on an interior surface of the main probe head wall for tripping a boundary layer flow separation in flow in the primary flow passage, wherein the flow separation trip feature spans the main probe head wall from one of the opposed sidewalls to the other;
a strut connecting between the probe head and an opposed probe mount, the strut defining a sensor passage connected to the primary flow passage and oriented at an angle relative to a flow axis defined from the airflow inlet to the main airflow outlet, wherein a temperature sensor is mounted within the sensor passage for total air temperature measurements;
a thermal shield is included in the sensor passage between the sensor and an interior wall of the sensor passage; and
a deicing heater operatively connected to heat the probe head and strut to form a heated boundary layer within the primary flow passage with a portion of the heated boundary layer passing from the primary flow passage into the sensor passage, wherein the flow separation trip feature is positioned so the portion of the heated boundary layer passing into the sensor passage avoids spilling into the thermal shield for reduction of deicing heater error.

US Pat. No. 10,120,785

AUTOMATIC GENERATION OF DATA COUPLING AND CONTROL COUPLING TEST CONDITIONS

Rosemount Aerospace Inc.,...

1. A method comprising:parsing, by an automatic test generator (ATG), a model file including syntactical notations describing a computer-executable design model of operational software of an aircraft electronic device;
wherein parsing comprises:
identifying one or more design model control coupling data, corresponding to calls between functional modules of the design model using the syntactical representation of interdependence of the function modules of the design model;
identifying one or more design model data coupling, comprising data exchanged between each of the functional modules of the design model;
automatically generating, by the ATG, a plurality of test conditions, wherein for each of the identified one or more design model control coupling data and identified one or more design model data coupling, a respective test condition is generated to test whether the operational software of the aircraft electronic device satisfies the design model data coupling or the design model control coupling identified;
generating a test procedure that implements the plurality of test conditions;
executing the test procedure on the operational software of the aircraft electronic device;
wherein executing the test procedure on the operational software of the aircraft electronic device comprises:
halting, for each of the plurality of test conditions, execution of the operational software;
determining, while the execution of the operational software is halted, whether the operational software satisfies the respective test condition; and
resuming execution of the operational software after determining whether the operational software satisfies the respective test condition; and
outputting, for each of the plurality of test conditions, an indication of whether the operational software of the aircraft electronic device satisfies the respective test condition.

US Pat. No. 10,060,943

SYMMETRIC MEMS PIEZOELECTRIC ACCELEROMETER FOR LATERAL NOISE

Rosemount Aerospace Inc.,...

1. A piezoelectric accelerometer comprising:a first acceleration sensor including:
a first axis;
a first proofmass having an axis coincident with the first axis;
a first axially-thin membrane portion coupled to and laterally extending from a first lateral end of the first proofmass; and
a first piezoelectric transducer on the first membrane portion,
wherein the first acceleration sensor is axially asymmetric, and
a second acceleration sensor including:
a second axis;
a second proofmass having an axis coincident with the second axis; and
a second axially-thin member portion coupled to and laterally extending from a first lateral end of the second proofmass;
wherein the second acceleration sensor is axially asymmetric, and
wherein the first and second acceleration sensors are mechanically coupled to one another at second lateral ends of the first and second acceleration sensors such that the first axis is coincident with the second axis.

US Pat. No. 10,151,785

PROBE HEATER REMAINING USEFUL LIFE DETERMINATION

Rosemount Aerospace Inc.,...

1. A system for an aircraft, the system comprising:a probe that includes a heater comprising a resistive heating element routed through the probe, wherein an operational voltage is provided to the resistive heating element to provide heating for the probe, and wherein the heating element comprises:
a lead wire;
a metallic sheath; and
insulation between the lead wire and the metallic sheath;
a capacitive measurement circuit connected between the lead wire and the metallic sheath and configured to provide an output indicative of an element capacitance between the lead wire and the metallic sheath; and
a control circuit connected to receive the element capacitance and configured to determine and monitor a resonance frequency of the element capacitance over time;
wherein the control circuit is further configured to determine a remaining useful life of the probe based on the resonance frequency of the resistive heating element over time.

US Pat. No. 10,126,101

SEEKER/DESIGNATOR HANDOFF SYSTEM FOR USE IN DUAL-MODE GUIDED MISSILES

Rosemount Aerospace Inc.,...

1. A dual-mode seeker for a guided missile, the dual-mode seeker comprising:a first-mode target locator configured to:
detect laser pulses reflected by a target within a scene aligned along a missile axis, each of the laser pulses projected onto the target by a remote Laser Target Designator (LTD) thereby designating the target;
determine, based on the detected laser pulses, a direction of the designated target relative to the optical axis; and
generate an output signal indicative of the direction of the designated target relative to the missile axis;
a second-mode target locator configured to:
capture Short-Wavelength InfraRed (SWIR) images of the aligned scene, each of the SWIR images captured at an exposure time period in which the remote LTD is not projecting a laser pulse onto the designated target;
identify an image feature within each of the SWIR images, the image feature corresponding to the designated target;
determine, based on the identified image feature, the direction of the designated target relative to the missile axis; and
generate an output signal indicative of the direction of the designated target relative to the missile axis; and
an active SWIR illuminator aligned parallel to the missile axis and configured to:
illuminate the designated target during an illumination time offset by a Phase Offset Interval (POI) from the exposure time period.

US Pat. No. 10,101,145

PASSIVE TEMPERATURE ERROR COMPENSATION FOR STRAIN GAUGE PRESSURE SENSORS

Rosemount Aerospace Inc.,...

1. A sensor system comprising:first, second, third, and fourth strain gauges connected at respective first, second, third, and fourth nodes to form a Wheatstone bridge, and configured to provide an output voltage indicative of a sensed pressure using an input voltage; and
a passive compensation circuit configured to control current through the plurality of strain gauges to control the output voltage for a selected temperature range and a selected pressure range, wherein the passive compensation circuit comprises:
a first span resistor configured to control a range of the output voltage for the pressure range and connected between the first node and the input voltage;
first and second compensation resistors configured to control current provided to the first, second, third, and fourth strain gauges; and
a first zero offset resistor configured to control a base value of the output voltage for zero pressure, wherein the first zero offset resistor is connected between the second node and a fifth node, the first compensation resistor is connected between the first node and the fifth node, and the second compensation resistor is connected between the fifth node and the third node, and wherein the output voltage is measured across the second and fourth nodes.

US Pat. No. 10,132,824

AIR DATA SENSING PROBE WITH ICING CONDITION DETECTOR

Rosemount Aerospace Inc.,...

1. A system comprising:a device having a first surface configured to be exposed to airflow about an exterior of an aircraft, the device including a first self-compensating heater configured to heat the first surface;
a first current monitor configured to produce a first measurement value representing electrical current flow through the first self-compensating heater;
one or more processors; and
computer-readable memory encoded with instructions that, when executed by the one or more processors, cause the system to:
receive aircraft flight condition data; and
produce an icing condition signal based upon the first measurement value and the aircraft flight condition data.

US Pat. No. 10,203,256

DUPLEX PRESSURE TRANSDUCERS

Rosemount Aerospace Inc.,...

1. A transducer baseplate comprising:a base with a protrusion extending from the base along a longitudinal axis;
a pair of transducer receptacles defined within the protrusion, wherein the transducer receptacles are opposed from one another across the longitudinal axis, wherein the transducer receptacles are in fluid and operational isolation from one another; and
a pair of pressure plena separated by a plenum wall, one plenum in fluid communication with each receptacle, respectively, wherein the pressure plena are in fluid and operational isolation from one another within the protrusion, wherein each plenum is in fluid connection with an area external to the protrusion through a respective pressure line, and wherein the pressure lines are at an oblique angle with respect to one another and provide a direct fluid path to their respective receptacles.

US Pat. No. 10,207,810

OPTICALLY DETECTING CLOUD METRICS USING SAMPLED ANALOG MEASUREMENTS OF LIGHT REFLECTION

Rosemount Aerospace Inc.,...

1. An optical icing conditions detector comprising:a pulsed laser system configured to generate a first pulse of circularly polarized light having a first wavelength; and
two analog channels, each of which includes:
a peak detector configured to generate an analog signal indicative of a peak of a light signal reflected by a cloud;
a post-peak slope detector configured to generate, based on one or two post-peak samples of the signal reflected by the cloud, an analog signal indicative of a rate of decay of the light signal reflected by the cloud, the rate of decay corresponding to a time following a time of the detected peak; and
a reflection fluctuation detector configured to generate an analog signal indicative of a magnitude of high-frequency fluctuation of the light signal reflected by the cloud;
wherein a first of the two analog channels is configured to operate on a first reflected light signal corresponding to light of the first pulse reflected by the cloud, the first reflected light signal having a left-hand circular polarization;
wherein a second of the two analog channels is configured to operate on a reflected light signal corresponding to light of the first pulse reflected by the cloud, the second reflected light signal having a right-hand circular polarization; and
wherein a microprocessor is configured to calculate metrics, which include:
based on the analog signal indicative of the peak and the analog signal indicative of the rate of decay, a backscatter coefficient; and/or
based on a ratio of calculations based on analog signals from the first channel to calculations based on analog signals from the second channel, an ice/liquid ratio; and/or
based on the magnitude of high-frequency fluctuation indicated by the analog signal generated by the reflection fluctuation detector, a measure of a density of large particles in the cloud.

US Pat. No. 9,383,170

LASER-AIDED PASSIVE SEEKER

ROSEMOUNT AEROSPACE INC, ...

1. A laser-aided semi-passive seeker comprising:
a semi-active laser seeker having an imager configured to detect and decode laser-based energy and image ambient energy;
said imager further configured to generate at a first predefined rate a sequence of semi-active laser-based images containing
a laser spot illuminating a target;

said imager said imager further configured to generate at a second predefined rate a sequence of passive ambient-energy images
containing said target without said laser spot;

a laser-aided semi-passive tracker configured to receive said sequence of semi-active laser-based images at said first predefined
rate;

said laser-aided semi-passive tracker further configured to receive said sequence of passive ambient-energy images at said
second predefined rate;

said laser-aided semi-passive tracker further configured to process an image pair comprising one of said sequence of semi-active
laser-based images received within a predetermined time of one of said sequence of passive ambient-energy images in order
to map laser spot coordinates of said laser spot of said one of said sequence of semi-active laser-based images to said one
of said sequence of passive ambient-energy images; and

said laser-aided semi-passive tracker further configured to track said laser spot coordinates on said sequence of passive
ambient-energy images that are not received by said laser-aided semi-passive tracker within said predetermined time of said
one of said sequence of said semi-active laser based images.

US Pat. No. 10,180,449

PROBE HEATER REMAINING USEFUL LIFE DETERMINATION

Rosemount Aerospace Inc.,...

1. A system for an aircraft, the system comprising:a probe positioned on the aircraft to determine environmental characteristics, wherein the probe includes a heater comprising a resistive heating element routed through the probe, and wherein an operational current is provided to the resistive heating element to provide heating for the probe;
a control circuit; and
a current sensor connected to provide a sensed current to the control circuit indicative of the operational current;
wherein the control circuit is configured to monitor the sensed current at a plurality of common points of operation of the probe over time and determine, using a predetermined function, a remaining useful life of the probe based on the operational current at each of the plurality of common points of operation.

US Pat. No. 10,249,203

METHOD AND SYSTEM FOR PROVIDING DOCKING GUIDANCE TO A PILOT OF A TAXIING AIRCRAFT

Rosemount Aerospace Inc.,...

1. A system for providing docking guidance to a pilot of a taxiing aircraft, the system comprising:a camera configured for mounting at a camera location on the taxiing aircraft, the camera configured to generate a two-dimensional image of a scene external to the taxiing aircraft, the generated two-dimensional image comprising pixel data generated by the two-dimensional array of light-sensitive pixels; and
a digital processor configured to identify first and second sets of pixel coordinates within the generated two-dimensional image of the scene external to the taxiing aircraft, the identified first and second sets of pixel coordinates corresponding to two vertically-separated and two laterally-separated indicia, respectively, of an alignment fiducial indicating a parking location for the taxiing aircraft, the digital processor further configured to calculate, based at least in part on the identified first pixel coordinates corresponding to the two vertically-separated indicia, a range to the parking location indicated by the alignment fiducial.

US Pat. No. 10,281,353

PNEUMATIC AIR DATA PROBE WITH ELLIPTICAL CROSS SECTION

Rosemount Aerospace Inc.,...

1. An air data probe comprising:a probe head, the probe head defining a longitudinal axis extending from a forward tip of the probe head to an aft end of the probe head, the probe head having a non-circular elliptical cross section orthogonal to the longitudinal axis; and
an air data sensing port disposed in the probe head aft of the forward tip;
wherein the air data probe further comprises a base plate configured to mount the air data probe to an exterior of an aircraft;
wherein the probe head comprises a proximate side and a distal side with respect to the base plate, the proximate side facing the base plate, and the distal side opposite the proximate side;
wherein the elliptical cross section comprises a major axis and a minor axis perpendicular to the major axis; and
wherein the minor axis extends between the proximate side and the distal side.

US Pat. No. 10,228,398

SYSTEM AND METHOD FOR MINIMIZING MAGNETIC FIELD EFFECT ON AN ISOLATED MAGNETOMETER

Rosemount Aerospace Inc.,...

1. A system for measuring an electrical current to a heater, the system comprising:an electrical line between a first power source and the heater;
a control sensor adjacent to the electrical line, the control sensor being a Hall Effect sensor to measure a first magnetic field induced by the electrical current and an ambient magnetic field and output a resulting first voltage;
a compensation sensor proximate the control sensor, the compensation sensor being a Hall effect sensor with the same orientation as the control sensor to measure a second magnetic field induced by the ambient magnetic field and output a resulting second voltage; and
an operational amplifier electrically connected to the control sensor and the compensation sensor, the operation amplifier able to receive the first voltage and the second voltage and determine the electrical current flowing through the electrical line.

US Pat. No. 10,343,783

METHOD AND APPARATUS OF DETECTING LIQUID WATER IN A CLOUD

Rosemount Aerospace Inc.,...

1. A cloud phase detector comprising:a magnetostrictive resonator having a baseline resonant frequency in an ice-free and liquid-water-free condition, the magnetostrictive resonator configured to resonate at a resonant frequency indicative of a measure of ice accretion upon an exterior surface of the magnetostrictive resonator;
a processor; and
computer-readable memory encoded with instructions that, when executed by the processor, cause the cloud phase detector to:
detect the resonant frequency of the magnetostrictive resonator;
detect temporal variations of the resonant frequency of the magnetostrictive resonator; and
generate a signal indicative of liquid-water content if either the detected resonant frequency is a first threshold less than the baseline resonant frequency or the detected temporal variations of the resonant frequency are greater than a second threshold.

US Pat. No. 10,309,852

REDUNDANT MEASUREMENT OF PSEUDO DIFFERENTIAL PRESSURE USING ABSOLUTE PRESSURE SENSORS

Rosemount Aerospace Inc.,...

1. A system for providing redundant measurement of pseudo differential pressure, the system comprising:a first absolute-pressure sensor exposed to a first environment, the first absolute-pressure sensor including a plurality of pressure transducers configured in a first Wheatstone bridge, the first Wheatstone bridge having first and second output nodes that operationally generate first and second output signals that increase and decrease, respectively, in response to increasing pressure of the first environment;
a second absolute-pressure sensor exposed to a second environment, the second absolute-pressure sensor including a plurality of pressure transducers configured in a second Wheatstone bridge, the second Wheatstone bridge having third and fourth output nodes that operationally generate first and second output signals that increase and decrease, respectively, in response to increasing pressure of the second environment;
a first difference calculator electrically coupled to the first and third output nodes of the first and second absolute-pressure sensors, respectively, the first difference calculator generating, based on a difference between the first and third output signals of the first and third output nodes, a first measurement signal indicative of a pressure difference between the first and second environments; and
a second difference calculator electrically coupled to the second and fourth output nodes of the first and second absolute-pressure sensors, respectively, the second difference calculator generating, based on a difference between the second and fourth output signals of the second and fourth output nodes, a second measurement signal indicative of the pressure difference between the first and second environments.

US Pat. No. 10,276,954

BOARD-TO-BOARD CONNECTORS AND MOUNTING STRUCTURE

Rosemount Aerospace Inc.,...

1. A circuit card assembly comprising:a first printed wiring board with a first receiving feature;
a second printed wiring board with a second receiving feature;
a first three dimensional trace attached to the first printed wiring board, wherein the first three dimensional trace is formed by a layer-by-layer additive manufacturing process, wherein the first three dimensional trace comprises a first end and a second end, wherein the first end of the first three dimensional trace engages with the first receiving feature of the first printed wiring board, wherein the second end of the first three dimensional trace engages with the second printed wiring board;
a support structure; and
a fixture, wherein the support structure is connected to the first three dimensional trace and the fixture is connected to the support structure.

US Pat. No. 10,217,371

METHOD AND SYSTEM FOR AIRCRAFT TAXI STRIKE ALERTING USING ADAPTIVE FIELD OF VIEW

Rosemount Aerospace Inc.,...

1. A system for calculating position values and/or range data of an object(s) external to an aircraft, the system comprising:a mode selector configured to determine an illumination field of view;
a projector mounted at a projector location on the aircraft and configured to project structured light within the illumination field of view, thereby illuminating the object(s) external to the aircraft that are within the illumination field of view;
a camera mounted at a camera location on the aircraft and configured to receive a portion of the structured light reflected by the object(s) within the illumination field of view, and further configured to focus the received portion of the structured light onto a focal plane array comprising a plurality of light-sensitive pixels, thereby forming an image of object(s) within the illumination field of view, the image comprising pixel data generated by the plurality of light-sensitive pixels; and
an image processor configured to identify pixel coordinates corresponding to a subset of the plurality of light-sensitive pixels upon which the received portion of the structured light reflected by the object(s) within the illumination field of view is focused, the image processor further configured to use triangulation, based on the projector location, the camera location, and the identified pixel coordinates, to calculate the position values and/or range data of the object(s) within the illumination field.

US Pat. No. 10,247,652

CONTROLLED SAMPLING VOLUME OF CLOUDS FOR MEASURING CLOUD PARAMETERS

Rosemount Aerospace Inc.,...

1. A system for calculating a metric of Super-cooled Large Droplets (SLDs) in a cloud atmosphere, the system comprising:an optical source configured to divergently project first and second pulses of optical energy about an optical axis;
an optical control module configured to receive at least a portion of each of the first and second divergently projected pulses of optical energy and to direct the received portion of each of the first and second divergently projected pulses within a projection range;
a collimator lens located within the projection range of the optical control module and configured to collimate a portion of each of the first and second pulses of optical energy directed by the optical control module therethrough into a cloud atmosphere;
an optical window located within the projection range of the optical control module and configured to transmit an uncollimated portion of each of the first and second pulses of optical energy directed by the optical control module therethrough into a cloud atmosphere;
an optical detector configured to detect and to generate first and second signals indicative of each of the first and second pulses of optical energy, respectively, backscattered by the cloud atmosphere; and
a processor configured to calculate, based on the generated first and second signals, a metric of SLDs in the cloud atmosphere.

US Pat. No. 10,227,139

HEATED AIR DATA PROBES

Rosemount Aerospace Inc.,...

1. An air data probe comprising:a probe head defining a longitudinal axis between a forward tip and aft base;
a heater coil positioned within the probe head; and
a thermocouple having a sense end in the forward tip to measure the temperature in the forward tip, wherein the thermocouple includes a thermocouple coil, wherein windings of the thermocouple coil are wound between windings of the heater coil.

US Pat. No. 10,444,368

MEASURING CLOUD METRICS USING DIVERGING QUASI-OPTICAL RADAR

Rosemount Aerospace Inc.,...

1. A system for measuring metrics of backscattering populations of water particles of a cloud atmosphere, the system comprising:a quasi-optical transmitter configured to project a pulse of quasi-optical energy from a horn aperture into a first divergent projection volume of the cloud atmosphere, the first divergent projection volume defined by a first axis of projection and a first angle of projection about the first axis of projection, the first angle of projection based on a ratio of a transverse dimension of the horn aperture to a wavelength of the quasi-optical energy;
a quasi-optical receiver configured to detect a portion of the projected pulse of quasi-optical energy backscattered by a first backscattering population of water particles within the first divergent projection volume of the cloud atmosphere;
a cloud metric calculator configured to determine, based on a first detected portion of the projected pulse of quasi-optical energy backscattered by the first backscattering population of water particles within the first divergent projection volume of the cloud atmosphere, a first density of the first backscattering population of water particles within the first divergent projection volume of the cloud atmosphere;
an optical transmitter configured to generate a pulse of optical energy;
a transmitter fiber configured to receive the generated pulse of optical energy and to project the received pulse of optical energy from a transmission end of the optical fiber into a second divergent projection volume of the cloud atmosphere, the second divergent projection volume defined by a second axis of projection and a second angle of projection about the second axis of projection, the second angle of projection based on the numerical aperture of the fiber; and
a receiver fiber configured to receive a portion of the projected pulse of optical energy backscattered by a second backscattering population of water particles within the second divergent projection volume of the cloud atmosphere,
wherein the cloud metric calculator is further configured to determine, based on a detected portion of the projected pulse of optical energy backscattered by the second backscattering population of water particles within the second divergent projection volume of the cloud atmosphere, a second density of the second backscattering population of water particles within the divergent projection volume of the cloud atmosphere.

US Pat. No. 10,320,141

HARD TARGET DETECTION FOR OPTICAL SYSTEMS

Rosemount Aerospace Inc.,...

1. A hard target detection system of a free-space laser system, the hard target detection system comprising:a laser configured to emit a laser beam along an optical path through transmitter optics into a field of view;
an optical detector positioned along a laser transmitter path and configured to receive retroreflections of the laser beam;
electronics configured to determine if an output of the optical detector is indicative of presence of a hard target within the field of view, and control the laser to a safe state if the output is indicative of presence of the hard target; and
receiver optics configured to direct backscatter of the laser beam to sensor detector elements, and wherein the optical detector is separate from the sensor detector elements.

US Pat. No. 10,371,000

FLUSH-MOUNT COMBINED STATIC PRESSURE AND TEMPERATURE PROBE

Rosemount Aerospace Inc.,...

1. A gas turbine engine extending along an axis comprising:a fan section comprising a plurality of rotor cascades and a plurality of stator cascades;
a splitter downstream of the fan section, the splitter including an inner side, an outer side, and an inside surface;
a compressor section downstream of the splitter;
a combustor section downstream of the compressor section;
a first turbine section downstream of the combustor section, the first turbine section being connected to the compressor section;
a second turbine section downstream of the first turbine section, the second turbine section being connected to the fan section; and
a probe assembly comprising:
a probe tip including a sensor face;
a pressure channel extending into the probe tip through the sensor face; and
a temperature channel extending into the probe tip through the sensor face;
a pressure sensor in fluid communication with a pressure channel; and
a temperature sensor in fluid communication with the temperature channel;
wherein:
the temperature channel is substantially parallel to the pressure channel; and
the sensor face is substantially flush with the inner side of the splitter.

US Pat. No. 10,281,254

PHASED ARRAY LIDAR IN ORDNANCE CONTROL

Rosemount Aerospace Inc.,...

1. A system for controlling a burst event of an explosive charge carried by a ballistic ordnance, the system comprising:a controller;
a laser electrically coupled to the controller, the laser generating, in response to receiving from the controller a timing signal at an emission time, a pulse of coherent light;
a two-dimensional array of light emitters, each optically coupled to receive a portion of the generated pulse of coherent light from the laser via an optical wave guide, and to emit the received portion of coherent light;
a plurality of phase modulators electrically coupled to the controller, the plurality of phase modulators configured to coordinate, in response to receiving from the controller a signal indicative of an emission angle, relative phases of emitted portions of the coherent light so as to form a beam of light directed at the emission angle; and
an optical detector electrically coupled to the controller, the optical detector configured to detect the directed beam of light reflected by a ground surface at a detection time,
wherein the controller is further configured to:
calculate, based on a difference between the detection time and the emission time, a distance between the system and the ground surface; and
generate a burst control signal configured to initiate the burst event of the explosive charge carried by the ballistic ordnance.

US Pat. No. 10,435,161

SURFACE SENSING FOR DROPLET SIZE DIFFERENTIATION

Rosemount Aerospace Inc.,...

1. A system capable of sensing ice accretion on an airfoil of an aircraft, the system comprising:a sensor having a sensing surface region, the sensor configured to be mounted at a mounting location aft of a leading edge of the airfoil such that the sensing surface region is flush with a surrounding adjacent surface of the airfoil, wherein, in certain flight conditions, water droplets of sizes less than or equal to a predetermined threshold do not impinge the sensor surface region;
a sensor driver coupled to the sensor and configured to provide an excitation signal to the sensor; and
a signal detector configured to detect a sensor signal responsive to the provided excitation signal, the detected sensor signal indicative of water particles of sizes exceeding the predetermined threshold impinging the sensing surface region of the sensor.

US Pat. No. 10,422,702

TOTAL AIR TEMPERATURE PROBE WITH REDUCED ICING SENSOR FLOW PASSAGE GEOMETRY

Rosemount Aerospace Inc.,...

1. A total air temperature probe comprising:a housing defining a total air temperature sensor flow passage; and
a sensor assembly positioned within the total air temperature sensor flow passage,
the sensor assembly including:
an element flow tube, wherein an upper portion of the element flow tube is an entrance including a plurality of protrusions that extend in an upstream direction; and
a sensing element within the element flow tube.

US Pat. No. 10,378,859

HARMONIC SHUTTER RESOLVER ALGORITHM FOR MULTIMODE SEEKER

Rosemount Aerospace Inc.,...

1. A method of detecting laser pulses having a predetermined pulse period by a multimode seeker, the method comprising:capturing image data, by the multimode seeker, during a search period, wherein the search period includes a plurality of search cycles, and wherein a duration of each of the plurality of search cycle is equal to the predetermined pulse period plus a predetermined drift period, including
executing a plurality of search expose cycles at a predetermined duty cycle, each of the plurality of search expose cycles including a search expose pulse during which the image data is captured and a dark time during which the image data is not captured;
detecting, from the image data, at least one laser candidate, including
performing, by an image processor, a peak-to-side-lobe analysis for the image data of each of the plurality of expose cycles; and
determining the at least one candidate laser pulse based upon the peak-to-side-lobe analysis of the image data; and
tracking, by the multimode seeker, the at least one candidate laser during a track period including evaluating, by an image processor, the at least one candidate laser; and
locking, by the multimode seeker, the at least one candidate laser as a tracked laser.

US Pat. No. 10,511,762

SYSTEM AND METHOD FOR AIRCRAFT CAMERA IMAGE ALIGNMENT

Rosemount Aerospace Inc.,...

1. An alignment system for images produced by cameras externally mounted on an aircraft, the alignment system comprising:a plurality of cameras on the aircraft positioned to provide images of the aircraft;
a visual display positioned at a flight deck of the aircraft, wherein the visual display displays a plurality of images provided by the plurality of cameras; and
an alignment device positioned at an electronics bay of the aircraft, the alignment device including a user interface comprising:
user inputs for selecting one of the plurality of cameras at the electronics bay and for aligning an image from the camera selected on the visual display at the flight deck, the user inputs including:
a camera selection button; and
a plurality of positioning buttons configured to receive pan and crop adjustment inputs for a selected image for the alignment device;
a depiction of the aircraft; and
a plurality of indicators positioned adjacent the depiction, each of the plurality of indicators representing selection of one of the cameras at the electronics bay for aligning the image from that camera on the visual display at the flight deck;
a camera selection interface configured to select one of the plurality of cameras as a source of a selected image based upon input from the camera selection button; and
a pan and crop adjustment processor configured to align a selected image based upon pan and crop adjustment inputs from the positioning buttons.

US Pat. No. 10,451,892

ACTIVE ISOLATION FOR SEEKER OPTICS

Rosemount Aerospace Inc.,...

1. An optical system configured to counteract deformation and/or vibration due to a munition launch and/or flight acceleration, the system comprising:a power supply;
a control system;
a cylindrical optical lens stack;
a cylindrical holder attached to and surrounding the optical lens stack;
a piezoelectric cylinder attached to and surrounding the cylindrical holder and connected to both the control system and the power supply,
wherein the control system actuates the piezoelectric cylinder to counteract the deformation and/or the vibration of the optical lens stack caused by the munition launch and/or the flight acceleration.

US Pat. No. 10,421,544

SYSTEMS AND METHODS FOR POSITIONING A HOIST AND HOOK

ROSEMOUNT AEROSPACE INC.,...

1. A hoist and hook system, comprising:a hoist;
a cable coupled to the hoist;
a hook assembly coupled to the cable;
a position sensor disposed on one of the hoist or the hook assembly and configured to detect a position of a target, located remote from the position sensor, relative to at least one of the hoist or the hook assembly; and
a compass disposed on the hook assembly and configured to determine an orientation of the hook assembly relative to the hoist.

US Pat. No. 10,393,766

WATER MANAGEMENT SYSTEM FOR ANGLE OF ATTACK SENSORS

Rosemount Aerospace Inc.,...

1. An angle of attack sensor comprising:a housing having an open first end and a closed second end;
a heated chassis positioned within the open first end of the housing;
a mounting plate positioned on the heated chassis adjacent the open first end of the housing such that an internal chamber is formed between the heated chassis and the mounting plate;
a transducer compartment between the heated chassis and the closed second end of the housing; and
a water management system located adjacent the internal chamber and the transducer compartment, the water management system including:
an annular chamber positioned in the internal chamber;
a first tube at a first end of the annular chamber, the first tube having a hole such that the first tube is in fluid communication with the annular chamber and the internal chamber; and
a second tube at a second end of the annular chamber, the second tube being in fluid communication with the annular chamber and the transducer compartment.

US Pat. No. 10,371,812

ULTRA-WIDEBAND RADAR ALTIMETER

Rosemount Aerospace Inc.,...

1. A system comprising:an unmanned aerial vehicle; and
an altimeter disposed on the unmanned aerial vehicle, the altimeter including an ultra-wideband radar antenna disposed orthogonally to a plane of straight and level flight of the unmanned aerial vehicle and having an omnidirectional azimuthal beam pattern orthogonal to the plane of straight and level flight of the unmanned aerial vehicle, the altimeter configured to determine an altitude of the unmanned aerial vehicle above a target surface based on time of flight of radar pulses between the ultra-wideband radar antenna and the target surface;
wherein the ultra-wideband radar antenna includes:
a first major face having a width extending along a first axis and a length extending along a second axis that is perpendicular to the first axis;
a second major face opposite the first major face, the second major face having the width extending along the first axis and the length extending along the second axis; and
a thickness extending between the first major face and the second major face along a third axis that is orthogonal to both the first axis and the second axis;
wherein the second axis is parallel to the plane of straight and level flight of the unmanned aerial vehicle; and
wherein the omnidirectional azimuthal beam pattern circumscribes the first major face and the second major face about the second axis.

US Pat. No. 9,494,687

SEEKER HAVING SCANNING-SNAPSHOT FPA

ROSEMOUNT AEROSPACE INC, ...

1. An imager comprising;
a focal plane array (FPA); and
an optical system communicatively coupled to the FPA, wherein said optical system is configured to perform a method comprising:
focusing laser energy comprising a first field-of-view to a first sub-window of said FPA;
focusing images comprising a second field-of-view identical to said first field-of-view to a second sub-window of said FPA;
pixel scanning said first sub-window of said FPA at an exposure rate that matches a predetermined pulse repetition frequency
(PRF) to thereby decode laser energy focused by said optical system to said first sub-window at said predetermined PRF;

snapshot exposing said second sub-window of said FPA, thereby capturing image energy focused by said optical system to said
second sub-window.

US Pat. No. 10,481,025

PIEZORESISTIVE SENSOR WITH SPRING FLEXURES FOR STRESS ISOLATION

Rosemount Aerospace Inc.,...

1. A sensor device comprising:a backing wafer comprising:
a backing support portion, and
a central backing plate connected to the backing support portion by one or more backing springs;
a diaphragm wafer connected to the backing wafer, the diaphragm wafer comprising:
a diaphragm support portion, and
a sensing portion connected to the diaphragm support portion by one or more diaphragm springs;
a passivation layer on the diaphragm wafer opposite the backing wafer; and
a topping wafer connected to the passivation layer opposite the backing wafer;
wherein the backing wafer and the diaphragm wafer are connected with frit, and wherein the diaphragm wafer and the topping wafer are connected with frit.

US Pat. No. 10,451,446

SYSTEM FOR INTERFACING WITH AN OPTICALLY-POWERED SENSOR

Rosemount Aerospace Inc.,...

1. A system for interfacing with an optically-powered sensor, the system comprising:an optical emitter configured to emit a beam of optical energy so as to provide operating power for the optically-powered sensor;
an optical detector configured to detect a time sequence of optical pulses generated by the optically-powered sensor, the time sequence of pulses modulated between first and second optical power levels;
a parameter extractor configured to determine a value of a sensed parameter based on the time sequence of optical pulses detected by the optical detector; and
a power controller configured to control power level of the emitted beam of optical energy based on the first and/or second optical power levels detected by the optical detector.

US Pat. No. 10,455,445

PERFORMANCE OPTIMIZATION FOR AVIONIC WIRELESS SENSOR NETWORKS

ROSEMOUNT AEROSPACE INC.,...

1. A data aggregator comprising:a traffic characterization module operable to generate a predicted quality of service for a plurality of sensors having one or more data rates and a plurality of priorities, wherein at least one of the priorities of at least one of the sensors changes based on a flight phase of an aircraft according to a predetermined mapping of sensor classes to a plurality of flight phases;
a rate estimator operable to generate a plurality of required data rates to maintain a target quality of service for one or more data consumers of an avionic communication network based on the predicted quality of service;
a data regulator operable to hold and release a plurality of sensor data from the sensors in one or more queues at the required data rates as a regulated data flow, wherein the predicted quality of service is determined based on an average waiting time of the sensor data in the one or more queues and an average network response time for a set of the one or more data rates and the priorities of the flight phase; and
a sensor data transmission interface operable transmit the regulated data flow to the one or more data consumers.

US Pat. No. 10,450,075

METHOD OF MAKING A MAGNETOSTRICTIVE OSCILLATOR ICE RATE SENSOR PROBE

Rosemount Aerospace Inc.,...

1. A method of improving the measurement accuracy of a digital ice rate sensor by providing an enhanced surface finish on a magnetostrictive oscillator detector probe, comprising the steps of:measuring external surface roughness on the magnetostrictive oscillator detector probe;
wherein the measuring is performed using equipment that is selected from the group consisting of an optical instrument and a surface profilometer;
comparing a value of the measured external surface roughness to a critical value;
taking at least one remedial action if the value of the measured external surface roughness is greater than the critical value;
wherein the at least one remedial action is selected from the group consisting of:
mechanically polishing the magnetostrictive oscillator detector probe; and
removing and reapplying a metallic coating on the magnetostrictive oscillator detector probe;
repeating the step of measuring the external surface roughness on the magnetostrictive oscillator detector probe at least one time after the at least one remedial action is taken; and
authorizing the magnetostrictive oscillator detector probe for use on the digital ice rate sensor if the value of the measure external surface roughness is not greater than the critical value.

US Pat. No. 10,389,195

ANNULAR MAGNETS FOR ROTOR POSITION ESTIMATION

Rosemount Aerospace Inc.,...

1. A magnetic position sensing system comprising:a first annular magnet mounted to a first surface of a rotating body;
a second annular magnet mounted to a second surface of the rotating body, the second surface being generally perpendicular to the first surface;
wherein each of the first and second annular magnets comprises:
a first end;
a second end;
an inner diameter surface; and
an outer diameter surface;
wherein the inner diameter surface and outer diameter surface define a radial thickness therebetween, the radial thickness varying from the first end to the second end.

US Pat. No. 10,468,180

ELECTROMAGNETIC ENERGY HARVESTER FOR AIRCRAFT APPLICATIONS

Rosemount Aerospace Inc.,...

1. An energy harvester system comprising:an aircraft power cable carrying an alternating current therethrough;
an energy harvester comprising:
a ferromagnetic ring encircling the aircraft power cable and configured so that the alternating current in the aircraft power cable generates magnetic flux in the ferromagnetic ring; and
an inductive coil wrapped around at least a portion of the ferromagnetic ring to generate a voltage from the magnetic flux in the ferromagnetic ring;
a step-up transformer electrically coupled to the energy harvester via the inductive coil to step up the voltage generated by the inductive coil; and
a tuning capacitor is electrically coupled to the step-up transformer.

US Pat. No. 10,466,157

SYSTEM AND METHOD FOR MEASURING CLOUD PARAMETERS

Rosemount Aerospace Inc.,...

1. A system for measuring cloud parameters, the system comprising:a pulsed light projector configured to simultaneously project both a collimated pulsed beam along a projection axis into a narrow-field projection volume of a cloud atmosphere and a divergent pulsed beam into a wide-field projection volume of the cloud atmosphere; and
an optical detector aligned so as to detect portions the projected collimated and divergent pulsed beams that are backscattered from within a detection volume of the cloud atmosphere, the detection volume aligned with a detection axis different from the projection axis,
wherein the detection volume intersects both the narrow-field and the wide-field projection volumes defining narrow-field/detection and wide-field/detection intersecting volumes, respectively,
wherein a distance between the narrow-field/detection intersecting volume and the optical detector is greater than a predetermined distance, and
wherein the optical detector is further configured to generate a signal indicative of the detected portions of the collimated and divergent pulsed beams backscattered from within both the narrow-field/detection and wide-field/detection intersecting volumes.

US Pat. No. 10,462,361

SEEKER WITH DYNAMIC RESOLUTION IMAGING

Rosemount Aerospace Inc.,...

1. A seeker imaging system comprising:at least one imager configured to output image frame data;
a plurality of optical elements configured to receive light and direct the light to the at least one imager; and
control electronics configured to receive the image frame data from the at least one imager, wherein the control electronics is configured to obtain a plurality of initial images from each frame of the image frame data, and wherein the control electronics is configured to generate a single output image based upon the plurality of initial images, wherein
if a target has not yet been acquired, an automatic target acquisition block of the control electronics receives the single output image at a desired resolution of the super resolution algorithm and processes the single output image to identify a location of a desired target in a field of view of the seeker and, if a target is recognized, the target acquisition block determines a target gate and passes the target gate to an automatic target tracker block as an initial target gate for subsequent images from the super resolution algorithm.

US Pat. No. 10,513,340

ROTOR ICE PROTECTION SYSTEMS AND METHODS

Rosemount Aerospace Inc.,...

7. A rotor ice protection system for a rotary aircraft, comprising:an icing rate sensor configured to detect an icing condition and generate an icing condition signal in response to the detected icing condition;
a first protection controller connected to the icing rate sensor and configured to generate a first de-icing signal in response to the icing condition signal;
a second protection controller connected to the icing rate sensor and configured to generate a second de-icing signal in response to the icing condition signal;
a first controller area network bus disposed in part in a slip ring assembly and connecting the first ice protection controller to a processor of an upper distributor;
a second controller area network bus disposed in part in the slip ring assembly and connecting the second ice protection controller to the processor of the upper distributor;
a first power line disposed in part in the slip ring assembly and connecting the upper distributor to a first power source; and
a second power line disposed in part in the slip ring assembly and connecting the upper distributor to a second power source,
wherein the processor of the upper distributor receives the first and second de-icing signals from the first and second ice protection controllers through the first and second controller area network buses, and in response thereto, transmits power from the first power line or the second power line to one or more heating elements for a respective rotor blade.

US Pat. No. 10,416,188

AIR DATA PROBE WITH TURBULENCE-PRODUCING GEOMETRY

Rosemount Aerospace Inc.,...

1. An air data probe comprising:a probe body comprising a barrel region, a tapered head region extending forward from the barrel region, and a tip at a forward-most end of the tapered head region; and
an air data sensing port disposed in the probe body at a port location aft of the tip,
wherein the probe body has a turbulence-producing geometry originating at the tip that produces a turbulent boundary layer of airflow that extends from the tip to the port location.

US Pat. No. 10,564,203

PROBE HEATER REMAINING USEFUL LIFE DETERMINATION

Rosemount Aerospace Inc.,...

1. A system for an aircraft, the system comprising:a probe that includes a heater comprising a resistive heating element routed through the probe, wherein an operational voltage is provided to the resistive heating element to provide heating for the probe;
a capacitive measurement circuit configured to determine a capacitance between a metallic sheath of the heater and the resistive heating element during each cycle of a plurality of cycles; and
a control circuit configured to provide the operational voltage and monitor the capacitance between the resistive heating element and the metallic sheath of the heater over time during each cycle;
wherein the control circuit is further configured to determine a remaining useful life of the probe based on the determined capacitance between the resistive heating element and the metallic sheath of the heater during each cycle, and an exponential function determined based on testing of a plurality of test probes during a plurality of test cycles to simulate the life of the probe, wherein a test capacitance of each of the test probes is determined at each test cycle.

US Pat. No. 10,457,412

ELECTRICAL ISOLATION OF ANGLE OF ATTACK VANE BEARINGS

Rosemount Aerospace Inc.,...

1. An angle of attack vane mounting system comprising:a mounting flange secured to an aircraft;
a shaft extending through the mounting flange;
a bearing disposed between the mounting flange and the shaft, wherein the bearing comprises:
an inner race attached to the shaft; and
an outer race attached to the mounting flange; and
an electric isolator disposed adjacent one of the inner race and the outer race and electrically isolating the bearing such that an electric current is prevented from passing between the inner race and the outer race;
wherein the electric isolator comprises at least one of a first sleeve disposed between the shaft and the inner race and a second sleeve disposed between the mounting flange and the outer race.

US Pat. No. 10,443,676

ISOLATED SEEKER OPTICS

Rosemount Aerospace Inc.,...

1. An optical lens stack comprising:an inner ring of a mounting structure including a plurality of axially-spaced circumferential lens mounting surfaces on an inside diameter of the inner ring, wherein an outside diameter of the inner ring is grooved over a fixed axial distance to form a circumferential channel in the outside diameter of the inner ring;
an outer ring formed to fit over the inner ring, wherein an inside diameter of the outer ring is grooved along the fixed axial distance as the inner ring thereby forming a circumferential cavity between the inside diameter of the outer ring and the outside diameter of the inner ring when the outer ring is mounted on the inner ring;
an energy absorbing conformal filler material that fills the cavity to form a mechanical vibration isolator in the mounting structure of the optical lens stack; and
a plurality of optical lenses formed to fit the lens mounting surfaces on the inside diameter of the inner ring of the mounting structure.

US Pat. No. 10,716,171

POWER EFFICIENT HEATER CONTROL OF AIR DATA SENSOR

ROSEMOUNT AEROSPACE INC.,...

1. A heater control system for an aircraft, the heater control system comprising:an air data sensor including a probe and transducer coupled to the probe;
a heating element disposed within the probe and configured to emit heat that heats the probe;
a thermal sensor system in operable communication with the air data sensor and configured to determine a temperature of the heating element based on a thermal radiation of heat released from a surface of the probe; and
a controller in operable communication with the thermal sensor system and the heating element, the controller configured to control power supplied to the heating element to vary the emitted heat based on the thermal radiation,
wherein the thermal sensor system comprises:
an optical unit configured to direct and focus infrared radiation flux of the heat released from the surface of the probe; and
a thermal detector configured to receive the infrared radiation flux from an optical unit, and to output a temperature signal indicative of the temperature of the heating element based on the infrared radiation flux.

US Pat. No. 10,656,369

MOUNTING OF OPTICAL ELEMENTS FOR IMAGING IN AIR VEHICLES

ROSEMOUNT AEROSPACE INC.,...

1. An optical assembly comprising:a mounting structure including a cylindrical body, a plurality of axially spaced circumferential recessed undercuts formed into an inner surface of the mounting structure, and a central bore defined by the inner surface, a width of the central bore increasing stepwise along an optical axis between an open end and a receiving end;
a plurality of optical elements axially spaced in the mounting structure, at least one of the plurality of optical elements including an undercut in a perimeter edge surface of the optical element, the undercut in the perimeter edge aligned with one of the plurality of undercuts in the mounting structure, the aligned circumferential undercuts defining a void; and
a conformal filler material cast in place in the void to create a mechanical lock between the optical element and mounting structure.

US Pat. No. 10,634,849

RUGGEDIZED TWO-AXIS OPTICAL BEAM STEERING DEVICE

Rosemount Aerospace Inc.,...

1. An optical beam steering device, comprising:an optical component for interacting with an optical beam;
a gimbal supporting the optical component and defining a pan axis;
a roll cage rotatably supporting the gimbal and defining a tilt axis, wherein the tilt axis is orthogonal to the pan axis;
a mount that houses and rotatably supports the roll cage;
a first spring and a first threaded ring configured to secure the gimbal within the roll cage; and
a second spring and a second threaded ring configured to secure the roll cage within the mount.

US Pat. No. 10,598,623

FOUR-WIRE CONDUCTIVITY CELL CIRCUIT

Rosemount Aerospace Inc.,...

14. A conductivity cell system comprising:a flow tube having a flow through hole extending from a first end of the flow tube to a second end of the flow tube;
a plurality of electrodes positioned in the flow tube, the plurality of electrodes forming a first pair of current electrodes axially spaced from a second pair of current electrodes and a first pair of voltage electrodes axially spaced from a second pair of voltage electrodes; and
circuitry connected to the plurality of electrodes, the circuitry including:
a Wheatstone bridge connected to the first pair of current electrodes and the second pair of current electrodes, the first pair of current electrodes being positioned at a first end of the flow through hole and the second pair of current electrodes being positioned at a second end of the flow through hole; and
an instrumentation amplifier connected to the first pair of voltage electrodes and the second pair of voltage electrodes, the first pair of voltage electrodes and the second pair of voltage electrodes being positioned adjacent each other along the flow through hole and between the first pair of current electrodes and the second pair of current electrodes.

US Pat. No. 10,578,637

INTEGRATION OF LOW ICE ADHESION SURFACE COATINGS WITH AIR DATA PROBES

Rosemount Aerospace Inc.,...

1. An air data probe comprising:a body;
a mount adjacent to the body;
a primary low ice adhesion surface coating on a primary impact region of the air data probe, the primary impact region being positioned for direct impact with water drops; and
a secondary low ice adhesion surface coating on a secondary impact region of the air data probe, the secondary impact region being positioned for indirect contact by water drops;
wherein the primary low ice adhesion surface coating has a different composition than the secondary low ice adhesion surface coating.

US Pat. No. 10,458,764

CANARD STOWAGE LOCK

Rosemount Aerospace Inc.,...

1. A canard mechanism comprising:a canard connected to a shaft that is hingedly attached to a rotatable hub, the canard being moveable between a stowed position and a deployed position; and
a locking feature on the canard for restraining the canard in the stowed position,
wherein the locking feature comprises a locking pocket on the canard, the locking pocket comprising:
first and second lateral sides extending towards a leading edge of the canard and at a location between a trailing edge of the canard and a widest portion of the canard; and
a bottom side extending from the first lateral side to the second lateral side, wherein the first and second lateral sides converge towards and terminate at the bottom side.

US Pat. No. 10,605,848

PROBE HEATER REMAINING USEFUL LIFE DETERMINATION

Rosemount Aerospace Inc.,...

1. A system for an aircraft, the system comprising:a probe that includes a heater comprising a resistive heating element routed through the probe, wherein an operational voltage is provided to the resistive heating element to provide heating for the probe;
an antenna, wherein the antenna is a radio-frequency (RF) antenna, the RF antenna is configured to provide a RF signal to the probe, and the RF signal comprises a plurality of signal frequencies; and
a control circuit configured to determine an antenna interaction between the resistive heating element and the antenna and determine a remaining useful life of the probe based on the antenna interaction over time, wherein the control circuit is configured to determine the response of the resistive heating element to the RF signal as the antenna interaction and the control circuit is configured to determine a resonant frequency from the resistive heating element in response to the plurality of signal frequencies over a plurality of flights of the aircraft, wherein the control circuit is configured to plot the resonant frequency over the plurality of flights and determine a half-life estimate of the resistive heating element based on the plot.

US Pat. No. 10,578,453

RENDER-BASED TRAJECTORY PLANNING

Rosemount Aerospace Inc.,...

1. A method comprising:collecting sensor data of an environment via one or more sensors disposed on a mobile platform, the sensor data including at least one of visual image data of the environment and range data to objects in the environment;
generating a three-dimensional computer model of the environment based on the collected sensor data;
generating a plurality of candidate trajectories within the environment based on the three-dimensional computer model;
forming rendered image data of the three-dimensional computer model and the plurality of candidate trajectories, wherein the rendered image data includes a two-dimensional image of the environment and the plurality of candidate trajectories within the environment;
selecting one of the candidate trajectories as a selected trajectory based on the rendered image data; and
controlling movement of the mobile platform based on the selected trajectory.

US Pat. No. 10,564,006

STATIC REFERENCE RESOLVER CIRCUIT

Rosemount Aerospace Inc.,...

1. A sensor comprising:a primary resolver circuit configured to provide first and second primary analog outputs, wherein the primary analog outputs are indicative of a sensed condition of the sensor;
a static reference circuit comprising a transformer, wherein the static reference circuit is configured to generate first and second reference analog outputs indicative of a static reference condition of the sensor, wherein the first and second reference analog outputs match the first and second primary analog outputs when the sensed condition is equivalent to the static reference condition, and wherein the transformer comprises:
a primary coil configured to receive a reference voltage;
a first secondary coil coupled to the primary coil and configured to output the first reference analog output; and
a second secondary coil coupled to the primary coil and configured to output the second reference analog output, wherein the primary coil, the first secondary coil, and the second secondary coil are not moveable relative to one another; and
a switch circuit configured to select between the first and second primary analog outputs during normal operations and the first and second reference analog outputs during a test condition for provision as first and second sensor analog outputs based upon a control input.

US Pat. No. 10,559,213

METHOD AND SYSTEM FOR AIRCRAFT TAXI STRIKE ALERTING

Rosemount Aerospace Inc.,...

1. A system for calculating trajectory and/or range data of object(s) external to an aircraft, the system comprising:a light projector configured to be mounted at a projector location on the aircraft and to project pulses of spatially-patterned light from the light projector onto a scene external to the aircraft, thereby providing rapidly-changing illumination of a spatially-patterned portion of the scene;
a camera configured to be mounted at a camera location on the aircraft and to receive a portion of the projected pulses of spatially-patterned light reflected by the scene, and further configured to focus the received portion onto a focal plane array comprising a plurality of light-sensitive pixels, the camera having a pulse-mode in which the camera forms a pulse image comprising pixel data generated by the plurality of light-sensitive pixels, the pixel data indicative of a rate of change of light intensity focused thereon exceeding a predetermined threshold; and
an image processor configured to identify pixel coordinates corresponding to a subset of the plurality of light-sensitive pixels indicative of the rate change of light intensity focused thereon exceeding the predetermined threshold, the identified pixel coordinates thereby corresponding to a subset of the plurality of light-sensitive pixels upon which the spatially-patterned light projected by the light projector and reflected from the spatially-patterned portion of the scene is focused, the image processor further configured to calculate, based on the projector location of the light projector, the camera location of the camera and the pixel coordinates so identified by the rate change of light intensity exceeding the predetermined threshold, trajectory and/or range data of object(s) in the scene from which the spatially-patterned light projected by the light projector is reflected.

US Pat. No. 10,489,971

SYSTEM AND METHOD FOR PROCESSING CAPTURED IMAGES FOR MOVING PLATFORM NAVIGATION

ROSEMOUNT AEROSPACE INC.,...

1. A system for processing images captured by a moving platform, the system comprising:a central processing unit (CPU), said CPU being interconnected functionally via a system bus to:
at least one sensor configured and disposed to capture a perceived environment including at least one of visual images of the environment and range data to objects in the environment;
a rendering unit (RU); and
at least one memory device thereupon stored a computer model of the environment and a set of instructions which, when executed by said CPU, causes the image processing system to:
capture a perceived environment through the at least one sensor, the perceived environment including visual images and range data;
render the computer model of the environment in the RU forming a rendered model of the environment;
compare the rendered model of the environment with the perceived environment;
selectively update the computer model of the environment based on the perceived environment; and
employ an iterative process to compute a position and orientation of the moving platform by performing a Z-buffer optimization of the perceived environment against the computer model of the environment.

US Pat. No. 10,634,692

INERTIALLY-AIDED AIR DATA COMPUTER ALTITUDE

Rosemount Aerospace Inc.,...

1. An air data computer configured to be installed on an aircraft, the air data computer comprising:an inertial sensor assembly comprising a plurality of accelerometers and a plurality of rate gyroscopes;
an air data parameter module configured to determine a pressure altitude of the aircraft based on measured pressure of airflow about an exterior of the aircraft;
an attitude determination module configured to determine an estimated attitude of the aircraft based on rotational rate sensed by the plurality of rate gyroscopes; and
an altitude rate blending module configured to:
determine a vertical acceleration of the aircraft based on the estimated attitude of the aircraft and acceleration sensed by the plurality of accelerometers;
perform a mathematical integration of the vertical acceleration to produce an accelerometer-based vertical velocity of the aircraft;
perform a mathematical differentiation of the pressure altitude to produce a pressure-based altitude rate of the aircraft;
filter, via a complementary filter, the accelerometer-based vertical velocity to remove low frequency signal and noise to produce a high-pass filtered accelerometer-based vertical velocity;
filter, via the complementary filter, the pressure-based altitude rate to remove high frequency signal and noise to produce a low-pass filtered pressure-based altitude rate; and
blend the high-pass filtered accelerometer-based vertical velocity and the low-pass filtered pressure-based altitude rate to produce the blended altitude rate of the aircraft; and
output the blended altitude rate.

US Pat. No. 10,589,870

MOISTURE RESISTANT AIR DATA PROBES

Rosemount Aerospace Inc.,...

1. An air data probe comprising:a probe head defining a longitudinal axis between a forward tip and aft base;
a port opening defined in the forward tip;
a first conduit in fluid communication with the port opening to guide fluid flow from the port opening to a first chamber, wherein the first chamber is downstream from the port opening; and
a second conduit, offset radially and circumferentially from the first conduit, in fluid communication with the first chamber to guide fluid flow from the first chamber to a second chamber, wherein the second chamber is downstream from the first chamber, wherein the offset between the first and second conduits is configured to prevent particle ingestion from the port opening from entering the second conduit.

US Pat. No. 10,571,419

CONTACTING TYPE FLOW THROUGH CONDUCTIVITY CELL

Rosemount Aerospace Inc.,...

14. A conductivity cell comprising:a cylindrical flaw tube holder having a closed first end and an open second end;
a first end fitting positioned on the first end of the flow tube holder;
a second end fitting positioned on the second end of the flow tube holder;
a flow tube positioned within the flow tube holder, the flow tube having a plurality of cavities;
an end cap positioned in the open second end of the flow tube holder and adjacent the flow tube and the second end fitting;
a plurality of electrodes positioned in the flow tube, each electrode including:
a main body;
a stem extending from an inner end of the main body;
a groove on the inner end of the main body of the electrode, the groove surrounding the stem;
a groove extending around a side of the main body, the side located between the inner end of the main body and an outer end of the main body;
an o-ring positioned in each of the grooves on the electrodes; and
a flow through hole extending from the first end fitting through the flow tube holder, the flow tube, and the end cap to the second end fitting;
wherein each of the plurality of electrodes is positioned in a corresponding one of the plurality of cavities such that a press-fit engagement is formed between each electrode in each corresponding cavity of the flow tube.

US Pat. No. 10,527,640

SYSTEM AND METHOD FOR PITOT TUBE BLOCKAGE DETECTION

ROSEMOUNT AEROSPACE INC.,...

1. A method of detecting blockage of a pitot tube, comprising:measuring a pitot tube temperature via one or more temperature sensors disposed inside a pitot tube;
measuring an outside ambient air temperature;
selecting a minimum measured pitot tube temperature threshold based on the measured outside ambient air temperature;
comparing the measured pitot tube temperature to the minimum measured pitot tube temperature threshold for the measured outside ambient air temperature; and
determining the pitot tube has a blockage condition when the measured pitot tube temperature is below the minimum measured pitot tube temperature threshold.

US Pat. No. 10,520,525

SYMMETRIC MEMS PIEZOELECTRIC ACCELEROMETER FOR LATERAL NOISE REDUCTION

Rosemount Aerospace Inc.,...

1. A method for sensing acceleration comprising:affixing, via a first axially-deformable member laterally extending from a first axial end of a first proofmass, the first proofmass to a device under test;
providing a first piezoelectric transducer on the first axially-deformable member,
affixing, via a second axially-deformable member laterally extending from a first axial end of a second proofmass, the second proofmass to the device under test;
providing a second piezoelectric transducer on the second axially-deformable member;
mechanically coupling second axial ends of the first and second proofmasses such that first and second axes of first and second proofmasses, respectively, are coincident with one another; and
generating, via the first and/or second piezoelectric transducers, a signal indicative of axial acceleration of the device under test.

US Pat. No. 10,666,498

ARCHITECTURE FOR WIRELESS AVIONICS COMMUNICATION NETWORKS

ROSEMOUNT AEROSPACE INC.,...

1. A method for architectures for wireless avionics communication networks, comprising:detecting a signal strength of wireless nodes;
assigning a primary data controller and standby data controller for each of the wireless nodes based at least in part on the signal strength;
connecting each of the wireless nodes to the primary data controller and the standby data controller;
generating a deployment matrix based on the assignment of the primary data controller and the standby data controller;
broadcasting the deployment matrix over a wired connection;
allocating a buffer size based on data rates of each of the wireless nodes connected to the primary data controller and the standby data controller; and
exchanging data based on the deployment matrix.

US Pat. No. 10,655,936

COORDINATING MULTIPLE MISSILE TARGETING VIA OPTICAL INTER-MISSILE COMMUNICATIONS

Rosemount Aerospace Inc.,...

1. A system configured to be mounted to a guided missile and to facilitate communications between the guided missile and other systems mounted to other guided missiles, the system comprising:an optical imaging system configured to generate an image of a scene aligned with a missile axis of the guided missile, the image comprising a two-dimensional array of pixel data;
a controller including:
a target identifier configured to identify a plurality of image portions within the image as corresponding to a plurality of potential targets in the aligned scene; a designation detector configured to determine a designated subset of the plurality of image portions within the image, the designated subset corresponding to potential targets in the aligned scene that have been designated via illumination by other optical emitters of the other systems mounted to the other guided missiles; and
a target selector configured to select, if at least one of the plurality of identified image portions is not a member of the designated subset, a target corresponding to one of the plurality of identified image portions that is not a member of the designated subset; and
an optical emitter configured to illuminate the selected target thereby communicating, to other missiles equipped to detect illumination of the target, that the selected target has been designated.

US Pat. No. 10,656,035

PIEZORESISTIVE SENSOR WITH SPRING FLEXURES FOR STRESS ISOLATION

Rosemount Aerospace Inc.,...

1. A method of making a sensor device comprises:processing a topping wafer;
making a backing wafer comprising:
a backing support portion, and
a central backing plate connected to the backing support portion by one or more backing springs;
creating a diaphragm wafer comprising:
a diaphragm support portion, and
a sensing portion connected to the diaphragm support portion by one or more diaphragm springs, wherein creating the diaphragm wafer comprises:
depositing a first passivation layer onto a silicon wafer,
adding a piezoresistive layer on the first passivation layer,
depositing a metal film on the first passivation layer,
depositing a top passivation layer on the metal film,
etching a diaphragm into the silicon wafer opposite the piezoresistive layer,
etching spring reliefs into the silicon wafer surrounding the diaphragm, and
etching fine features of the diaphragm springs;
processing a base wafer; and
assembling a wafer stack with the topping wafer, the backing wafer, the diaphragm wafer, and the base wafer, such that the backing wafer and the diaphragm wafer are connected with frit, and the diaphragm wafer and the topping wafer are connected with frit.

US Pat. No. 10,656,084

SYSTEM AND METHOD FOR MEASURING CLOUD PARAMETERS

Rosemount Aerospace Inc.,...

1. A system for measuring cloud parameters, the system comprising:a pulsed-beam projector configured to project a pulsed-beam of polarized light into a projection volume of a cloud atmosphere;
a receiver configured to receive a reflected portion of the projected pulsed beam backscattered from within the projection volume of the cloud atmosphere and to filter the received reflected portion into orthogonal polarized components;
a beam splitter aligned with the orthogonal polarized components so as split each of the orthogonal polarized components into first and second parts;
a first detector having a first gain, the first detector aligned with the first parts of the orthogonal polarized components and configured to generate first signals indicative of the first parts of the received reflected portion, respectively;
a second detector having a second gain, the second detector aligned with the second parts of the orthogonal polarized components and configured to generate second signals indicative of the second parts of the orthogonal polarized components, respectively; and
a processor configured to determine large water droplet size based on a magnitude of scintillation spikes of the first signals, and to determine water content based on the second signals,
wherein a ratio of the first and second gains of the first and second detectors, respectively, is greater than 3.

US Pat. No. 10,640,860

LASER METAL DEPOSITION METHODOLOGY ON GRAPHITE SUBSTRATES FOR AEROSPACE COMPONENTS

ROSEMOUNT AEROSPACE INC.,...

1. A laser direct metal deposition method for a graphite substrate, the laser direct metal deposition method comprising:creating an assembling by sliding an outer sheath over the graphite substrate;
performing a laser scanning of the outer sheath; and
performing a laser metal deposition over the graphite substrate with the outer sheath.

US Pat. No. 10,620,342

MICROSCOPIC IMAGER FOR AIRCRAFT CLOUD CONDITION DETECTION

Rosemount Aerospace Inc.,...

1. An imaging system for determining conditions of a cloud, the imaging system comprising:a laser emitter that generates a short pulse laser beam;
a fluorescent filter configured to convert the short pulse laser beam into a short pulse light beam, wherein a spectral content of the short pulse light beam is greater than a spectral content of the short pulse laser beam and the spectral content of the short pulse light beam is selected to result in reduced interference fringes around super cooled large water droplets in the cloud compared to use of a short pulse laser beam; and
optics configured to direct the short pulse light beam to the cloud, receive a reflected portion of the short pulse light beam from the cloud, and direct the reflected portion to an imager configured to detect super cooled large water droplets in the cloud.

US Pat. No. 10,591,363

ACCURATE AND FAST RESPONSE TEMPERATURE MEASUREMENT

Rosemount Aerospace Inc.,...

1. A temperature measurement arrangement having:a resistive temperature detector (RTD);
a single thermocouple; and
a processor,
wherein
the RTD is configured to generate a first sensing signal,
the single thermocouple is configured to generate a second sensing signal indicative of a temperature difference,
the processor is configured to select between a precision mode and a fast-response mode based on a magnitude of the second sensing signal, and wherein the temperature measurement arrangement is configured to determine temperature faster than the RTD alone and more accurately than the single thermocouple alone.

US Pat. No. 10,712,129

TERMINAL-IMAGING SEEKER WITH SOFTWARE DEFINED OPTICS

Rosemount Aerospace Inc.,...

1. A system for creating a corrected image of a scene for a terminal-imaging seeker, the system comprising:a focal plane array aligned with an optical axis and having an imaging region comprising a plurality of pixels;
a coded-aperture plate aligned along the optical axis and having opaque regions and a plurality of pinhole-like transparent regions separated from one another by the opaque regions, the coded-aperture plate configured to transmit light through the plurality of pinhole-like transparent regions onto the imaging region of the focal plane array thereby forming a raw shadow image of a corresponding plurality of overlapping images of the scene, the raw shadow image comprising pixel data generated by the plurality of pixels;
an optically-neutral lens aligned along the optical axis and having a front convex surface and a back planar surface, the front convex surface configured to provide low aerodynamic drag when engaging air at a leading edge of the terminal-imaging seeker, the optically-neutral lens configured to receive light from a scene aligned along the optical axis and configured to transmit light from the scene received at the front convex surface to the back planar surface in an optically-neutral fashion; and
an image processor configured to create, based on an algorithm corresponding to a configuration of the plurality of pinhole-like transparent regions and on the raw shadow image, the corrected image of the scene.

US Pat. No. 10,662,058

WET ETCH PATTERNING OF AN ALUMINUM NITRIDE FILM

Rosemount Aerospace Inc.,...

1. A method of manufacturing a patterned aluminum nitride layer, the method comprising:growing an amorphous patterned layer on a seed layer, wherein the amorphous patterned layer promotes growth of a first type aluminum nitride layer having a disordered crystallographic structure and wherein the seed layer promotes growth of a second type aluminum nitride layer with a vertically oriented columnar crystal structure;
depositing aluminum nitride over the amorphous patterned layer and the seed layer to form the first type aluminum nitride layer with the disordered crystallographic structure over the amorphous patterned layer and the second type aluminum nitride layer with the vertically oriented columnar crystal structure over the seed layer;
depositing a masking layer over the second type aluminum nitride layer; and
etching away the first type aluminum nitride layer.

US Pat. No. 10,613,112

AIR DATA PROBE ASSEMBLY METHOD

Rosemount Aerospace Inc.,...

1. An air data probe comprising:a strut including:
a socket defining an interior surface of the strut; and
an interior groove extending radially into the interior surface;
a probe head partially positioned within the socket, the probe head including:
an exterior surface; and
an exterior groove extending radially into the exterior surface, the exterior groove being axially alignable with the interior groove; and
a retaining ring being partially positioned within the exterior groove and partially positioned within the interior groove, when the exterior groove and the interior groove are axially aligned, to retain the probe head to the strut while allowing the probe head to rotate relative to the strut.

US Pat. No. 10,625,869

AUTOMATED SUPER-COOLED WATER-DROPLET SIZE DIFFERENTIATION USING AIRCRAFT ACCRETION PATTERNS

Rosemount Aerospace Inc.,...

1. A super-cooled water-droplet size measurement system comprising: a housing having a convex exterior surface, the housing configured to be mounted to an aircraft so as to expose the convex exterior surface to an airstream of the aircraft in flight; an ice detector configured to detect ice accretion at a plurality of test locations within a testing region of the convex exterior surface, wherein ice accretes, in conducive conditions, on at least an ice-accretion portion of the testing region; a boundary locator configured to prospectively calculate a specific one of the plurality of test locations within the testing region of the convex exterior surface, the determined specific one of the plurality of test locations corresponding to a boundary that separates the ice-accretion portion of the testing region and an ice-free portion of the testing region in conditions that include the atmosphere having super-cooled water droplets up to a predetermined maximum size, wherein the test location is calculated based on at least one of: airspeed; angle of attack; angle of sideslip; and total air temperature; and a gimballed mounting mechanism that facilitates orientation of a leading edge of the housing in response to changing flying conditions.

US Pat. No. 10,612,984

SENSOR ASPIRATION UTILIZING HOOP AIRFLOW INDUCTION

Rosemount Aerospace Inc.,...

1. A probe comprising:a housing defining a flow passage for a first fluid and having an entrance port and an exit port;
a sensor configured to sense a parameter of the first fluid and positioned within the flow passage; and
a hoop ejector connected to an exterior surface of the housing such that a channel of the hoop ejector surrounds the exit port, the hoop ejector having a plurality of holes configured to port a second fluid from the channel such that the first fluid is aspirated from the flow passage and out through the exit port.

US Pat. No. 10,611,488

ICE ACCRETION BOUNDARY LOCATOR

Rosemount Aerospace Inc.,...

1. A system for monitoring ice accretion on an aircraft, the system comprising:a boundary locator configured to determine a test location within a projection region of an aircraft window, the determined test location corresponding to a boundary that separates an ice-accretion portion of an exterior surface of the aircraft window and an ice-free portion of the exterior surface of the aircraft window in conditions that include the atmosphere having super-cooled water droplets up to a predetermined size; and
an optical projector configured to project a beam of light upon an interior surface of the aircraft window, and to direct the projected beam of light onto the determined test location within the projection region of the interior surface of the aircraft window.

US Pat. No. 10,611,499

TOTAL AIR TEMPERATURE SENSORS

Rosemount Aerospace Inc.,...

1. A total air temperature sensor comprising:a probe head having an airflow inlet and an airflow outlet;
a strut defining a leading edge and an opposed trailing edge extending along a longitudinal axis, the strut connecting between the probe head and an opposed probe mount; and
a turbulence inducing surface defined in the strut aft the leading edge configured to trip a fluid boundary layer passing over the strut to transition from laminar to turbulent to reduce acoustic noise emission from the total air temperature sensor wherein the turbulence inducing surface comprises a series of features spaced apart from one another
wherein the series of features is defined along an outer surface of the strut in an axial direction with respect to the longitudinal axis of the strut.

US Pat. No. 10,739,371

ACOUSTIC AIRSPEED SENSORS

Rosemount Aerospace Inc.,...

1. An acoustic airspeed sensor system, comprising:at least one acoustic transmitter configured to provide an acoustic pulse;
a plurality of acoustic receivers, including at least:
a first acoustic receiver positioned at a first radial distance from the at least one acoustic transmitter, the first acoustic receiver configured to:
receive the acoustic pulse at a first time; and
output a first receiver signal;
a second acoustic receiver positioned at a second radial distance from the at least one acoustic transmitter, the second acoustic receiver configured to:
receive the acoustic pulse at a second time; and
output a second receiver signal; and
an air data module operatively connected to the first acoustic receiver and the second acoustic receiver, the air data module configured to:
receive the first receiver signal and the second receiver signal;
determine a first signal delay between receiving the first receiver signal and transmission of the acoustic pulse by the acoustic transmitter;
determine a second signal delay between receiving the second receiver signal and transmission of the acoustic pulse by the acoustic transmitter;
receive or determine a wind angle;
determine true air speed (TAS) based upon the first signal delay, the second signal delay, and the wind angle; and
output a TAS signal indicative of the TAS.

US Pat. No. 10,739,372

DETACHABLE PROBE AND SEALING OF AN INTEGRATED AIR DATA SENSOR

Rosemount Aerospace Inc.,...

1. An integrated air data sensor comprising:a transducer;
a probe operably attachable to the transducer by a sealing feature such that a first gas path defined by the probe is fluidically coupled to a second gas path defined by the transducer via an inlet to the second gas path when the probe is attached to the transducer and the inlet is blocked from fluid flow therethrough when the probe is not attached to the transducer; and
the sealing feature comprises:
a plunger within the second gas path adjacent the inlet to the second gas path;
a first resilient member abutting the plunger, the first resilient member configured to bias the plunger to the closed position in which the plunger prevents contaminants from entering the second gas path; and
a protrusion adjacent to an outlet to the first gas path,
wherein when the probe is abutting the transducer the protrusion pushes the plunger into the open position such that air is able to flow by the plunger and into the second gas path.

US Pat. No. 10,730,637

INTEGRAL VANE BASE ANGLE OF ATTACK SENSOR

Rosemount Aerospace Inc.,...

1. An angle of attack sensor comprising:a housing;
a heated chassis positioned at least partially within the housing and defining a pocket;
a mounting plate positioned on the heated chassis and having a circular opening, an external surface facing away from the housing, and an internal surface facing toward the housing; and
a vane assembly extending through the circular opening of the mounting plate, the vane assembly including:
a vane extending from a root to a tip; and
a vane base having a body with a cylindrical portion, the body defining a face at an outer surface of the body, wherein the root of the vane is connected to the face of the vane base, and the vane base is positioned within the pocket of the heated chassis such that the face of the vane base is offset inwardly from the external surface of the mounting plate toward the housing.

US Pat. No. 10,723,465

ROUTABLE BACKUP POWER CONTROL UNITS

Rosemount Aerospace Inc.,...

1. A system comprising:a power source;
a plurality of primary control circuits connected to control load power from the power source to respective ones of a plurality of load power inputs;
a load configured to receive power from the plurality of load power inputs;
at least one secondary control circuit connected to the power source;
a switch circuit connected between the at least one secondary control circuit and the plurality of load power inputs; and
a control channel,
wherein the control channel is configured to control the switch circuit to connect the at least one secondary control circuit to a selected one of the plurality of load power inputs, and
wherein the control channel is further configured to detect a fault in one of the plurality of primary control circuits, and control the switch circuit to connect the at least one secondary control circuit to the selected one of the plurality of load power inputs upon detection of the fault.

US Pat. No. 10,723,479

SYNTHETIC AIR DATA OUTPUT GENERATION

Rosemount Aerospace Inc.,...

1. A method comprising:receiving, over an aircraft data communications bus, a plurality of non-pneumatic inputs;
processing the plurality of non-pneumatic inputs through an artificial intelligence network to generate a first air data output value without changing any one or more of first weights, biases, or transfer functions of the artificial intelligence network;
outputting the first air data output value to a consuming system;
processing the plurality of non-pneumatic inputs through the artificial intelligence network by applying second weights, biases, and transfer functions to generate a second air data output value; and
outputting the second air data output value to the consuming system.

US Pat. No. 10,701,558

SYSTEM AND METHOD FOR SECURING A WI-FI NETWORK

Rosemount Aerospace Inc.,...

1. A system for securing a Wi-Fi network, the system comprising:a power source that transmits an electric current along at least one power line;
a power line communication (PLC) module in electrical communication with the power source via the at least one power line, the PLC module configured to modulate the electric current to include a power line communication that contains a Wi-Fi network authentication key; and
a control module in electrical communication with and electrically downstream from the PLC module via the at least one power line, the control module configured to extract the power line communication from the electric current and utilize the Wi-Fi network authentication key to access the Wi-Fi network,
wherein extracting the power line communication from the electric current includes demodulating the electric current to separate the power line communication containing the Wi-Fi network authentication key from the electric current.

US Pat. No. 9,473,710

VIDEO SIGNAL TERMINATION DETECTION CIRCUIT

Rosemount Aerospace Inc.,...

1. A video signal termination detection system, comprising:
an input configured to connect to a video driver that produces a video signal having a driver video signal type;
an output configured to connect to a video receiver that operates with a receiver video signal type;
a detection circuit connected between the input and the output and configured to detect the receiver video signal type of
the video receiver and to output a detection signal;

a conversion circuit configured to receive the video signal from the video driver and to convert the driver video signal type
to the receiver video signal type of the video receiver if the driver video signal type is different from the receiver video
signal type of the video receiver;

a video interrupt switch configured to interrupt the video signal;
a test voltage supply for supplying a test voltage to the system when the video signal is interrupted by the video interrupt
switch, the supplying of the test voltage being controlled by at least one test voltage switch; and

a controller configured to control at least one of the video interrupt switch, the test voltage switch, and the conversion
circuit based on the detection signal received from the detection circuit;

wherein the controller is configured to shut off the input, switch on the test voltage, determine the receiver video signal
type, disconnect the test voltage, and reconnect the input to supply the receiver video signal type to the video receiver.