US Pat. No. 10,206,292

BACKSHELL GUARD FOR AN AVIONICS UNIT

Gulfstream Aerospace Corp...

1. A guard for a backshell, the backshell having a mating connector to a connector on a circuit card that is mounted in a chassis, the guard comprising:a guard body having:
a first feature formed therein to slidably receive a first portion of the backshell when the backshell is not connected to the circuit card that is mounted in the chassis;
a second feature formed therein to slidably receive a second portion of the backshell when the backshell is not connected to the circuit card that is mounted in the chassis; and
a third feature formed therein to protectively cover the mating connector when the backshell is not connected to the circuit card that is mounted in the chassis and has been slid into the guard body.

US Pat. No. 10,029,778

AIRCRAFT DOOR WITH COMPRESSIBLE HEADER

Gulfstream Aerospace Corp...

1. An interior door system for an aircraft comprising:a door having an opening across a top portion thereof;
a compressible header configured to reside in the opening across the door, the compressible header including a biasing mechanism configured to reside in the opening across the door and upwardly bias the compressible header which is configured to permit lateral movement of the compressible header within the opening across the door, the compressible header being compressed into the opening across the door as the compressible header contacts a headliner of the aircraft as the door moves from an open position to a closed position with the compressible header configured to move laterally and vertically relative to the door when the door is in the closed position.

US Pat. No. 9,221,554

RUNWAY OVERRUN MONITOR

Gulfstream Aerospace Corp...

1. In an aircraft performing a landing maneuver on a runway, a runway alerting method for the aircraft comprising: (a) receiving,
by a processor, information from sensors onboard the aircraft during the landing maneuver; (b) determining, in the processor,
a minimum stopping position and a maximum stopping position for the aircraft along the runway using aircraft energy, deceleration
and braking information, the minimum stopping position being determined based upon the aircraft performing a maximum flare
maneuver prior to touchdown on the runway and the maximum stopping position being determined based upon the aircraft performing
a minimum flare maneuver prior to touchdown on the runway, and wherein the minimum stopping position and the corporate maximum
stopping position are determined using the equation:

where: BrkonPt is the position on the runway (distance from runway start) where deceleration is predicted to begin begins as determined
by the second apparatus; V is the speed of the aircraft as determined by the first apparatus; and |A| is the absolute value
of the acceleration (deceleration being a negative value) using either the maximum deceleration or the corporate deceleration
depending on which predicted stopping point is being computed; (c) controlling, by the processor, a display unit onboard the
aircraft to display the minimum stopping position and the maximum stopping position of the aircraft to provide predicted indications
of the aircraft position relative to the runway at the conclusion of the landing maneuver; and (d) repeating steps (a) through
(c) until the aircraft has completed the landing maneuver.

US Pat. No. 9,290,263

NOSE LANDING GEAR ARRANGEMENTS AND METHODS FOR MAKING THE SAME

Gulfstream Aerospace Corp...

1. A nose landing gear arrangement for an aircraft that includes a fuselage, the nose landing gear arrangement comprising:
a wheel assembly;
a main strut operatively coupled to the wheel assembly and configured to extend outside of the fuselage substantially along
a generally vertical plane to position the wheel assembly for takeoff and/or landing of the aircraft;

a folding follow-up door pivotally coupled to the main strut and extending to the fuselage, wherein the folding follow-up
door comprises a first door section and a second door section that extend outwardly in directions away from each other to
define an unfolded position, and wherein the folding follow-up door is foldable to move the first and second door sections
towards each other about the generally vertical plane to define a folded position; and

an actuating arm pivotally coupled to the main strut and independently to the folding follow-up door and configured for moving
the folding follow-up door between the unfolded and folded positions.

US Pat. No. 9,246,425

APPARATUS AND SYSTEMS FOR ENGINE AND GENERATOR CONTROL WITHIN AN AIRCRAFT

Gulfstream Aerospace Corp...

1. A system, comprising:
a compound AC generator comprising: a permanent magnet generator (PMG) configured to be driven by a shaft to generate an AC
power signal;

an engine electronic controller (EEC) module that is configured to control an engine; and
a generator control unit (GCU) module that is configured to control the compound AC generator, wherein the PMG is coupled
to the GCU module and the EEC module such that the compound AC generator is configured to simultaneously supply the AC power
signal to the GCU module and to the EEC module.

US Pat. No. 9,233,756

SYSTEM AND METHOD FOR AIRCRAFT CABIN ATMOSPHERIC COMPOSITION CONTROL

Gulfstream Aerospace Corp...

1. A method for controlling a degree of oxygen/nitrogen shift of incoming air in response to a partial pressure of oxygen
in areas of an aircraft, said method comprising:
separating oxygen from ambient air onboard the aircraft to establish a high-concentration oxygen supply and separating nitrogen
from the ambient air onboard the aircraft to establish a high-concentration nitrogen supply;

determining that an increased oxygen concentration is desired in an occupant cabin, and dispensing an oxygen flow from the
high-concentration oxygen supply to the occupant cabin of the aircraft to increase a level of oxygen concentration within
the occupant cabin to a level greater than a naturally-occurring partial pressure of oxygen at an experienced internal cabin
pressure;

dispensing a nitrogen flow from the high-concentration nitrogen supply to a fire-susceptible, internal non-habitable region
of the aircraft to decrease a capability for an atmosphere therein to support combustion; and

determining that reduced oxygen concentration is desired in the occupant cabin; and
dispensing into the occupant cabin nitrogen from the high-concentration nitrogen supply, thereby diluting the oxygen concentration
in the occupant cabin.

US Pat. No. 9,121,369

NOZZLE ARRANGEMENT AND METHOD OF MAKING THE SAME

Gulfstream Aerospace Corp...

1. A nozzle arrangement for use with a supersonic jet engine configured to produce a plume of exhaust gases when the supersonic
jet engine is operating at a predetermined power setting and moving at a predetermined Mach speed, the nozzle arrangement
comprising:
a nozzle configured to exhaust the plume of exhaust gases, the nozzle having a trailing edge; and
a plug body partially positioned within the nozzle and coaxially aligned with the nozzle, the plug body having an expansion
surface and a compression surface downstream of the expansion surface, a protruding portion of the plug body extending downstream
of the trailing edge, the protruding portion of the plug body having a concave surface proximate a terminus of the plug body,
the plug body having contours and dimensions configured to shape the plume of exhaust gases such that the plume of exhaust
gases flows substantially parallel to a direction of a free stream of air flowing off of the trailing edge of the nozzle proximate
the trailing edge of the nozzle when the supersonic jet engine is operating at the predetermined power setting and moving
at the predetermined Mach speed and has further contours and dimensions that are configured to cause the plume of exhaust
gases to isentropically turn the free stream of air flowing off of the trailing edge of the nozzle at a location downstream
of the trailing edge of the nozzle such that the free stream of air flowing off of the trailing edge moves in a direction
parallel to a longitudinal axis of the plug body when the supersonic jet engine is operating at the predetermined power setting
and moving at the predetermined Mach speed.

US Pat. No. 9,376,096

APPARATUS AND METHOD FOR CONTROLLING A HYDRAULIC BRAKE OF AN AIRCRAFT

Gulfstream Aerospace Corp...

1. An apparatus for controlling a hydraulically-actuated brake of an aircraft, said apparatus comprising:
a brake control unit configured to receive a brake signal corresponding to actuation of a brake control input device from
an operator of the aircraft;

a reservoir for holding hydraulic fluid;
a pump in fluidic communication with said reservoir and the brake and configured to supply the hydraulic fluid from said reservoir
to the brake; and

an electric motor in communication with said brake control unit and coupled to said pump to control pressure of the hydraulic
fluid in accordance with the brake signal,

wherein the aircraft includes a hydraulic system providing hydraulic fluid, said apparatus further comprising a source selection
valve in fluidic communication with the hydraulic system, said pump, and the brake and configured to select hydraulic fluid
from one of the hydraulic system and said pump and supply the hydraulic fluid to the brake, and

wherein the apparatus further comprises a pressure sensing device configured to sense a pressure of the hydraulic system and
in communication with said source selection valve and wherein said source selection valve is configured to select hydraulic
fluid from said pump and deliver the hydraulic fluid to the brake in response to a pressure of the hydraulic system being
less than a predetermined value.

US Pat. No. 9,446,839

SYSTEMS AND METHODS FOR CONTROLLING A MAGNITUDE OF A SONIC BOOM

Gulfstream Aerospace Corp...

1. A method of controlling a magnitude of a sonic boom caused by operation of a supersonic aircraft at supersonic speeds,
the method comprising the steps of:
monitoring, with a processor, a weight of the supersonic aircraft and a distribution of fuel onboard the supersonic aircraft;
determining, with the processor, that there is a deviation of the weight of the supersonic aircraft from a design-condition
weight;

controlling, with the processor, a redistribution of the fuel onboard the supersonic aircraft to adjust an amount of fuel
stored within a wing to minimize a twist in the wing caused by the deviation, the fuel being redistributed to the wing when
the supersonic aircraft is above a design-condition weight and the fuel being redistributed from the wing when the supersonic
aircraft is below the design weight.

US Pat. No. 9,196,166

RUNWAY TAKEOFF MONITOR

Gulfstream Aerospace Corp...

1. A runway alerting method for an aircraft attempting a take-off maneuver, comprising:
determining, in a processor, stopping positions for the aircraft along the runway using aircraft energy, deceleration and
braking information, the stopping positions including at least a minimum stopping position and a corporate stopping position,
wherein the minimum stopping position and the corporate stopping position are determined using the equation:


 Where:
BrkonPt is the position on the runway (distance from runway start) where the brakes are predicted to be applied;

V is the predicted velocity of the aircraft at the brakes-on location as determined by aircraft speed sensors and assumed
speed loss that would occur before the brakes are applied; and

|A| is the absolute value of the acceleration (deceleration being a negative value) using the appropriate deceleration depending
on which predicted stopping point is being computed; and

displaying, by the processor, the stopping positions on a display.

US Pat. No. 9,233,763

METHODS AND SYSTEMS FOR AIRCRAFT SYSTEMS HEALTH TREND MONITORING

Gulfstream Aerospace Corp...

1. A method for health and trend monitoring for aircraft systems, comprising:
receiving, by a processor on the aircraft, a plurality of sensor signals from a respective plurality of sensors onboard the
aircraft;

determining a reference signal from a subset of the plurality of sensor signals;
individually comparing each of the plurality of sensor signals to the reference signal to provide a plurality of difference
signals, each of the plurality of differences signal associated with a respective sensor of the plurality of sensors;

comparing each of the plurality of difference signals to a threshold value; and
providing a maintenance message for any respective sensor associated with any of the plurality of difference signals exceeding
the threshold value.

US Pat. No. 9,353,704

AIR INLET ARRANGEMENT AND METHOD OF MAKING THE SAME

Gulfstream Aerospace Corp...

1. An air inlet arrangement for use with a supersonic jet engine configured to consume air at a predetermined mass flow rate
when the supersonic jet engine is operating at a predetermined power setting and moving at a predetermined Mach speed, the
air inlet arrangement comprising:
a cowl having a cowl lip; and a center body coaxially aligned with the cowl, the center body having an apex, a first compression
surface downstream of the apex, and a second compression surface downstream of the first compression surface, the second compression
surface being spaced apart from the cowl lip such that the second compression surface and the cowl lip define an inlet,

wherein a protruding portion of the center body extends upstream of the cowl lip and wherein the protruding portion of the
center body is configured to displace a portion of a column of air disposed upstream of the center body and longitudinally
aligned therewith, the column of air having a periphery defined by a leading edge of the cowl, the portion of the column of
air being displaced out of the path of the inlet by the protruding portion of the center body such that a remaining sub-portion
of the column of air at an upstream boundary of a terminal shock of the inlet is not greater than an amount of air that can
be consumed by the supersonic jet engine when the supersonic jet engine consumes air at the predetermined mass flow rate while
the supersonic jet engine is operating at the predetermined power setting and moving at the predetermined Mach speed.

US Pat. No. 9,302,767

NOSE LANDING GEAR ARRANGEMENT FOR AIRCRAFT AND METHOD OF ASSEMBLY

Gulfstream Aerospace Corp...

1. A nose landing gear arrangement for an aircraft, the nose landing gear arrangement comprising:
a wheel assembly configured for use with the nose landing gear arrangement;
a shock strut extending upwards from the wheel assembly towards a fuselage of the aircraft; and
a torque arm assembly coupled to the wheel assembly and to the shock strut, the torque arm assembly configured to transmit
torque to the wheel assembly, the torque arm assembly being disposed forward of the shock strut with respect to a direction
of travel of the aircraft, the torque arm assembly having a width that tapers along a substantial length of the torque arm
assembly, the torque arm assembly having a concave cross-section with respect to a direction opposite the direction of travel
of the aircraft, and the shock strut being disposed at least partially within a recess formed by the concave cross-section.

US Pat. No. 10,065,583

INTEGRATED POWER DISTRIBUTION, DATA NETWORK, AND CONTROL ARCHITECTURES FOR A VEHICLE

Gulfstream Aerospace Corp...

1. An integrated multi-function node, comprising:a housing; and
a plurality of components that are contained within and enclosed by the housing to form a single integrated unit, wherein the plurality of components are interconnected with connections that are internal to the housing, the plurality of components comprising:
power distribution (PD) components that are configured to receive electrical power from at least one source external to the integrated multi-function node and that are configured to distribute and control the electrical power to a plurality of active and passive electrical loads that are external to the integrated multi-function node, the PD components comprising:
an electrical power input interface configured to receive an electrical power input from the at least one source external to the integrated multi-function node; and
one or more power control modules, wherein each power control module is configured to control the electrical power supplied to one or more electrical power output interfaces, wherein the one or more electrical power output interfaces are configured to supply power to the plurality of active and passive electrical loads; and
data collection and distribution (DCD) components that are configured to receive data from data sources external to the integrated multi-function node and to transmit data to data consumers external to the integrated multi-function node.

US Pat. No. 9,482,155

ISENTROPIC COMPRESSION INLET FOR SUPERSONIC AIRCRAFT

Gulfstream Aerospace Corp...

5. A method of relaxing the geometry of an isentropic region of a compression surface to facilitate a reduced cowl lip angle
in an external compression inlet, comprising the steps of:
providing an initial, straight segment at one of a leading edge and an apex of said compression surface at a constant, initial
turn angle ? with respect to a free stream;

positioning a cowl lip at a predetermined distance aft of the one of said leading edge and said apex such that, at a specific
and predetermined design cruising speed, said initial, straight segment produces a bow shock which intersects a predetermined
intersection point proximate said cowl lip;

defining, for said specific and predetermined design cruising speed, a terminal shock which extends from said predetermined
intersection point to said compression surface;

providing a continuously curved concave segment aft of and structurally contiguous with said initial, straight segment;
configuring said continuously curved concave segment to produce, at said specific and predetermined design cruising speed,
a plurality of successive infinitesimally weak shocklets generally directed towards a portion of said terminal shock which
extends away from said cowl lip; and

relaxing, for a plurality of successive points in the aft direction along said continuously curved concave segment, the local
angle of inclination of said continuously curved concave segment relative to a traditional isentropic surface, such that at
said specific and predetermined design cruising speed a plurality of shocklets extend from said relaxed portion of said continuously
curved concave segment and intersect said terminal shock aft of and away from said predetermined intersection point, and said
plurality of successive infinitesimally weak shocklets do not focus at said predetermined intersection point at said specific
and predetermined design cruising speed.

US Pat. No. 9,878,772

MOUNTING ASSEMBLY AND METHOD FOR MOUNTING A SOUND-DEADENING BODY TO A FUSELAGE OF AN AIRCRAFT

Gulfstream Aerospace Corp...

1. A mounting assembly for mounting a sound-deadening blanket to a fuselage of an aircraft, the mounting assembly comprising:
a mounting bracket configured for attachment to the fuselage;
a retaining member configured to engage the sound-deadening blanket; and
an isolating member comprising an elastomeric material, the isolating member engaged with the mounting bracket and with the
retaining member in a manner such that the isolating member supports the retaining member on the mounting bracket and obstructs
direct contact between the retaining member and the mounting bracket, the isolating member being at least partially elastically
deformable, wherein the elastomeric material diminishes transmission of vibration from the fuselage to the retaining member
when the mounting bracket is attached to the fuselage of the aircraft,

wherein the retaining member includes a pair of spaced apart flanges configured to engage the isolating member, and
wherein the retaining member includes a detachable alignment portion that is configured to facilitate detection of the retaining
member through the sound deadening blanket.

US Pat. No. 9,878,778

SYSTEM AND METHOD FOR CONTROLLING A PRESSURE FIELD AROUND AN AIRCRAFT IN FLIGHT

Gulfstream Aerospace Corp...

1. A system for controlling a pressure field around an aircraft in flight, the system comprising:
a plurality of pressure sensors arranged at a plurality of locations extending along an external surface of the aircraft,
each pressure sensor configured to measure a respective local pressure;

a primary controller configured to control movement of a movable component onboard the aircraft; and
a controller communicatively coupled with the plurality of pressure sensors, the controller configured to receive information
indicative of the-respective local pressure from each pressure sensor and to compile each respective local pressure to determine
the pressure field along the external surface of the aircraft, to determine when the pressure field deviates from a desired
pressure field based on the information, and to transmit a request to the primary controller to move the movable component
in a manner that reduces the deviation, and wherein the primary controller is further configured to evaluate the request and
to comply with the request only when the request does not conflict with a control law governing the primary controller.

US Pat. No. 9,199,721

WING FLAPS FOR AIRCRAFT AND METHODS FOR MAKING THE SAME

Gulfstream Aerospace Corp...

1. A wing control body for an aircraft, the wing control body comprising:
an outer section adjacent to a flap-to-wing interface, the outer section comprising a side edge portion that at least partially
surrounds a side-edge cavity and is at least partially formed from an upper outer skin section and a lower outer skin section;
and

a close-out rib that extends between the upper and lower outer skin sections and that is disposed adjacent to the side-edge
cavity; and

a porous cavity-filler insert positioned in the side-edge cavity and having an upper surface, a lower surface, a covered inner
side surface, and an exposed outer side surface, and

wherein the outer section covers the covered upper and lower surfaces of the porous cavity-filler insert, the close-out rib
opposes the covered inner side surface, and the exposed outer side surface is exposed to an area outside of the side edge
portion of the wing control body.

US Pat. No. 9,834,320

AIRCRAFT AND EXTERIOR SPEAKER SYSTEMS FOR AIRCRAFT

Gulfstream Aerospace Corp...

1. An aircraft, comprising:
an outer skin membrane having an exterior surface that defines an exterior boundary of the aircraft;
a wing having a wingtip;
a vibration actuator coupled for common vibration with the outer skin membrane; and
a controller operatively coupled with the vibration actuator and configured to generate a command for the vibration actuator
based on audible content to be projected from the exterior surface and further configured to transmit the command to the vibration
actuator, the vibration actuator being configured to vibrate in response to receiving the command, wherein the controller
is further configured to generate the command based on proximity of the wingtip to an object for providing a tug driver with
towing warnings.

US Pat. No. 9,446,838

SYSTEMS FOR INCEPTOR CONTROL IN FLY-BY-WIRE AIRCRAFT SYSTEMS

Gulfstream Aerospace Corp...

1. An aircraft comprising:
a flight control surface; and
a control-by-wire system comprising:
an input device configured to control the flight control surface; and
a controller communicatively coupled with the input device and configured to automatically offset a neutral force position
of the input device based on a deviation of the aircraft from a reference condition while the aircraft is operated in a manual
flight mode.

US Pat. No. 9,114,887

METHODS AND SYSTEMS FOR DISPLAYING AIRCRAFT INFORMATION

Gulfstream Aerospace Corp...

1. A method of presenting aircraft information, the method comprising:
activating, with a controller, a master indicator in response to a trigger event associated with operation of the aircraft,
wherein activating the master indicator is activating a master warning or activating a master caution;

receiving, at the controller, a user input associated with the master indicator; and
displaying, on a display, information associated with the trigger event in response to receiving the user input associated
with the master indicator.

US Pat. No. 9,091,762

METHODS AND SYSTEMS FOR AVOIDING A COLLISION BETWEEN AN AIRCRAFT ON A GROUND SURFACE AND AN OBSTACLE

Gulfstream Aerospace Corp...

1. A method for avoiding a collision between an aircraft on a ground surface and an obstacle, the aircraft comprising a fuselage,
wings, a vertical stabilizer and a horizontal stabilizer, the method comprising:
receiving, at a processor onboard an aircraft, a detection signal from one of a plurality of proximity sensors comprising
first proximity sensors disposed on the wings of the aircraft and a second proximity sensor disposed on at least one of the
vertical stabilizer or the horizontal stabilizer, wherein the detection signal indicates that the obstacle has been detected
by a particular proximity sensor that transmitted the detection signal;

receiving, at the processor onboard the aircraft, a plurality of video image signals each being generated by a particular
one of a plurality of video imagers each being disposed at various different locations on the aircraft and each being associated
with at least one of the proximity sensors, wherein the video imagers comprise first video imagers disposed on the wings of
the aircraft and a second video imager disposed on at least one of the vertical stabilizer or the horizontal stabilizer;

transmitting only one particular video image signal of the plurality of video image signals from the processor to a display
in the cockpit of the aircraft in response to receiving the detection signal, wherein the one particular video image signal
corresponds to a particular one of the video imagers that is associated with the particular proximity sensor that detected
the obstacle;

displaying a video image on the display corresponding to the one particular video image signal, wherein the video image is
of a particular region around the aircraft that includes the obstacle; and

transmitting, from the processor in response to receiving the detection signal, an alert signal to an element in a cockpit
of the aircraft, and a brake activation signal to automatically activate a braking system to prevent the aircraft from colliding
with the obstacle.

US Pat. No. 9,919,791

STIFFENING STRUCTURES, WING STRUCTURES, AND METHODS FOR MANUFACTURING STIFFENING STRUCTURES

Gulfstream Aerospace Corp...

1. An aircraft stiffening structure of composite material comprising: a first longitudinal member and a second longitudinal
member; a first rib that extends from the first longitudinal member to the second longitudinal member and is directly integral
with the first longitudinal member and the second longitudinal member; wherein the first longitudinal member has a first wall,
a second wall and a joining wall that joins the first wall and the second wall, and wherein the first wall, the second wall
and the joining wall form a space having a trapezoidal shapes wherein the first rib has a first wall, a second wall and a
joining wall that joins the first wall and the second wall of the first rib, and wherein the first wall, the second wall and
the joining wall of the first rib form a space having a trapezoidal shape; wherein the joining wall of the first rib shares
a first plie of the composite material with the joining wall of the first longitudinal member.

US Pat. No. 9,625,716

OMNIDIRECTIONAL HUD

Gulfstream Aerospace Corp...

1. A head-up display (HUD) system, the HUD system comprising:
a 3-D projector configured to project a first 3-D HUD layout;
a projection surface configured to display the projected first 3-D HUD layout;
a controller operatively coupled with the 3-D projector, the controller configured to control the projector to project the
first 3-D HUD layout onto the projection surface; and

a first pair of active shutter 3-D glasses configured to synchronize with the 3-D projector to present the first 3-D HUD layout
to a first user.

US Pat. No. 9,561,847

SYSTEMS AND METHODS FOR CONTROLLING A MAGNITUDE OF A SONIC BOOM

Gulfstream Aerospace Corp...

1. A system for controlling a magnitude of a sonic boom of a supersonic aircraft at supersonic speeds, the system comprising:
a first sensor configured to detect a first condition of the supersonic aircraft;
a pair of wings configured to move; and
a processor communicatively coupled with the sensor and operatively coupled with the pair of wings, the processor configured
to:

receive a first information from the first sensor, the first information indicative of the first condition of the supersonic
aircraft,

calculate a lift distribution of the supersonic aircraft based, at least in part, on the first information,
determine an existence of a deviation of the lift distribution from a desired lift distribution based on the flight condition,
calculate an amount and a direction of movement for the pair of wings that will reduce the deviation in response to determining
the existence of the deviation, and

control the pair of wings to move the amount and the direction of movement.

US Pat. No. 9,845,144

AIRCRAFT AND AIR EXCHANGE SYSTEMS FOR VENTILATED CAVITIES OF AIRCRAFT

Gulfstream Aerospace Corp...

1. An aircraft, comprising:
a fuselage;
a wing secured to the fuselage;
an outer skin panel secured to at least one of the wing and the fuselage, wherein the outer skin panel at least partially
defines a cavity; and

an air exchange system configured to exchange air between the cavity and an external environment outside of the aircraft,
the air exchange system comprising:

an air inlet disposed in the outer skin panel and configured to permit an air flow between the cavity and the external environment,
and

a silencer in fluid communication with the air inlet and configured to direct the air flow between the air inlet and the cavity
and reduce noise.

US Pat. No. 9,334,801

SUPERSONIC AIRCRAFT JET ENGINE INSTALLATION

Gulfstream Aerospace Corp...

1. An inlet for an engine of a supersonic aircraft comprising:
an inlet ramp;
a cowl lip spaced outwardly of said inlet ramp and configured to receive an air flow between said inlet ramp and said cowl
lip;

a forward portion of said inlet ramp from which an oblique shock extends outwardly to pass proximate said cowl lip when the
supersonic aircraft is operating at a predetermined supersonic Mach speed;

a rearward portion of said inlet ramp from which a terminal shock extends outwardly to a point proximate said cowl lip when
the supersonic aircraft is operating at the predetermined supersonic Mach speed;

wherein said inlet ramp comprises:
a first section configured to produce said oblique shock;
a second section located rearwardly of said first section and configured to produce substantially constant Mach number flow;
a third section comprising a relaxed isentropic compression surface configured to produce a plurality of shocklets extending
from said third section and intercepting said terminal shock between said inlet ramp and said cowl lip at a plurality of locations
spaced apart from the cowl lip when the supersonic aircraft is operating at the predetermined supersonic Mach speed;

a fourth section configured to produce a substantially constant Mach number; and
a fifth section turning of the air flow towards the engine proximate the terminal shock.

US Pat. No. 9,132,910

METHOD FOR ATTACHING A COMPONENT TO AN INTERNAL PORTION OF AN AIRCRAFT FUSELAGE

Gulfstream Aerospace Corp...

1. A method for attaching a component to an internal portion of an aircraft fuselage, the method comprising:
mounting a vibration isolator assembly to the internal portion of the aircraft fuselage, the vibration isolator assembly having
a protruding engagement portion having a flange;

attaching an alignment spike to the protruding engagement portion;
pressing a vibration-deadening body against the alignment spike;
detecting a location on a nearside of the vibration-deadening body that corresponds with a position of the alignment spike;
marking the location with a visible mark;
defining an opening in the vibration-deadening body by beginning to define the opening with a cutting implement on the nearside
of the vibration-deadening body proximate the visible mark and continuing to define the opening until the opening extends
through a far side of the vibration-deadening body and until the cutting implement contacts a rear flange of the alignment
spike;

aligning the opening with an end of the protruding engagement portion;
positioning the vibration-deadening body over the vibration isolator assembly after the opening has been defined and aligned
with the end of the protruding engagement portion such that the protruding engagement portion is received within the opening;

removing the alignment spike;
pressing a retaining member onto the protruding engagement portion such that the retaining member engages the flange, wherein
the retaining member is configured to retain a portion of the vibration-deadening body below an end of the protruding engagement
portion; and

attaching the component to the protruding engagement portion.

US Pat. No. 9,650,154

AIRCRAFT LANDING GEAR ASSEMBLIES WITH NON-ROTATING LIGHT ELEMENT CLUSTERS

Gulfstream Aerospace Corp...

1. A landing gear assembly for an aircraft, the landing gear assembly comprising:
a main post having a non-rotating portion and a rotatable steering portion;
a lamp fairing rotationally fixed to the non-rotating portion;
a tiller rotationally coupled with the rotatable steering portion of the main post; and
a light element cluster associated with the non-rotating portion, attached to the lamp fairing and including at least two
independently illuminating sections, wherein the at least two independently illuminating sections include a first starboard
section configured to face a starboard side of the aircraft and a first port section configured to face a port side of the
aircraft, and

wherein the first starboard section is configured to illuminate in response to the tiller rotating to point the rotatable
steering portion to the starboard side, and wherein the first port section is configured to illuminate in response to the
tiller rotating to point the rotatable steering portion to the port side.

US Pat. No. 9,840,334

AUXILIARY POWER UNIT INLET DUCT ASSEMBLY FOR MITIGATING NOISE

Gulfstream Aerospace Corp...

1. An auxiliary power unit inlet assembly for use with an auxiliary power unit on an aircraft, the auxiliary power unit inlet
assembly comprising:
an inlet duct having a first end and a second end, the first end configured for coupling to the auxiliary power unit;
a door associated with the second end of the inlet duct, the door configured to move between a first position and a second
position, the door closing the second end of the inlet duct when the door is in the first position and the door permitting
air to enter the second end of the inlet duct when the door is in the second position; and

a sound absorbing component mounted to the door and disposed proximate the inlet duct, the sound absorbing component positioned
at a location on the door such that a noise generated by the auxiliary power unit will impinge on the sound absorbing component.

US Pat. No. 9,838,436

AIRCRAFT DATA NETWORKS

Gulfstream Aerospace Corp...

1. An aircraft data network, comprising:
a first communication path between a first transmitting system and a first receiving system, comprising:
a first Remote Data Concentrator (RDC) configured to: receive one or more input signals comprising data from the first transmitting
system; and translate the data to generate translated data;

a network switch, communicatively coupled to the first RDC via a bus, the network switch being configured to: receive the
translated data from the first RDC; determine a destination for at least some of the translated data from the first RDC; and
route the at least some of the translated data from the network switch toward the first receiving system;

a second RDC configured to: receive the at least some of the translated data from the network switch; convert the at least
some of the translated data from the network switch to generate converted data having a format designed for use by the first
receiving system; and communicate the converted data from the second RDC to the first receiving system;

wherein the first RDC, the network switch, and the second RDC collectively define a first hardware and software of the first
communication path; and

a second communication path between the first transmitting system and the first receiving system, comprising:
a first remote interface unit (RIU) configured to: receive the one or more input signals comprising the data from the first
transmitting system; and translate the data to generate translated data;

a processing unit, communicatively coupled to the first RIU, the processing unit being configured to: receive the translated
data from the first RIU; determine a destination for at least some of the translated data from the first RIU; and route the
at least some of the translated data from the processing unit toward the first receiving system; and

a second RIU configured to: receive the at least some of the translated data from the processing unit; convert the at least
some of the translated data from the processing unit to generate converted data for use by the first receiving system; and
communicate the converted data from the second RIU to the first receiving system,

wherein the first RIU, the processing unit, and the second RIU collectively define a second hardware and software of the second
communication path, and

wherein the first hardware and software of the first communication path is different from the second hardware and software
of the second communication path.

US Pat. No. 9,459,120

METHODS AND SYSTEMS FOR DISPLAYING FLIGHT INFORMATION

Gulfstream Aerospace Corp...

1. An avionics system, comprising:
a display; and
a controller communicatively coupled with the display to present an image, the controller configured to:
generate a flight clearance portion of the image including flight clearance information,
generate a flight progress portion of the image including flight progress information,
generate an adjustment input portion of the image, wherein the controller is further configured to generate a second portion
of an airspeed column, a second portion of a vertical speed column, a second portion of an altitude column, a third portion
of a heading column, or combinations thereof to generate the adjustment input portion of the image, and

adjust the flight clearance portion in response to an input at the adjustment input portion of the image.

US Pat. No. 9,341,207

WEB COMPONENT AND METHOD OF MAKING A WEB COMPONENT

Gulfstream Aerospace Corp...

1. A web component in an aircraft suitable for use with a snap-fit assembly, the web component comprising:
a generally flat unitary sheet metal member having a periphery, a first side and a second side, the sheet metal member including
a plurality of protrusions integral with the sheet metal member, the plurality of protrusions extending from a first surface
of the first side and from a second surface of the second side, the plurality of protrusions disposed proximate a portion
of the periphery and inset from the portion of the periphery, the sheet metal member further including a plurality of depressions
extending into the first surface and into the second surface, the plurality of depressions disposed proximate the portion
of the periphery and disposed inset from the portion of the periphery, the plurality of depressions being aligned with the
plurality of protrusions.

US Pat. No. 9,146,250

METHODS AND SYSTEMS FOR DISPLAYING BACKUP AIRSPEED OF AN AIRCRAFT

Gulfstream Aerospace Corp...

1. A system for selecting an airspeed reference that is displayed within a cockpit of an aircraft, the system comprising:
a Global Position System (GPS) receiver-processor module located on-board the aircraft, the GPS receiver-processor module
configured to:

receive GPS signals transmitted from each of a plurality of GPS satellites over radio frequency links, wherein each GPS signal
includes GPS information, wherein the GPS information comprises: GPS positional data and corresponding time stamps that indicate
when that GPS positional data was measured; and

process the GPS information to generate the backup airspeed based on the GPS positional data and corresponding time stamps;
a processor configured to determine whether primary airspeed is valid or invalid, and, to select a backup airspeed as the
airspeed reference that is output to the display when the processor determines that the primary airspeed is invalid; and

a display that is configured to display the backup airspeed as the airspeed reference.

US Pat. No. 9,889,926

AIR VEHICLES AND SYSTEMS FOR PREEMPTIVE TURBULENCE MITIGATION

Gulfstream Aerospace Corp...

1. An air vehicle comprising:
a flight control surface;
a sensor configured to determine a velocity of an air mass that is separated from the air vehicle by a predetermined distance;
and

a controller communicatively coupled with the sensor and configured to:
determine whether the air mass will disturb smooth flight of the air vehicle; and
manipulate the flight control surface in response to determining that the air mass will disturb smooth flight of the air vehicle
based on the velocity of the air mass,

wherein the controller is further configured to manipulate the flight control surface using a control algorithm.

US Pat. No. 9,448,186

SYSTEM AND METHOD FOR DETERMINING A CONCENTRATION OF GAS IN A CONFINED SPACE

Gulfstream Aerospace Corp...

1. A system for determining a concentration of gas in a confined space, said system comprising:
a first frequency generator for generating a first radio frequency (RF) signal;
a first antenna electrically connected to said first frequency generator for transmitting the first RF signal across the confined
space;

a second antenna for receiving the first RF signal;
a first RF signal power detector for detecting the power of the first RF signal prior to transmission through the confined
space and generating a first power signal corresponding to the first RF signal prior to transmission;

a second RF signal power detector for detecting the power of the first RF signal received at said second antenna and generating
a second power signal corresponding to the first RF signal received at said second antenna;

a first comparator circuit in communication with said first and second RF signal power detectors for determining a concentration
of oxygen in the confined space based on at least the first power signal and the second power signal;

at least one thermal reference device for sensing a temperature;
a temperature compensation comparator circuit in communication with said at least one thermal reference device, said first
RF signal power detector for adjusting the first power signal to compensate for the temperature, and said second RF signal
power detector for adjusting the second power signal to compensate for the temperature;

a second frequency generator for generating a second RF signal;
a third antenna electrically connected to said second frequency generator for transmitting the second RF signal across the
confined space;

a fourth antenna for receiving the RF signal; and
a sixth comparator circuit in communication with said second frequency generator and said fourth antenna for determining a
concentration of water vapor in the confined space based on at least the second RF signal prior to transmission through the
confined space and the second RF signal received by said fourth antenna,

wherein said first comparator circuit is in communication with said sixth comparator circuit for determining a concentration
of water vapor in the confined space and determining a concentration of oxygen in the confined space based on at least the
power signals corresponding to the first RF signal and the concentration of water vapor in the confined space.

US Pat. No. 9,884,684

IN-FLIGHT LEVELING SYSTEM

Gulfstream Aerospace Corp...

1. An in-flight leveling system for a seat onboard an aircraft, the seat having a seat cushion and a seat back and the aircraft
traveling at an angle of inclination during flight, comprising:
a swivel mechanism having a front pivot point and providing selective arcuate movement of an aft portion of the seat to compensate
for the angle of inclination of the aircraft during the flight, the swivel mechanism comprising:

a front pivot rod extending between a pair of spaced apart support base risers;
a rear slide rod extending between the pair of spaced apart support base risers and guided by arcuate slots formed in the
pair of spaced apart support base risers; and

a sector pivotally coupled to one of the pair of spaced apart support base risers, the sector having an arcuate toothed rack
and an opening for receiving the rear slide rod;

a locking mechanism coupled to the swivel mechanism to retain the seat in a first position and a second position the locking
mechanism comprising a pawl having teeth to selectively engage the arcuate toothed rack of the sector; and

an actuator for moving the locking mechanism between a locked condition and an unlocked condition permitting the aft portion
of the seat to move between the first position to the second position the actuator comprising a lever causing a cam to move
the pawl toward or away from the arcuate toothed rack of the sector;

whereby, the actuator moves the locking mechanism from the locked condition to the unlocked condition permitting the aft portion
of the seat to move from the first position to the second position to remain substantially level during the flight due to
the swivel mechanism compensating for the angle of inclination of the aircraft during the flight.

US Pat. No. 9,694,898

METHODS FOR MANUFACTURING AN I-STRINGER OF AN AIRCRAFT AND DEVICES FOR USE IN SUCH METHODS

Gulfstream Aerospace Corp...

1. A device for forming a cap section of an I-stringer of an aircraft, the device comprising:
a base;
a first support member fixedly attached to the base;
a second support member fixedly attached to the base and aligned parallel to the first support member, wherein the first support
member and the second support member are spaced a first distance apart; and

two pinching wheels spaced a second distance apart, wherein the two pinching wheels are positioned proximate to ends of the
first support member and the second support member, wherein the second distance is less than the first distance, and wherein
the two pinching wheels are configured to receive a composite material layout between them and to cause two opposing lengths
of the composite material layout to contact each other.

US Pat. No. 9,205,934

ADAPTIVE OSCILLATORY FAULT MONITORING

Gulfstream Aerospace Corp...

1. An aircraft system comprising:
a third oscillation monitoring module configured to:
select third oscillating portions of an input signal;
generate a frequency signal that indicates a frequency of the third oscillating portions; and
generate a third failure signal in response to the frequency of the third oscillating portions exceeding third oscillatory
fault detection requirements for the input signal; and

a second oscillation monitoring module configured to:
select second oscillating portions of the input signal based on the frequency signal generated by the third oscillation monitoring
module; and

generate a second failure signal in response to a frequency of the second oscillating portions exceeding second oscillatory
fault detection requirements for the input signal.

US Pat. No. 9,550,574

VENTILATION SYSTEM AND METHOD OF ASSEMBLY

Gulfstream Aerospace Corp...

1. A ventilation system for ventilating a passenger compartment of an aircraft, the ventilation system comprising:
a nozzle adapted to be mounted proximate an interior of the aircraft and configured to direct a stream of air into the passenger
compartment;

a valve spaced apart from the nozzle and positioned upstream of the nozzle, the valve configured to control a flow of air
to the nozzle; and

a conduit fluidly coupling the valve to the nozzle, the conduit configured to convey the flow of air from the valve to the
nozzle,

wherein the nozzle includes a transitional section having a first cross-sectional area at an upstream portion of the transitional
section and a second cross-sectional area at a downstream portion of the transitional section and wherein the first cross-sectional
area is greater than the second cross-sectional area, wherein the nozzle includes a pintle disposed in the transitional section,
and wherein the transitional section comprises a pathway surface and the pintle comprises a pintle surface, and wherein a
segment of the pathway surface is substantially equidistant from a corresponding segment of the pintle surface,

wherein the pintle is attached to the nozzle via a plurality of tabs and wherein each tab of the plurality of tabs extends
through a pathway formed by the pathway surface of the transitional section and the pintle surface of the pintle and wherein
each tab is at least partially configured as an airfoil.

US Pat. No. 9,883,302

SYSTEM FOR IDENTIFYING A SOURCE OF AN AUDIBLE NUISANCE IN A VEHICLE

Gulfstream Aerospace Corp...

1. A system for identifying a source of an audible nuisance in a vehicle, the system comprising:
a device comprising a camera configured to receive a visual dataset, and to generate a camera signal in response to the visual
dataset;

a dock configured to removably couple to the device, the dock comprising a microphone array configured to receive the audible
nuisance, and to generate a microphone signal in response to the audible nuisance; and

a processor module configured to be communicatively coupled with the device and the dock, to generate a raw soundmap signal
in response to the microphone signal, to combine the camera signal and the raw soundmap signal, and to generate a camera/soundmap
overlay signal in response to combining the camera signal and the raw soundmap signal.

US Pat. No. 9,580,169

SYSTEMS AND METHODS FOR CONTROLLING A MAGNITUDE OF A SONIC BOOM

Gulfstream Aerospace Corp...

1. A system for controlling a magnitude of a sonic boom caused by operation of a supersonic aircraft at supersonic speeds,
the system comprising:
a sensor configured to detect a condition of the supersonic aircraft;
a control surface mounted to a wing of the supersonic aircraft; and
a processor communicatively coupled to the sensor and operatively coupled with the control surface, the processor configured
to:

receive information from the sensor indicative of the condition of the supersonic aircraft,
determine that there is a deviation between a lift distribution and a design-condition lift distribution based, at least in
part on the information, and

control the control surface to move in a manner that reduces the deviation,
wherein the processor is configured to control the control surface in a manner that applies a torsion force to the wing, the
torsion force causing the wing to twist in a nose-up direction when the processor determines that the condition of the supersonic
aircraft will cause the wing to twist in a nose-down direction, and the torsion force causing the wing to twist in a nose-down
direction when the processor determines that the condition of the supersonic aircraft will cause the wing to twist in a nose-up
direction and

wherein the condition comprises one of an off-design condition weight of the supersonic aircraft and an off-design condition
velocity of the supersonic aircraft.

US Pat. No. 9,501,869

SYSTEMS AND METHODS FOR PRESENTING VEHICLE COMPONENT INFORMATION

Gulfstream Aerospace Corp...

1. A method for presenting vehicle component information, said method comprising:
storing voxel data in a database wherein the voxel data represents a plurality of small voxels and a plurality of large voxels
spatially arranged to encompass a shape representing a vehicle, and wherein each of the large voxels represent a first volume
larger than a second volume represented by each of the small voxels;

storing a plurality of component records in the database each with a spatial orientation, wherein each component record corresponds
to a component of the vehicle, and wherein the spatial orientation indicates how the component is situated in the vehicle,
wherein one component record corresponds to one version of a component of the vehicle and another component record corresponds
to another version of the component;

associating each component record with voxel data representing at least one small voxel and at least one large voxel;
displaying a graphical representation of at least part of the vehicle including at least one of the components on a display
based on the spatial orientation of each of the at least one of the components with respect to the vehicle in response to
a user input including a bounding box indicating the at least part of the vehicle; and

displaying the plurality of component records based on the at least one of the components of the displayed graphical representation
and based on the user input.

US Pat. No. 9,260,188

APPARATUS AND METHOD FOR ALLOWING MULTI-MODE USE OF AN AIRCRAFT COCKPIT

Gulfstream Aerospace Corp...

1. A method for operating an aircraft, comprising:
determining, by a processor in the aircraft, whether the aircraft is operating in a flight mode or a non-flight mode;
deactivating aircraft engines and permitting wireless device access to one or more aircraft systems when the aircraft is operating
in the non-flight mode; and

enabling the aircraft engines and preventing wireless device access to the one or more aircraft systems when the aircraft
is operating in the flight mode.

US Pat. No. 9,989,377

METHOD AND SYSTEM FOR DISPLAYING INFORMATION

Gulfstream Aerospace Corp...

1. A method for presenting aircraft flight information, said method comprising:receiving a category at a controller, wherein the category is a phase of flight of an aircraft;
determining a selector to be displayed based on relevance to operation of the aircraft at the phase of flight;
displaying the selector configured to be selected by a user on a first portion of a display in response to receiving the category, wherein the selector is configured to control an aspect of the aircraft and is associated with the received phase of flight; and
displaying other information related to operation of the aircraft on a second portion of the display regardless of the phase of flight category.

US Pat. No. 9,972,142

METHODS, SYSTEMS AND APPARATUS FOR AUTOMATED GENERATION OF A FLIGHT LOG AND A SQUAWK LIST FILE

Gulfstream Aerospace Corp...

1. A method for automatic generation of a final flight log and a final squawk list, the method comprising:recording flight log data for a flight in a preliminary flight log data file;
recording squawk events that occur while the aircraft is in flight;
automatically generating, at an on-board computer upon occurrence of a trigger event, a preliminary squawk list file comprising: a plurality of squawk events; and
executing, at a portable wireless communication device that is configured to communicate with the on-board computer over a communication link, a software application that is designed to generate a final flight log and a final squawk list file, wherein executing comprises:
presenting, at a graphical user interface of the portable wireless communication device, each squawk event from the preliminary squawk list file for review;
receiving inputs from an input system of the portable wireless communication device, wherein the inputs comprise: an input for each particular squawk event in the preliminary squawk list file comprising at least one of: an edit input to change content of that particular squawk event, an approval input that indicates that the particular squawk event has been approved for inclusion in the final squawk list file, or a removal input that indicates that the particular squawk event has not been approved for inclusion in the final squawk list file and is to be deleted from the preliminary squawk list file; and
when all squawk events in the preliminary squawk list file have been reviewed, generating a final flight log and the final squawk list file, wherein the final squawk list file comprises: each of the squawk events from the preliminary squawk list file that have been reviewed and approved for inclusion in the final squawk list file as squawk events to be investigated for corrective action after the flight.

US Pat. No. 10,059,427

OVER-FRAME BLANKET ASSEMBLIES AND METHODS OF INSTALLATION IN FUSELAGE ASSEMBLIES

GULFSTREAM AEROSPACE CORP...

1. A fuselage assembly for an aircraft, the fuselage assembly comprising:a fuselage skin;
a cabin liner having an outer side facing the fuselage skin; and
an over-frame blanket assembly disposed between the fuselage skin and the cabin liner and separated from the cabin liner, the over-frame blanket assembly comprising a first blanket piece, the first blanket piece comprising:
a first sound barrier layer that defines a first outer surface of the over-frame blanket assembly that is exposed radially inward of the over-frame blanket assembly and faces the cabin liner;
a first sound absorbing layer that defines a second outer surface of the over-frame blanket assembly facing the fuselage skin;
a second blanket piece comprising a second sound barrier layer that further defines the first outer surface of the over-frame blanket assembly; and
an acoustic barrier patch that includes a sound barrier material adhered directly to the first sound barrier layer and directly to the second sound barrier layer.

US Pat. No. 9,944,062

COMPOSITE AIRCRAFT MANUFACTURING TOOLING AND METHODS USING ARTICULATING MANDRELS

Gulfstream Aerospace Corp...

1. A method of manufacturing a composite stringer of an aircraft, the method comprising:laying skin plies on a layup tool that includes a contoured surface having a first portion with a first surface complexity and a second portion with a second surface complexity;
placing an articulating stringer mandrel on the skin plies, wherein placing the articulating stringer mandrel further includes:
positioning a first rigid mandrel element on the skin plies so that a first bottom surface of the first rigid mandrel element opposes the first portion, wherein the first rigid mandrel element defines a first aperture and a first stringer surface to which the composite stringer conforms, the first rigid mandrel element having a first length along a longitudinal direction of the composite stringer; and
positioning a second rigid mandrel element on the skin plies adjacent to the first rigid mandrel element so that a second bottom surface of the second rigid mandrel element opposes the second portion, the second rigid mandrel element defining a second aperture and a second stringer surface to which the composite stringer conforms, the second rigid mandrel element having a second length along the longitudinal direction,
wherein the positioning the first rigid mandrel element is based at least in part on the first length and the first surface complexity and positioning the second rigid mandrel element is based at least in part on the second length and the second surface complexity so that a gap between the first rigid mandrel element and the second rigid mandrel element does not exceed a predetermined gap threshold; and
tightening a cable that extends through the first aperture and the second aperture;
laying stringer plies overtop the articulating stringer mandrel; and
curing the skin plies and the stringer plies.

US Pat. No. 9,944,407

METHODS AND SYSTEMS FOR AVOIDING A COLLISION BETWEEN AN AIRCRAFT AND AN OBSTACLE USING A THREE DIMENSIONAL VISUAL INDICATION OF AN AIRCRAFT WINGTIP PATH

Gulfstream Aerospace Corp...

1. A method for avoiding a collision between an aircraft on a ground surface and an obstacle, the aircraft having winglets positioned at the wingtips, the method comprising:receiving, at the processor onboard an aircraft, a video image from a camera positioned in one of the winglets, the video image representing a field of view through which the wingtip of the aircraft will pass along a present heading of the aircraft;
determining, by the processor, a predicted three-dimensional area representing the height of the winglet and the angle of the winglet from the wingtip within the field of view through which the winglet of the aircraft will pass along the present heading of the aircraft; and
displaying the video image on a display together with an overlay representing the predicted three-dimensional area in the field of view;
wherein the overlay provides information to assist in preventing the winglet of the aircraft from colliding with obstacles in the field of view.

US Pat. No. 9,987,768

COMPOSITE TOOLS AND METHODS FOR FABRICATING COMPOSITE TOOLS

Gulfstream Aerospace Corp...

1. A method for fabricating a composite tool, the method comprising the steps of:providing a master mold having a surface;
forming a substructure such that a topographical surface of the substructure is formed to the same surface topography as the surface of the master mold;
forming a low temperature cured resin laminate overlying the master mold, wherein the low temperature cured resin laminate has a master mold surface that is formed in contact with the master mold;
heating and compressing the low temperature cured resin laminate to form a cured low temperature cured resin laminate, the low temperature cured resin laminate heated to a first temperature;
removing the cured low temperature cured resin laminate from the master mold;
affixing the master mold surface of the cured low temperature cured resin laminate and the topographical surface of the substructure;
forming a high temperature cured resin laminate overlying the cured low temperature cured resin laminate; and
heating and compressing the high temperature cured resin laminate to form a cured high temperature cured resin laminate, the high temperature cured resin laminate heated to a second temperature, wherein the second temperature is higher than the first temperature.

US Pat. No. 9,701,424

DETACHABLE DETECTION AND WARNING SYSTEM FOR AN AIRCRAFT

Gulfstream Aerospace Corp...

1. A system, comprising:
a detachable mounting apparatus that is configured to be secured on an aircraft, comprising:
a belt that is configured to wrap around a portion of the aircraft, wherein the belt comprises: protection material to prevent
damage to the portion of the aircraft that the belt is wrapped around, and a locking mechanism that locks the belt on the
aircraft to prevent the belt from being removed from the aircraft until the locking mechanism is unlocked;

a battery that is configured to supply electrical power for the system;
solar cells integrated within the belt and configured to generate electrical energy to supply at least part of the electrical
power;

a detection system configured to detect objects in proximity to the aircraft and to generate a detection signal when an object
is detected in proximity to the aircraft;

an imaging device configured to capture and record at least one image of the object that is in proximity to the aircraft;
and

a warning system configured to generate at least one alarm signal that is perceptible outside the aircraft.

US Pat. No. 9,475,569

METHODS FOR MANUFACTURING AN I-STRINGER OF AN AIRCRAFT AND DEVICES FOR USE IN SUCH METHODS

Gulfstream Aerospace Corp...

1. A method for manufacturing a reinforced composite structure for an aircraft, the method comprising the steps of:
forming a composite material layout by arranging a first composite material ply overlying a second composite material ply
and positioning a pre-cured cap insert on the first composite material ply;

advancing the composite material layout through a cap-forming device, wherein the advancing results in a preformed cap section,
a first length of the composite material layout and a second length of the composite material layout;

removing the composite material layout from the cap-forming device;
arranging the preformed cap section of the composite material layout within a cavity of a flexible mandrel with a foot portion
of the first length and a foot portion of the second length remaining outside the cavity of the flexible mandrel;

contacting the foot portion of the first length and the foot portion of the second length with a skin structure: and
heating and pressurizing the composite material layout using the flexible mandrel to cure the composite material layout and
form the reinforced composite structure affixed to the skin structure.

US Pat. No. 9,884,688

PROPULSION SYSTEM USING LARGE SCALE VORTEX GENERATORS FOR FLOW REDISTRIBUTION AND SUPERSONIC AIRCRAFT EQUIPPED WITH THE PROPULSION SYSTEM

Gulfstream Aerospace Corp...

1. A propulsion system for a supersonic aircraft, the propulsion system comprising:
an engine including an engine core and an engine bypass, the engine core having a higher sensitivity than the engine bypass
to a change in stagnation pressure;

a compression surface disposed upstream of the engine;
a shroud partially surrounding the engine and configured to direct an airflow passing over the compression surface towards
the engine; and

a plurality of vortex generators positioned upstream of the engine, each vortex generator of the plurality of vortex generators
having a height such that when the supersonic aircraft is flown at a predetermined altitude and at a predetermined cruise
speed, the predetermined cruise speed being greater than Mach 1, the plurality of vortex generators create a plurality of
vortices that propagate at least partially outside of a boundary layer formed proximate a surface of a supersonic inlet, the
plurality of vortices causing a high-velocity portion of the airflow to move towards the engine core and a low-velocity portion
of the airflow to move towards the engine bypass prior to the airflow reaching a face of the engine, the plurality of vortex
generators being disposed aft of a terminal shock formed when the supersonic aircraft is flown at the predetermined cruise
speed, and each vortex generator of the plurality of vortex generators having a height greater than a thickness of the boundary
layer at the location of each vortex generator of the plurality of vortex generators.

US Pat. No. 9,569,848

ADVANCED AIRCRAFT VISION SYSTEM UTILIZING MULTI-SENSOR GAIN SCHEDULING

Gulfstream Aerospace Corp...

1. In an aircraft performing a landing maneuver, a method for enhancing pilot vision, comprising:
receiving, by a processor onboard the aircraft, data from sensors or systems onboard the aircraft at least one of the sensors
or systems providing an aircraft altitude;

(a) determining, by the processor, a position of the aircraft relative to a runway using the data;
(b) adjusting the gain of a first vision system according to a gain control curve based upon the aircraft altitude to provide
an adjusted first image;

(c) adjusting the gain of a second vision system according to a corresponding opposite gain control curve based upon the aircraft
altitude to provide an adjusted second image;

(d) merging the adjusted first image and the adjusted second image to provide a merged image;
(e) displaying the merged image; and
(f) repeating steps (a)-(e) until the aircraft has completed the landing maneuver.

US Pat. No. 9,902,484

FLIGHT DECK ARRANGEMENT

Gulfstream Aerospace Corp...

1. A flight deck arrangement comprising:
a window;
a surface disposed proximate the window and positioned below the window;
a rail mounted to the surface, the rail disposed proximate the window and positioned below the window, the rail extending
along the surface in a direction generally aligned with a lower portion of the window;

a visor mounted to the rail and selectively positionable along the rail; and
an upright pillar bordering the window, the upright pillar including a recess,
wherein an end of the visor is configured to reside within the recess and wherein the recess is configured to support the
end of the visor when the visor is positioned at a longitudinal end of the rail.

US Pat. No. 10,071,415

ERGONOMIC BUCKING BAR

Gulfstream Aerospace Corp...

1. A bucking bar, comprising:a bar body comprised of a first material having a first density and having a proximal end and a distal end, the proximal end having a plurality of apertures formed therein;
a compliant hand grip positioned over the proximal end of the bar body the compliant hand grip having a compliant density different from the first density;
wherein the plurality of apertures reduces weight of the bar body at the proximal end and the compliant hand grip reduces vibrations transmitted from the distal end through the bar body during a riveting operation using the bucking bar.

US Pat. No. 10,059,430

AIRCRAFT AIR SCOOP SYSTEMS WITH PASSIVE PNEUMATIC ACTUATORS

Gulfstream Aerospace Corp...

1. An aircraft, comprising:an interior compartment configured to enclose a substantially constant interior air mass at a cabin pressure during flight of the aircraft;
an outer skin that at least partially defines a ventilated cavity;
an air scoop disposed on the outer skin and configured to communicate air between the ventilated cavity and an external environment in which the aircraft is located;
a movable element movable between an open position and a closed position over the air scoop to define an air flow area through the air scoop;
a passive pneumatic actuator comprising a first side in pneumatic communication with the interior compartment and a second side in pneumatic communication with the external environment, wherein the passive pneumatic actuator is operatively coupled with the movable element and is configured to move the movable element towards the closed position in response to an increasing altitude of the aircraft based on a differential pressure between the interior air mass and the external environment; and
a pressure actuated valve coupled between the interior air mass and the passive pneumatic actuator, wherein the pressure actuated valve is configured to restrict air flow from the interior compartment to the passive pneumatic actuator when the differential pressure is below a threshold value.

US Pat. No. 9,714,084

SUPERSONIC AIRCRAFT WITH SPIKE FOR CONTROLLING AND REDUCING SONIC BOOM

Gulfstream Aerospace Corp...

1. An aerospace vehicle configured to reduce the effects of a sonic boom created by the aerospace vehicle when flown at supersonic
speed, the aerospace vehicle comprising:
a fuselage;
an empennage coupled to a rear end of the fuselage; and
a spike operably associated with the empennage and configured to extend in a rearward direction from a rear portion of the
empennage, the spike extending from a location on the empennage spaced apart from a longitudinal axis of the fuselage,

wherein the spike comprises a first section telescopically coupled with a second section and wherein the second section is
configured to collapse into the first section, and

wherein each section of the spike is narrower than each forward section of the spike and wider than each aft section of the
spike.

US Pat. No. 9,725,186

METHODS AND SYSTEMS FOR REQUESTING AND RETRIEVING AIRCRAFT DATA DURING FLIGHT OF AN AIRCRAFT

Gulfstream Aerospace Corp...

1. A system for health and trend monitoring of an aircraft, the system comprising:
a gateway configured to communicate with the aircraft via satellite communication links and to receive a crew alerting system
(CAS) message file comprising unprocessed data from the aircraft, wherein the CAS message file automatically indicates that
measured parametric data from a sub-system of the aircraft is outside one or more threshold limits;

a ground-based computer configured to:
process the unprocessed data in the CAS message file to generate processed data;
generate a parameter request message for transmission to the aircraft using the gateway, wherein the parameter request message
includes a parameter file that specifies a duration value and additional parametric data to be collected by the aircraft to
identify one or more sources that are causing the measured parametric data to be outside the one or more threshold limits,
wherein the duration value specifies how long the additional parametric data is to be recorded; and

process the additional parametric data recorded by the aircraft in response to receiving the additional parametric data at
the gateway.

US Pat. No. 10,143,302

METHOD FOR MACHINING DRAWERS OF AN ARTICLE OF FURNITURE

Gulfstream Aerospace Corp...

1. A method for machining a plurality of surfaces of a respective plurality of drawers of an article of furniture, the method comprising the steps of:mounting a side of the article of furniture to a support structure to form a work piece;
positioning the work piece on a base of a vertical gantry router in an orientation such that the plurality of surfaces are generally perpendicular to a cutting head of the vertical gantry router;
moving each drawer of the respective plurality of drawers relative to the side of the article of furniture to an extended position such that the plurality of surfaces are generally aligned with one another in a single plane;
fixing each of the drawers in the extended position to define the drawers in fixed, extended positions relative to the side of the article of furniture; and
machining the plurality of surfaces of the drawers in the fixed, extended positions with the vertical gantry router until the plurality of surfaces are substantially flat and substantially coplanar with one another.

US Pat. No. 9,669,519

WORK PIECE HOLDER AND METHOD OF USING A WORK PIECE HOLDER TO SUPPORT A WORK PIECE

Gulfstream Aerospace Corp...

1. A work piece holder comprising:
a bracket having a first arm and a second arm, there being a gap between the first arm and the second arm, a first portion
of the second arm being non-parallel to a first portion of the first arm such that a lower portion of the gap is narrower
than an upper portion of the gap; and

a wedge configured to at least partially fit in the gap, the wedge having a first side and a second side, the second side
configured to engage the first portion of the second arm, the wedge configured to move along the first portion of the second
arm, and the first side and the first portion of the first arm configured to cooperate to support the work piece when the
work piece is positioned in the gap while the second side is engaged with the first portion of the second arm and when the
wedge has moved along the first portion of the second arm to a position where the first side engages the work piece, and

wherein the second side of the wedge is configured to engage the first portion of the second arm in a tongue-in-groove manner.

US Pat. No. 9,828,086

NOSE LANDING GEAR ARRANGEMENTS INCLUDING A FLEXIBLE SHEET AND METHODS FOR MAKING THE SAME

Gulfstream Aerospace Corp...

1. A nose landing gear arrangement for an aircraft that includes a fuselage, the nose landing gear arrangement comprising:
a wheel assembly;
a main strut operatively coupled to the wheel assembly and configured to move between an extended position and a retracted
position, wherein the main strut in the extended position extends outside of the fuselage substantially along a generally
vertical plane to position the wheel assembly for takeoff and/or landing of the aircraft, and wherein the main strut in the
retracted position is disposed inside the fuselage; and

a flexible continuous sheet with a continuous surface disposed adjacent to the main strut and configured such that when the
main strut is in the extended position the continuous surface is positioned substantially around the main strut.

US Pat. No. 10,148,021

BACKSHELL INSTALLATION GUIDE

Gulfstream Aerospace Corp...

1. An installation guide for a backshell, the backshell having a mating connector to a connector on a circuit card installed in an equipment rack, the installation guide comprising:an installation guide body having:
a first feature formed therein to receive at least a portion of the backshell to retain the backshell in the installation guide; and
a second feature formed therein to align the installation guide with a portion of the equipment rack prior to the mating connector of the backshell contacting the connector of the circuit card;
wherein, the installation guide having the backshell retained within the first feature is configured to position the mating connector of the backshell in alignment with the connector of the circuit card facilitating interconnection of the mating connector with the connector as the installation guide is moved toward the circuit card with the second feature aligned with the portion of the equipment rack.

US Pat. No. 10,093,410

SYSTEMS AND METHODS FOR CONTROLLING A MAGNITUDE OF A SONIC BOOM

Gulfstream Aerospace Corp...

1. A method of controlling a magnitude of a sonic boom caused by off-design condition operation of a supersonic aircraft at supersonic speeds, the method comprising the steps of:operating the supersonic aircraft at supersonic speeds and at an off-design condition, the supersonic aircraft having a pair of swept wings and a center box joining each wing of the pair of swept wings, the pair of swept wings having a plurality of composite plies, all composite plies of the plurality of composite plies being oriented at an angle such that an axis of greatest stiffness is oriented at an angle of ten to thirty degrees with respect to a rear spar of each wing of the pair of swept wings, and each wing being free of any composite ply having an axis of greatest stiffness oriented in a manner that is parallel to the rear spar of each wing;
reducing wing twist caused by operation of the supersonic aircraft at supersonic speeds at the off-design condition with the composite plies; and
minimizing the magnitude of the sonic boom through reduction of wing twist.

US Pat. No. 10,093,431

AIRCRAFT INSTRUMENTATION SYSTEMS FOR DISPLAYING ELECTRONIC CIRCUIT BREAKER INFORMATION

Gulfstream Aerospace Corp...

1. An aircraft instrumentation system for an aircraft, the aircraft instrumentation system comprising:a display; and
a controller communicatively coupled with the display, the controller configured to:
monitor a current phase of flight in which the aircraft is currently operating;
generate a checklist associated with a next consecutive phase of flight that follows the current phase of flight; and
generate a signal that causes the display to present the checklist associated with the next consecutive phase of flight in response to one of transitioning to, reaching a predetermined time until, and reaching a predetermined distance from the next consecutive phase of flight.

US Pat. No. 9,878,801

CONSOLE ASSEMBLY INCLUDING STOWABLE SUPPORT SURFACE

GULFSTREAM AEROSPACE CORP...

1. A console assembly for use on a flight deck of an aircraft, the console assembly comprising:
a console configured to be mounted in the flight deck of the aircraft, the console having a recess defined therein, the recess
having an opening, the opening facing towards the flight deck when the console is mounted in the flight deck;

a mounting assembly mounted within the recess;
a support surface mounted to the mounting assembly; and a closeout panel mounted to the support surface,
wherein the support surface is configured to fit within the recess, wherein the mounting assembly is configured to facilitate
movement of the support surface between a retracted position and a deployed position, wherein the support surface is disposed
within the recess when in the retracted position and disposed outside of the recess when in the deployed position, wherein
the closeout panel is disposed at a location on the support surface that causes the closeout panel to close the opening of
the recess when the support surface is in the retracted position, wherein the support surface includes a first body and a
second body, wherein the second body is pivotally attached to the first body, wherein the second body is pivotable from a
first position to a second position where the first body and second body form the support surface, wherein when the second
body is pivoted to the second position the closeout panel moves with respect to the support surface to a position below the
support surface.

US Pat. No. 9,771,142

SYSTEMS AND METHODS FOR PROVIDING VISUAL FEEDBACK IN AIRCRAFT

GULFSTREAM AEROSPACE CORP...

1. A system for providing visual feedback for an aircraft having an actuatable component, said system comprising:
a controller providing automatic control of the actuatable component in an automatic mode and permitting manual control of
the actuatable component in a manual mode;

a handle assembly in communication with the actuatable component to provide manual control of the actuatable component in
the manual mode; and

a light panel integrated with said handle assembly, in communication with said controller, and configured to selectively illuminate
to inform a user of the mode of the actuatable component.

US Pat. No. 9,637,244

AIRCRAFT INSTRUMENTATION SYSTEMS FOR DISPLAYING ELECTRONIC CIRCUIT BREAKER INFORMATION

Gulfstream Aerospace Corp...

1. A controller for an aircraft, the controller comprising:
a processor; and
an electronic memory unit communicatively coupled with the processor, the electronic memory unit storing instructions that
when executed by the processor enable the controller to:

monitor an operational status of each of a plurality of aircraft systems;
generate, for each of the plurality of aircraft systems, an Electronic Circuit Breaker (ECB) status selector and an operational
status visual indicator that indicates the operational status;

generate an image arrangement that includes the operational status visual indicator for each of the plurality of aircraft
systems;

replace the operational status visual indicator with the ECB status selector for each of the plurality of aircraft systems
in response to selection of a set ECB mode selector; and

generate a signal that causes a display to present the image arrangement.

US Pat. No. 10,160,532

AIRCRAFT DOOR WITH RETRACTABLE HEADER

Gulfstream Aerospace Corp...

1. An interior cabin door for an aircraft, comprising:a door panel having an opening in a top portion thereof;
a retractable header configured to retract into the opening in the door panel as the door panel moves toward an open position; and
a lifting system configured to raise the retractable header when the door panel moves toward a closed position, the lifting system comprising:
a first bar and a second bar coupled to the door panel and the retractable header;
a cable and pulley system having one or more pulleys coupled to the door panel and the cable being configured to be coupled at a first end to a bulkhead and coupled at a second end to the first bar; and
a biasing member coupled to the door panel and the second bar configured to upwardly bias the retractable header.

US Pat. No. 10,672,166

SYSTEMS AND METHODS FOR PROVIDING A VIRTUAL AIRCRAFT BUILD PROCESS

Gulfstream Aerospace Corp...

1. A computer-implemented method for displaying multiple aircraft build states of an aircraft build process, said method comprising:storing, in a computer storage device, visual depictions of the multiple aircraft build states that are layered over one another during the aircraft build process;
wherein the multiple aircraft build states of an aircraft represent different operational states of the aircraft over time during the aircraft build process;
wherein the visual depictions are associated with operational state data to indicate operational phases to which the visual depictions of the multiple aircraft build states are related, wherein the operational phases include a maintenance phase, a test phase, and a completed aircraft phase; and
providing, by one or more data processors, a user interface for display to a user; wherein the user interface is configurable to display the multiple aircraft build states as layers that correspond to a chronological order of each aircraft state of the multiple aircraft build states during the aircraft build process;
manipulating, by the user. the user interface to switch from displaying a visual photographic depiction of a substantially entire interior aircraft in the maintenance phase to displaying a visual photographic depiction of a substantially entire interior aircraft in the test phase; and
manipulating, by the user, the user interface to switch from displaying the visual photographic depiction of a substantially entire interior aircraft in the test phase to displaying a visual photographic depiction of a substantially entire interior aircraft in the completed aircraft phase.

US Pat. No. 9,889,946

ELECTRONIC CHECKLISTS WITH DYNAMIC VISIBILITY OF ANNOTATIONS

Gulfstream Aerospace Corp...

1. A display system for an aircraft, the display system comprising:
a display unit;
an input device; and
a controller communicatively coupled with the display unit and the input device, the controller having a first checklist presentation
mode and a second checklist presentation mode, the controller configured to:

retrieve an electronic checklist that includes a plurality of tasks including an annotated task associated with at least one
of a note, a caution, a warning, and task information (NCWI);

hide from view the at least one of the NCWI of the annotated task in an image of the electronic checklist based on viewing
criteria when the controller is in the first checklist presentation mode;

show in the electronic checklist the NCWI for each of the plurality of tasks that is associated with the NCWI regardless of
which of the plurality of tasks is an active task when the controller is in the second checklist presentation mode; and

generate a signal that causes the display unit to visually present the image.

US Pat. No. 10,252,705

SYSTEM FOR CONTROLLING A WHEEL BRAKE OF AN AIRCRAFT

Gulfstream Aerospace Corp...

1. A system for controlling a wheel brake of an aircraft, the system having a normal operational mode and a modulated operational mode, the system comprising:an input device configured to generate a command signal defining a first brake force;
a brake controller configured to generate a brake actuation signal in response to the command signal, the brake actuation signal defining a second brake force when the system is in the normal operational mode and defining a third brake force when the system is in the modulated operational mode, the third brake force being greater than the second brake force;
a fluid source configured to provide fluid in response to the brake actuation signal, the fluid having a first portion and a second portion;
a return valve in fluid communication with the fluid source, and configured to return the first portion of the fluid to the fluid source when the system is in the modulated operational mode;
a wheel brake in fluid communication with the fluid source and configured to engage a wheel of the aircraft in response to at least the second portion of the fluid; and
a wheel speed sensor configured to detect a wheel speed of the wheel;
wherein the system is in the modulated operational mode when the wheel speed is decreasing over a predetermined time period.

US Pat. No. 10,228,692

AIRCRAFT FLIGHT ENVELOPE PROTECTION AND RECOVERY AUTOPILOT

Gulfstream Aerospace Corp...

1. An avionics system for an aircraft, the avionics system comprising:a trajectory selection module configured to select a potential aircraft path relative to a current aircraft flight condition;
a trajectory flight condition module configured to estimate a modeled flight condition of the aircraft along the potential aircraft path, wherein the trajectory flight condition module comprises:
a vertical velocity module configured to calculate a vertical velocity of the aircraft on the potential aircraft path;
an energy state module configured to calculate an energy state of the aircraft on the potential aircraft path; and
an airspeed prediction module configured to estimate an airspeed of the aircraft on the potential aircraft path based on the vertical velocity and the energy state;
a limit comparison module configured to determine whether the modeled flight condition violates an aircraft limit; and
a violation indicator module configured to generate an indication of impending violation.

US Pat. No. 10,229,606

CONTROLLERS AND AIRCRAFT WITH PITCH AND FLIGHT PATH BASED FLIGHT DIRECTOR MODES

Gulfstream Aerospace Corp...

1. An avionics system, comprising:a display unit configured to present an image;
a controller communicatively coupled with the display unit and configured to control the display unit to present the image in a takeoff mode and in a flight mode of the controller, the controller further configured to:
receive signals indicating an aircraft attitude, a target attitude, and an aircraft flight path;
generate a marker in the image in the takeoff mode based on an attitude difference between the aircraft attitude and the target attitude;
generate the marker in the image in the flight mode based on the aircraft flight path; and
generate a signal that causes the display unit to present the image.

US Pat. No. 10,239,626

ARRANGEMENTS AND METHODS FOR SUPPLYING HEATED AIR TO A WING ANTI-ICING SYSTEM

Gulfstream Aerospace Corp...

1. An arrangement for supplying heated air to a wing anti-icing system on an aircraft propelled by a jet engine, the arrangement comprising:a pre-cooler configured to receive a flow of bleed-air from the jet engine, to receive a flow of cooling-air from a freestream, to cool the flow of bleed-air with the flow of cooling-air, to exhaust a flow of cooled bleed air, and to exhaust a flow of warmed cooling-air; and
an ejector configured to:
receive a portion of the flow of cooled bleed-air from the pre-cooler,
to entrain a portion of the flow of warmed cooling-air with the portion of the flow of cooled bleed-air,
to mix the portion of the flow of cooled bleed-air with the portion of the flow of warmed cooling-air to form a combined flow having a temperature and a volume suitable for use by the wing anti-icing system, and
to exhaust the combined flow.

US Pat. No. 10,399,662

AIRCRAFT WITH CABIN ACOUSTIC SYSTEMS HAVING QUARTER WAVELENGTH ABSORBERS

Gulfstream Aerospace Corp...

1. An aircraft comprising:a fuselage;
a passenger compartment disposed in the fuselage and having a cabin surface that defines a first aperture, wherein an entirety of the passenger compartment defines boundary conditions;
an air mass having a first acoustic mode defined by the boundary conditions; and
a first chamber acoustically coupled with the first aperture and having a length that is one quarter of a wavelength of sound at the first acoustic mode.

US Pat. No. 10,535,351

AIRCRAFT AND INSTRUMENTATION SYSTEM FOR VOICE TRANSCRIPTION OF RADIO COMMUNICATIONS

Gulfstream Aerospace Corp...

1. An aircraft instrumentation system, comprising:a radio device;
a display device for displaying information to a flight crew of an aircraft; and
a controller communicatively coupled with the radio device and the display device, the controller configured to:
monitor the radio device;
recognize a voice communication received over the radio device;
generate an electronic transcript of the voice communication;
replace spoken word waypoints, spelled out phonetic alphabet waypoints, and combinations thereof in the electronic transcript with standardized waypoint identifiers; and
control the display device to display a transcript of the voice communication.

US Pat. No. 10,533,840

METHOD FOR CHARACTERIZING SHAPE CHANGES OF AN AIRCRAFT DUE TO FLIGHT LOADS

Gulfstream Aerospace Corp...

1. A method for characterizing shape changes of an interior portion of an aircraft from flight loads, the method comprising the steps of:positioning one or more 3D scanners within the interior portion of the aircraft;
creating a reference scan of the interior portion with the one or more 3D scanners while the aircraft is substantially stationary and/or on the ground;
creating a deformed scan of the interior portion with the one or more 3D scanners while the aircraft is in flight subject to substantial flight loads; and
postprocessing and analyzing the reference scan and the deformed scan to characterize the shape changes of the interior portion of the aircraft from the substantial flight loads.

US Pat. No. 10,532,805

AIRFOIL FOR AN AIRCRAFT HAVING REDUCED NOISE GENERATION

Gulfstream Aerospace Corp...

1. An airfoil having reduced noise generation for use with an aircraft, the airfoil comprising:a body having a leading edge spaced from a trailing edge and a side surface disposed between the leading edge and the trailing edge, the body defining an inlet proximate to the leading edge and configured to receive air, the side surface defining an outlet in fluid communication with the inlet, and the outlet configured to exhaust air away from the side surface; and
a cover overlying the inlet and movable between a first cover position and a second cover position, and the cover configured to prevent movement of air through the inlet when the cover is in the first cover position and configured to permit movement of air through the inlet when the cover is in the second cover position, wherein the cover is biased toward the first cover position and is configured to move from the first cover position to the second cover position in response to a stagnation pressure on the cover when the body is in a second position in which the stagnation pressure is aligned with the cover.

US Pat. No. 10,398,229

CORNER ARRANGEMENT FOR AN ARTICLE OF FURNITURE, ARTICLE OF FURNITURE, AND METHOD OF MAKING THE SAME

Gulfstream Aerospace Corp...

1. An article of furniture comprising:a first core having a first end;
a second core having a second end, the second core positioned adjacent to the first core such that the second core is oriented substantially transverse to the first core and such that the first end and the second end form a corner having an outside portion and an inside portion;
a first skin extending and adhered along an outer surface of the first core; and a second skin extending and adhered along an outer surface of the second core, the second skin further extending and adhered around the outside portion of the corner, and the second skin further extending and adhered along one of a portion of the outer surface of the first core and a portion of the first skin, the first skin and the second skin cooperating to affix the second core to the first core without any mechanical fasteners;
a third core affixed to the second core to form a second corner;
a fourth core affixed to the third core and to the first core to form a third corner and a fourth corner,
wherein the first core, the second core, the third core, and the fourth core cooperate to form a housing.

US Pat. No. 10,543,539

DRILLING AID APPARATUS AND A METHOD FOR DRILLING A STRUCTURE

Gulfstream Aerospace Corp...

1. A drilling aid apparatus comprising:a bushing holder portion having a first surface for facing a first structure portion, a second surface on a side opposite the first surface and facing upward away from the bushing holder portion, and an opening formed through the bushing holder portion extending from the first surface to the second surface, wherein the opening is configured to receive a bushing that is sized for guiding a drill bit for drilling into the first structure portion, wherein the bushing holder portion has a drilling chip relief channel formed along the first surface extending between the opening and a lateral edge section of the bushing holder portion, and wherein the drilling chip relief channel is configured to allow drilling chips formed from drilling the first structure portion with the drill bit to be advanced through the drilling chip relief channel towards the lateral edge section of the bushing holder portion; and
a first coupling member coupled to the bushing holder portion and extending generally upward exposed to the second surface, and wherein the first coupling member is configured to couple to a second structure portion for supporting the bushing holder portion in a fixed position relative to the first structure portion.

US Pat. No. 10,538,072

DEVICES AND METHODS FOR DISPENSING ADHESIVE ELEMENTS

Gulfstream Aerospace Corp...

1. A device for dispensing adhesive elements,the device comprising:
a first holder configured to rotatably hold a film having adhesive elements and a protective layer attached on adhesive areas of the adhesive elements;
a second holder configured to receive the protective layer as the protective layer is peeled off the adhesive areas of the adhesive elements while the adhesive elements move towards an alignment element; and
the alignment element arranged in a direction of movement of the adhesive elements at a predetermined position on the alignment element and configured to receive and align the adhesive elements.

US Pat. No. 10,472,043

OVER-FRAME BLANKET ASSEMBLIES AND METHODS OF INSTALLATION IN FUSELAGE ASSEMBLIES

Gulfstream Aerospace Corp...

1. A fuselage assembly for an aircraft, the fuselage assembly comprising:a fuselage structural member;
a fuselage skin associated with the fuselage structural member;
a cabin liner having an outer side facing the fuselage skin;
an over-frame blanket assembly disposed between the fuselage skin and the cabin liner and separated from the cabin liner, the over-frame blanket assembly comprising a first blanket piece, the first blanket piece comprising:
a first sound barrier layer that defines a first outer surface of the over-frame blanket assembly that is exposed radially inward of the over-frame blanket assembly and faces the cabin liner, and
a first sound absorbing layer that defines a second outer surface of the over-frame blanket assembly facing the fuselage skin; and
a retaining assembly comprising:
a retaining spike passing through an aperture in the first blanket piece; and
a retaining cap coupled with the fuselage structural member, secured to the retaining spike, and including a vibration isolating layer that abuts the first sound barrier layer.

US Pat. No. 10,414,515

AIRCRAFT AND DEPLOYABLE VISION SYSTEMS FOR AIRCRAFT

Gulfstream Aerospace Corp...

1. An aircraft comprising:a fuselage defining an outer mold line; and
a vision sensor system comprising;
a housing selectively deployable between a retracted position and a deployed position, the housing disposed within the outer mold line in the retracted position and outside of the outer mold line in the deployed position,
a vision sensor package associated with the housing and positioned to collect imaging information when the housing is in the deployed position, and
a controller configured to deploy and retract the vision sensor system.

US Pat. No. 10,486,568

SEAT ASSEMBLIES INCLUDING AN ARMREST WITH AN ARMREST LID AND A HINGE ARRANGEMENT

Gulfstream Aerospace Corp...

1. A seat assembly comprising:a seat base portion and a seat backrest portion that include at least in part a seat frame that supports the seat backrest portion extending substantially upright from the seat base portion; and
an armrest disposed adjacent to the seat base portion and forward of the backrest portion, wherein the armrest comprises:
a fixed armrest portion that is coupled to the seat frame; and
an armrest lid configured to move relative to the fixed armrest portion between a closed position overlying an upper section of the fixed armrest portion and an open position allowing access to the upper section of the fixed armrest portion; and
a hinge arrangement pivotably coupling the armrest lid to the fixed armrest portion, wherein the hinge arrangement comprises a damper and a damper gear that meshes with the damper to dampen movement of the armrest lid between the closed and open positions, wherein the damper gear is coupled to the armrest lid, and wherein the fixed armrest portion defines a track and the hinge arrangement further comprises:
at least one guide bearing coupled to the armrest lid and movably disposed in the track to limit a range of opening of the armrest lid; and
a linkage coupling the at least one guide bearing to the damper gear to move the damper gear during movement of the armrest lid, wherein the hinge arrangement further comprises at least one shaft coupled to the armrest lid and disposed through the at least one guide bearing, and wherein the linkage comprises:
a coupler link coupled to the at least one shaft; and
a damper link coupled to the coupler link and the damper gear.

US Pat. No. 10,259,564

CONTROLLING ELEVATOR TO STABILIZER OFFLOAD IN FLY-BY-WIRE AIRCRAFT SYSTEMS

Gulfstream Aerospace Corp...

1. A control unit for controlling movement of a stabilizer and an elevator on an aircraft, the control unit comprising:a processor, configured to:
receive a pitch reference command from a flight control input device of the aircraft;
determine, based on the pitch reference command, an elevator command configured to command the elevator in the aircraft nose-up or nose-down direction;
determine a difference between the elevator command and a desired elevator value based on an estimated elevator effectiveness and corresponding to the pitch reference command, wherein the estimated elevator effectiveness is a relationship between elevator deflection and resulting airplane response at a given altitude and airspeed condition;
determine a threshold value as a desired maximum value of the difference at a given pitch reference command;
compare the difference with the threshold value and in response thereto generate a command signal configured to retain a current position of the stabilizer when the difference is smaller than or equal to the threshold value, and to command the elevator in the aircraft nose-up or nose-down direction based on the pitch reference command.

US Pat. No. 10,225,673

SYSTEM FOR IDENTIFYING A SOURCE OF AN AUDIBLE NUISANCE IN A VEHICLE

Gulfstream Aerospace Corp...

1. A system for identifying a source of an audible nuisance in a vehicle, the system comprising:a device configured to receive a visual dataset, and to generate a camera signal in response to the visual dataset;
a dock configured to removably couple to the device, the dock comprising a microphone array configured to receive the audible nuisance, and to generate a microphone signal in response to the audible nuisance; and
a processor module configured to be communicatively coupled with the device and the dock, to generate a raw soundmap signal in response to the microphone signal, to combine the camera signal and the raw soundmap signal, and to generate a camera/soundmap overlay signal in response to combining the camera signal and the raw soundmap signal.

US Pat. No. 10,417,840

METHODS, SYSTEMS AND APPARATUS FOR AUTOMATED GENERATION OF A FLIGHT LOG AND A SQUAWK LIST FILE

Gulfstream Aerospace Corp...

1. A method, comprising:recording, at an on-board computer, preliminary squawk events that occur while an aircraft is in flight;
presenting, at a portable device, the preliminary squawk events;
receiving approval inputs that indicate approved squawk events of the preliminary squawk events; and
generating a squawk list that includes each of the approved squawk events to be investigated for corrective action after the flight.

US Pat. No. 10,537,978

METHOD AND APPARATUS FOR WHEEL MAINTENANCE

Gulfstream Aerospace Corp...

1. An apparatus for wheel maintenance, comprising:a frame having a first pair of opposing rails and a second pair of opposing rails orthogonal to the first pair of opposing rails;
a first roller coupled at each end to the second pair of opposing rails and having a first rotational axis orthogonal to the second pair of opposing rails;
a second roller spaced apart from the first roller and coupled at each end to the second pair of opposing rails and having a second rotational axis coplanar with the first rotational axis; and
a rotating base coupled to the frame for rotating the frame and first and second rollers about a third rotational axis orthogonal to the first and second rotational axes;
wherein, a wheel positioned on the first and second rollers may be rotated about a wheel rotational axis and the third rotational axis by the rollers and the rotating base during a maintenance procedure.

US Pat. No. 10,384,760

SELF-ADJUSTING DOOR JAMB FOR AN AIRCRAFT DOOR

Gulfstream Aerospace Corp...

20. A vehicle, comprising:one or more engines for propelling the vehicle;
a passenger cabin;
one or more bulkheads within the passenger cabin;
at least one of the one or more bulkheads having a first opening therein for receiving a slideable door panel and a surface for receiving a door jamb receiver;
a door jamb configured to receive an edge of the slidable door panel as it slides from an open position to a closed position wherein the door jamb has a first position when the edge of the interior door comes into contact with the door jamb and moves the door jamb into a second position when the interior door is in the closed position;
a plurality of bias mechanisms each positioned within the door jamb receiver and coupled to the door jamb, the plurality of bias mechanisms being compressed as the door jamb moves into the second position while facilitating movement of the door jamb along an axis; and
a plurality of angular translating mechanisms each positioned within the door jamb receiver and respectively coupled to one of the plurality of bias mechanisms and facilitating angular displacement of the door jamb relative to the axis;
wherein, the movement of the door jamb along the axis and the angular displacement of the door jamb maintain contact between the slideable door panel and the door jamb despite forces applied to the bulkhead.

US Pat. No. 10,322,810

IN-FLIGHT LEVELING SYSTEM

Gulfstream Aerospace Corp...

1. An in-flight leveling system for a seat onboard an aircraft, the seat having a seat cushion and a seat back and the aircraft traveling at an angle of inclination during flight, comprising:a seat track and swivel mechanism coupled to the seat and to the leveling system, the seat track and swivel mechanism having a front pivot point providing selective arcuate movement of an aft portion of the seat to compensate for the angle of inclination of the aircraft during the flight;
the leveling system, comprising:
a locking mechanism positioned beneath and coupled to the seat track and swivel mechanism to retain the seat in a first position and a second position; and
an actuator positioned beneath the seat track and swivel mechanism for moving the locking mechanism between a locked condition and an unlocked condition permitting the aft portion of the seat to move between the first position to the second position;
whereby, the actuator moves the locking mechanism from the locked condition to the unlocked condition permitting the aft portion of the seat to move from the first position to the second position to remain substantially level during the flight due to the seat track and swivel mechanism compensating for the angle of inclination of the aircraft during the flight.

US Pat. No. 10,315,366

APPARATUSES AND METHODS FOR MAKING REINFORCEMENT STRUCTURES

Gulfstream Aerospace Corp...

1. An apparatus for making a reinforcement structure, the apparatus comprising:a first rigid mandrel; and
a first flexible bladder at least partially surrounding the first rigid mandrel for supporting a reinforcement structure-forming material during fabrication of the reinforcement structure, wherein the first flexible bladder is configured to apply a force to the reinforcement structure-forming material in a direction opposite the first rigid mandrel in response to a pressure differential between inside and outside of the first flexible bladder, wherein the apparatus further comprises a heating and/or pressurizing device configured for heating and curing of the reinforcement structure-forming material, wherein the first flexible bladder has an open end and the first rigid mandrel is disposed inside of the first flexible bladder and extends therefrom through the open end during both the pressure differential and curing of the reinforcement structure-forming material in the heating and/or pressurizing device with a portion of the first rigid mandrel disposed outside the first flexible bladder, wherein the first flexible bladder is configured to inflate from a nominal condition to a pressurized condition in response to the pressure differential, wherein the first flexible bladder in the nominal condition is sized nearly net fit to the first rigid mandrel, and wherein in the pressurized condition a first inner bladder surface of the first flexible bladder is spaced apart from a first outer mandrel surface of the first rigid mandrel a distance of from about 0.001 to about 5 mm during both the pressure differential and curing of the reinforcement structure-forming material.

US Pat. No. 10,540,905

SYSTEMS, AIRCRAFTS AND METHODS FOR DRONE DETECTION AND COLLISION AVOIDANCE

Gulfstream Aerospace Corp...

1. A system for drone detection and collision avoidance, the system comprising:a sensor;
a processor; and
an avoidance unit comprising a control unit,
wherein the sensor is configured to detect a drone signal in a predetermined space and to transmit the drone signal to the processor,
wherein the processor is configured to determine the presence of a drone in the predetermined space based on the drone signal, wherein the drone is separate from the system,
wherein the processor is configured to transmit a command to the avoidance unit when the processor determines the presence of a drone,
wherein the control unit is configured to receive the command and to generate a warning signal in response to receiving the command, and
wherein the avoidance unit is configured to transmit an avoidance signal to the drone in response to the control unit receiving the command, wherein the avoidance signal is configured to interact with the drone and is at least one of a control signal, an interference signal, and a location spoofing signal, and
wherein the control signal uses control frequencies identified by intercepting drone control signals sent by an operator of the drone and by decoding the drone control signals to find the control frequencies used to control the drone.

US Pat. No. 10,518,675

SEAT ASSEMBLY INCLUDING A MODULAR FOAM ARRANGEMENT WITH A VENTING MODULAR SECTION AND METHOD FOR FABRICATING THE SAME

Gulfstream Aerospace Corp...

1. A seat assembly comprising: a seat frame; a seat cushion supported by the seat frame and comprising: a modular foam arrangement having an interior surface disposed therein, the modular foam arrangement comprising a venting modular section in fluid communication with the interior surface, wherein the venting modular section has a chamber formed therein and a plurality of vents in fluid communication with the chamber; and an outer covering that at least partially covers the modular foam arrangement; and an air movement device in fluid communication with the venting modular section for advancing air between the interior surface and the air movement device, wherein the air movement device is disposed in the chamber of the venting modular section and draws air from about the interior surface through the vents to the air movement device for removing heat from the seat cushion, wherein the venting modular section is a venting modular foam section comprising a foam material.

US Pat. No. 10,351,226

SYSTEMS AND METHODS FOR CONTROLLING A MAGNITUDE OF A SONIC BOOM

Gulfstream Aerospace Corp...

1. A method of controlling a magnitude of a sonic boom caused by operation of a supersonic aircraft at supersonic speeds, the method comprising the steps of:operating the supersonic aircraft at supersonic speeds, the supersonic aircraft having a lift generating component, the lift generating component having a plurality of composite plies, all composite plies of the plurality of composite plies being oriented at an angle such that an axis of greatest stiffness is oriented at an angle of ten to thirty degrees with respect to a rear spar of the lift generating component, and the lift generating component being free of any composite ply having an axis of greatest stiffness oriented in a manner that is parallel to the rear spar of the lift generating component;
reducing twist of the lift generating component caused by operation of the supersonic aircraft at supersonic speeds with the composite plies; and
minimizing the magnitude of the sonic boom through reduction of twist of the lift generating component.

US Pat. No. 10,220,938

AIRCRAFT, CONTROL SURFACE ARRANGEMENTS, AND METHODS OF ASSEMBLING AN AIRCRAFT

Gulfstream Aerospace Corp...

1. An aircraft comprising:an airframe;
a control surface; and
a plurality of rotary actuators cooperating to rotatably mount the control surface to the airframe, the plurality of rotary actuators being directly mounted to the airframe and supporting the control surface on the airframe and configured to rotate the control surface with respect to the airframe when the plurality of rotary actuators is actuated, the plurality of rotary actuators further configured to be coupled to the control surface at a longitudinally intermediate position along an output shaft of each rotary actuator.

US Pat. No. 10,457,384

EMISSION-CAPTURING APPARATUS AND METHOD FOR CAPTURING EMISSIONS FROM AN EJECTION PORT

Gulfstream Aerospace Corp...

1. An emission-capturing apparatus for use in conjunction with a vehicle having a surface, the surface including an ejection port, the emission-capturing apparatus comprising:a tank having an inlet and an outlet, the outlet being disposed above a bottom of the tank, an internal ambient pressure of the tank being at least equal to an external ambient pressure at all times;
a muffler fluidly coupled with the outlet, the muffler configured to intercept all fluid exiting the outlet, to permit passage of gas through the muffler, and to inhibit passage of liquid through the muffler;
a hose having a tank end and a coupler end, the tank end fluidly coupled to the inlet of the tank; and
a coupler fluidly coupled to the coupler end of the hose, the coupler having a drain hole extending through the coupler, the coupler configured to be fluidly coupled to the surface, to completely cover the ejection port, and to support the coupler end of the hose in a position to receive an emission from the ejection port when the coupler is coupled to the surface and when the drain hole is aligned with the ejection port.

US Pat. No. 10,351,394

LOAD ASSEMBLY AND METHOD FOR LIFTING A LOAD INTO AN AIRCRAFT

Gulfstream Aerospace Corp...

1. A load assembly for use with an aircraft, the load assembly comprising:a support sub-assembly configured for removable coupling to a structural member of the aircraft, the structural member having a first interior position and a second interior position, the support sub-assembly extending between the first interior position and the second interior position, wherein the support sub-assembly comprises one or more retainer clamps including a forward retainer clamp and an aft retainer clamp configured to engage the structural member of the aircraft for removable coupling the support sub-assembly to the structural member of the aircraft, and wherein the support sub-assembly comprises a beam portion and a fixed spacer portion extending transversely from the beam portion, the fixed spacer portion comprises the forward retainer clamp and the beam portion comprises the aft retainer clamp; and
a lifting sub-assembly movably coupled to the support sub-assembly, the lifting sub-assembly movable along the support sub-assembly between the first interior position and the second interior position and configured to lift or lower a load and to support the load as the lifting sub-assembly moves along the support sub-assembly between the first interior position and the second interior position.

US Pat. No. 10,351,248

AIRCRAFT AND AIRCRAFT WINDSHIELD HEATING SYSTEMS

Gulfstream Aerospace Corp...

1. An aircraft windshield heating system for use on a flight deck of an aircraft, the aircraft windshield heating system comprising:a windshield having a main portion and a reduced portion;
a first heating element thermally coupled with the main portion of the windshield;
a second heating element thermally coupled with the reduced portion of the windshield; and
a power bus controller operatively coupled with the first heating element and the second heating element and configured for coupling to a primary power supply and a backup power supply, the power bus controller configured to determine when the primary power supply is available, to direct power from the primary power supply to the first heating element when the primary power supply is available and to direct power from the backup power supply to the second heating element and restrict power transfer to the first heating element when the primary power supply is not available.

US Pat. No. 10,669,043

FIXTURES FOR WORKING AIRCRAFT COMPONENTS AND METHODS FOR THE SAME

Gulfstream Aerospace Corp...

1. A rib for working an aircraft component having an aircraft component surface, the rib comprising:a rib surface configured to receive the aircraft component and the rib surface configured to be in abutting contact with at least a portion of the aircraft component surface, wherein the rib surface is arched and has an upper portion with an apex that has a curved shape; and
a plurality of extensions extending away from the rib in different directions, the plurality of extensions including a first extension and a second extension each independently configured to be received in a mount to couple to a worksurface;
wherein orientation of the rib is configured to be adjustable relative to the worksurface for improving working of the aircraft component, wherein the rib surface extends to a perimeter of the rib surface, the rib defines an unoccupied groove surrounding the rib surface adjacent the perimeter, and the groove extends to a groove surface that is substantially parallel to the rib surface, wherein when the second extension is disposed in the mount to couple to the worksurface, the orientation of the rib is different than when the first extension is disposed in the mount to couple to the worksurface.

US Pat. No. 10,703,239

SEAT ASSEMBLY INCLUDING A MODULAR FOAM ARRANGEMENT AND METHOD FOR FABRICATING THE SAME

Gulfstream Aerospace Corp...

1. A seat assembly comprising:a seat frame; and
a seat cushion supported by the seat frame and comprising:
a modular foam arrangement comprising a first modular foam section having a first interlocking feature and a second modular foam section having a second interlocking feature engaged with the first interlocking feature, wherein the second modular foam section is disposed adjacent to the first modular foam section along an interface, and wherein the interface is free of any adhesive and is defined by corresponding unbonded trimmed surfaces of the first and second modular foam sections that are in direct contact with each other; and
an outer covering that at least partially covers the modular foam arrangement.

US Pat. No. 10,711,391

CLOTHES STEAMER FOR AN AIRCRAFT CABIN

Gulfstream Aerospace Corp...

1. A clothes steamer for an aircraft cabin, the clothes steamer comprising:a case having a closable door, the case and closable door defining a clothes holding cavity;
a steam generator fluidly coupled to the clothes holding cavity, the steam generator configured to produce steam and to direct the steam into the clothes holding cavity;
a humidity sensor configured to provide a humidity signal indicative of the humidity within the clothes holding cavity;
a temperature sensor configured to produce a temperature signal indicative of the temperature within the clothes holding cavity;
a pressure sensor configured to provide a pressure signal indicative of an atmospheric pressure within the aircraft cabin;
a controller electrically coupled to the steam generator, the humidity sensor, the temperature sensor, and the pressure sensor, the controller configured to produce a steamer control signal,
wherein said steam generator is configured to receive the steamer control signal and to produce an amount of steam based on the steamer control signal.

US Pat. No. 10,688,890

SEAT ASSEMBLY THAT RECLINES AND INCLUDES A BACK PANEL

Gulfstream Aerospace Corp...

1. A seat assembly comprising:a seat frame for supporting the seat assembly and comprising a seat structure portion and a backrest structure portion pivotally coupled to the seat structure portion for movement between a substantially upright seat position and a substantially reclined seat position;
an upper back shell panel coupled to the seat frame and having an outer surface on a side opposite the seat frame; and
a lower back skirt panel having an upper edge portion and disposed adjacent to the upper back shell panel and a gap is present between the lower back skirt panel and the upper back shell panel, wherein the lower back skirt panel and the upper back shell panel are cooperatively configured to allow relative movement between each other during movement of the seat frame between the substantially upright seat position and the substantially reclined seat position while maintaining at least a portion of the gap between the lower back skirt panel and the upper back shell panel, wherein the lower back skirt panel and the upper back shell panel are operatively coupled together with a track-cam arrangement, wherein the lower back skirt panel is pivotably coupled to the seat frame.

US Pat. No. 10,731,556

ISENTROPIC COMPRESSION INLET FOR SUPERSONIC AIRCRAFT

Gulfstream Aerospace Corp...

1. An external compression inlet for use with a supersonic jet engine, comprising:a cowl having a cowl lip; and
an external compression surface comprising, in cross section, a leading edge or point, an initial segment downstream of the leading edge or point and inclined at a constant, initial turn angle with respect to a freestream, a curved segment downstream of the initial segment, the curved segment inclined with respect to a freestream at a varying angle which increases in an aft direction, a straight segment downstream of the curved segment, and a transition from the straight segment to a shoulder;
wherein said external compression surface is disposed such that, at a predetermined design cruising speed, a terminal shock extends from a point proximate said cowl lip to said external compression surface; and
wherein said curved segment comprises a relaxed isentropic compression surface which differs from a conventional isentropic compression surface in that said relaxed isentropic compression surface, at said predetermined design cruising speed, is characterized by a continuum of infinitesimally weak shocklets, a plurality of which are defocused away from said cowl lip and extend along said terminal shock.

US Pat. No. 10,683,883

WEB COMPONENT AND METHOD OF MAKING A WEB COMPONENT

Gulfstream Aerospace Corp...

1. A web component suitable for use with a snap-fit assembly, the web component comprising:a unitary sheet metal member having a periphery, a first side and a second side, the sheet metal member including a plurality of protrusions integral with the sheet metal member, the plurality of protrusions extending from a first surface of the first side and from a second surface of the second side, the plurality of protrusions disposed in a region proximate a portion of the periphery and inset from the portion of the periphery, the sheet metal member further including a plurality of depressions extending into the first surface and into the second surface, the plurality of depressions being disposed in the region, the plurality of depressions being aligned with the plurality of protrusions, each depression of the plurality of depressions being spaced apart from each protrusion of the plurality of protrusions along the first side and the second side, the sheet metal member having a central region located within the periphery, the region forming an outer border of the central region, the central region being free of protrusions and depressions,
wherein the central region comprises a majority portion of the unitary sheet metal member.

US Pat. No. 10,882,427

SEAT ASSEMBLY INCLUDING AN ARMREST SUB-ASSEMBLY AND METHOD FOR FABRICATING THE SAME

Gulfstream Aerospace Corp...

1. A seat assembly comprising:a seat base portion;
a seat backrest portion coupled to the seat base portion and configured to extend substantially upright from the seat base portion; and
an armrest sub-assembly configured to move between a stowed position that is substantially within the seat backrest portion and an extended position that is forward of the seat backrest portion, wherein at least a portion of the armrest sub-assembly translates substantially linearly along an incline that is at an angle of from 20 to 80° relative to the seat base portion and that is forward of the seat backrest portion during movement from the stowed position towards the extended position.

US Pat. No. 10,807,693

AIRCRAFT AIR STAIR SUPPORT

Gulfstream Aerospace Corp...

1. An air stair support system comprising:an aircraft fuselage defining a door frame that defines a door opening, the door frame defining a stair hook receptacle;
a stair door configured to pivot between a retracted position within the door opening and an extended position in which the stair door is configured to form an aircraft entry/exit stairway;
a door bulb seal attached to the door frame and extending into the door opening; and
a stair support cable assembly comprising:
at least one cable having a door frame end and a stair end, the at least one cable extending away from the door frame along a line that passes through the door bulb seal;
a first hook comprising:
a curved end portion hooked onto the stair hook receptacle;
a cable end portion secured to the door frame end of the at least one cable at the line; and
an intermediate portion including a first intermediate leg, a second intermediate leg, and a curved middle portion, wherein the first intermediate leg is adjacent to the curved end portion and is substantially straight, and wherein the second intermediate leg is adjacent to the cable end portion and is substantially straight, and wherein the curved middle portion is connected to the first intermediate leg and the second intermediate leg and defines a widest lateral dimension of the first hook to extend the intermediate portion away from the door bulb seal when the stair support cable assembly is installed on the door frame and the stair door; and
a second hook configured to secure to the stair end and to hook on the stair door.

US Pat. No. 10,704,306

TUNABLE STAY FOR AIRCRAFT COMPARTMENT CLOSURE

Gulfstream Aerospace Corp...

1. A tunable stay device for a closure of an aircraft, comprising:a mounting base extending, at least in part, along a mounting axis and mountable to the closure or an area of the aircraft in proximity to the closure;
a holding element mounted for movement along the mounting axis and configured to, at least in part, effect a hold force; and
an adjuster mounted to at least one of the mounting base and the holding element and configured and arranged to effect a change in position of the holding element with respect to the mounting base along the mounting axis;
wherein, when the stay device is mounted to the closure or in the area of the aircraft in proximity to the closure, the hold force biases the closure in one of an open orientation and a closed orientation, wherein the holding element is configured to effect the hold force with cooperation from a coupling element located at the closure or in the area of the aircraft in proximity to the closure, wherein the holding element is a magnet having an opening and the coupling element is one of a magnet and a magnetically permeable element and
wherein the mounting base has a mounting post extending along the mounting axis that is received in the opening of the magnet, the mounting post having an engagement feature for adjustably mounting the magnet to the mounting base.

US Pat. No. 10,946,985

CRADLE ASSEMBLY FOR SUPPORTING A DOOR OF AN AIRCRAFT TO FACILITATE SERVICING THE DOOR, AND ARRANGEMENTS AND METHODS FOR THE SAME

Gulfstream Aerospace Corp...

1. A cradle assembly for supporting a door of an aircraft to facilitate servicing the door, the cradle assembly comprising:a base comprising a base plate; and
a cradle support subassembly pivotably coupled to the base above the base plate and configured to support an outer section of the door, the cradle support subassembly comprising:
a first pair of arms that are spaced apart from each other and that extend in a first direction;
a second pair of arms that are spaced apart from each other and that extend in a second direction that is at an angle to the first direction; and
a gusseted skin coupled to the first and second pair of arms, and wherein the gusseted skin is operatively coupled to the base to allow the cradle support subassembly to pivot relative to the base.

US Pat. No. 10,899,467

ENGINE INLET COVER DETECTION SYSTEM AND METHOD

Gulfstream Aerospace Corp...

1. A cover detection system, comprising:an engine having moving parts and defining a fluid opening, wherein the fluid opening exposes the moving parts to an ambient environment and remains uncovered during operation of the engine;
a first sensor component proximate to the engine;
an engine cover assembly comprising:
an engine cover configured to cover the fluid opening and to be completely separated from the engine during operation of the engine; and
a second sensor component attached to the engine cover and configured to interact with the first sensor component; and
a controller configured to determine whether the engine cover is installed on the engine based on an interaction between the first sensor component and the second sensor component.

US Pat. No. 10,876,856

AIRCRAFT HUD WITH CURVED TAPES AND FLIGHT MODE ANNUNCIATION BOXES

Gulfstream Aerospace Corp...

1. An aircraft, comprising:an avionics system comprising:
a display screen configured to present an image arrangement that is visible to a user; and
a controller configured to:
generate curved tapes in the image arrangement to convey flight values to the user, wherein the curved tapes are configured to direct an eye of the user to a portion of the image arrangement; and
roll the curved tapes three-dimensionally based on changes to flight values of the aircraft to provide peripheral indication of changes to flight values when the flight values are changing, and
wherein the controller is further configured to generate the curved tapes as a left tape and a right tape at a left side and a right side of the display screen with a distance between centers of the curved tapes being greater than a distance between ends of adjacent curved tapes.

US Pat. No. 10,875,629

YOKE INSTALLATION PROTECTION ASSEMBLY WITH INTEGRATED INCLINOMETER PORTION

Gulfstream Aerospace Corp...

1. A yoke alignment assembly for aligning an aircraft yoke with a column, the yoke alignment assembly comprising:a rigid cover defining a protective portion configured to protect the yoke and an inclinometer portion configured to hold an inclinometer; and
a flexible cover secured to an upper part of the protective portion and configured to protect the yoke.

US Pat. No. 10,869,552

CORNER ARRANGEMENT FOR AN ARTICLE OF FURNITURE, ARTICLE OF FURNITURE, AND METHOD OF MAKING THE SAME

Gulfstream Aerospace Corp...

1. A method for making an article of furniture, the method comprising:setting up a fixture in a manner that includes a first corner, wherein the fixture comprises a plurality of cores, and wherein setting up the fixture comprises arranging the plurality of cores in a manner corresponding to a desired shape of the article of furniture;
sealing all seams between adjacent cores of the plurality of cores;
positioning a first skin and a second skin in the fixture such that, at the first corner, the second skin one of overlaps and underlaps the first skin;
positioning a first core and a second core in the fixture such that the first core and the second core form a second corner free of any mechanical fasteners, such that the second corner is aligned with the first corner, and such that the second skin wraps around the second corner;
compressing the fixture, the first skin, the second skin, the first core, and the second core;
curing an adherent between the first skin, the second skin, the first core and the second core;
removing an assembly of the first core, the second core, the first skin, and the second skin from the fixture.

US Pat. No. 10,744,724

COMPOSITE AIRCRAFT MANUFACTURING TOOLING AND METHODS USING ARTICULATING MANDRELS

Gulfstream Aerospace Corp...

1. A composite tooling system for manufacturing a composite stringer of an aircraft, the composite tooling system comprising:an articulating stringer mandrel, the articulating stringer mandrel comprising:
a first rigid mandrel element defining a first cavity having a first cavity surface at an end of the first rigid mandrel element;
a second rigid mandrel element defining a second cavity having a second cavity surface at an end of the second rigid mandrel element opposing the first cavity of the first rigid mandrel element,
wherein a first cross section perimeter of the first rigid mandrel element is shorter than a second cross section perimeter of the second rigid mandrel element, and wherein the first cross section perimeter and the second cross section perimeter are each substantially uniform along a longitudinal direction;
a mandrel ball disposed at least partially within the first cavity of the first rigid mandrel element and at least partially within the second cavity of the second rigid mandrel element, the mandrel ball defining a first pivot surface and a second pivot surface, wherein the first pivot surface opposes and has substantially a same shape as the first cavity surface of the first rigid mandrel element and the second pivot surface opposes and has substantially a same shape as the second cavity surface of the second rigid mandrel element; and
a cable having a relaxed state and a tensed state, wherein the relaxed state permits the first rigid mandrel element and the second rigid mandrel element to pivot with respect to each other about the mandrel ball, and wherein in the tensed state the cable tightens the articulating stringer mandrel to compress the first rigid mandrel element, the mandrel ball, and the second rigid mandrel element.

US Pat. No. 10,996,810

WINDOW FOR AN AIRCRAFT AND DISPLAY FOR AIRCRAFT WINDOW

Gulfstream Aerospace Corp...

1. A window for an aircraft, the window comprising:a transparent outer window member;
a transparent inner window member;
a thin film transparent display disposed between the transparent outer window member and the transparent inner window member, the transparent display being configured to display information to a passenger; and
a controllable data transmission circuit configured to provide a signal to the transparent display to vary light transmission through the thin film transparent display, wherein the window further comprises:
a first sensor configured to measure an amount of light from outside the aircraft being transmitted through the thin film transparent display and provide a first signal indicative thereof;
a second sensor configured to measure an amount of light within the passenger compartment and provide a second signal indicative thereof, and wherein the controllable data transmission circuit is configured to measure a difference between the first and second signals; and
a third sensor configured to measure a temperature of the thin film transparent display and provide a third signal indicative thereof, and wherein the controllable data transmission circuit is configured to provide a fourth signal as the signal to the thin film transparent display based on the third signal and the difference between the first and second signals to vary the light transmission through the thin film transparent display.

US Pat. No. 10,982,623

PROPULSION SYSTEM FOR AN AIRCRAFT, A NOZZLE FOR USE WITH THE PROPULSION SYSTEM, AND A METHOD OF MANUFACTURING A PROPULSION SYSTEM FOR AN AIRCRAFT

Gulfstream Aerospace Corp...

1. A propulsion system for an aircraft, the propulsion system comprising:an engine configured to generate a mass flow;
a nozzle coupled with the engine, the nozzle having a pathway extending therethrough, the pathway configured to guide the mass flow, the pathway including a throat and a trailing edge, the trailing edge defining an exit plane, at least one of the throat and the trailing edge configured to enlarge and contract;
a first deployable obstructer disposed within the pathway, the first deployable obstructer configured to move between a deployed position and a retracted position, the first deployable obstructer configured to partially obstruct the pathway when the first deployable obstructer is out of the retracted position and to avoid obstructing the pathway when the first deployable obstructer is in the retracted position;
a first pressure sensor associated with the pathway and disposed to sense a static pressure of the mass flow at the trailing edge;
a second pressure sensor associated with the aircraft and disposed to sense an ambient pressure of a freestream proximate the aircraft; and
a controller communicatively coupled with the first pressure sensor and the second pressure sensor and operatively coupled with the first deployable obstructer and with the at least one of the throat and the trailing edge configured to enlarge and contract, the controller configured to obtain the static pressure from the first pressure sensor, to obtain the ambient pressure from the second pressure sensor, to compare the static pressure with the ambient pressure, and in response to a disparity between the static pressure and the ambient pressure, the controller is further configured to control at least one of the first deployable obstructer and the at least one of the throat and the trailing edge configured to enlarge and contract in a manner that reduces the disparity.

US Pat. No. 10,981,659

PROPULSION SYSTEM USING LARGE SCALE VORTEX GENERATORS FOR FLOW REDISTRIBUTION AND SUPERSONIC AIRCRAFT EQUIPPED WITH THE PROPULSION SYSTEM

Gulfstream Aerospace Corp...

1. An arrangement for use with a propulsion system for a supersonic aircraft, the arrangement comprising:a center body configured for coupling to an inlet and to support a boundary layer formed when the supersonic aircraft is flown at a predetermined altitude and a predetermined speed greater than Mach 1;
a first vortex generator disposed on the center body, the first vortex generator extending a first height above the center body; and
a second vortex generator disposed on the center body, said second vortex generator extending a second height above the center body, the second height being greater than the first height,
wherein said first height and said second height are greater than approximately seventy-five percent of a thickness of the boundary layer proximate a location of the first vortex generator and the second vortex generator, respectively, when the aircraft is flown at the predetermined altitude and the predetermined speed.

US Pat. No. 10,974,806

UNIFIED CANOPIES FOR AIRCRAFT

Gulfstream Aerospace Corp...

1. An aircraft component, comprising:an outer skin portion having an interior side and an exterior side configured to define an exterior boundary of an aircraft;
a plurality of major stiffeners unified with the outer skin portion and extending out from the interior side, wherein the plurality of major stiffeners are configured to resist deflection of the aircraft component in response to a bird strike on the aircraft component;
a plurality of minor stiffeners disposed between the plurality of major stiffeners, unified with the outer skin portion, and extending out from the interior side, wherein the plurality of minor stiffeners are configured to resist perforation of the aircraft component in response to the bird strike on the aircraft component; and
a crown frame unified with the outer skin portion and disposed around a periphery of the aircraft component extending out from the interior side, and
wherein the plurality of major stiffeners extend across the interior side from a first portion of the crown frame to a second portion of the crown frame.

US Pat. No. 10,967,986

POTENTIAL AIRCRAFT TRAJECTORY WIND EFFECT COMPUTATION

Gulfstream Aerospace Corp...

1. An avionics system for an aircraft, the avionics system comprising:a storage device for storing instructions for monitoring an actual performance of the aircraft; and
one or more data processors configured to execute the instructions to:
generate a lateral component and a longitudinal component of a measured moving air mass relative to the aircraft;
generate a plurality of wind independent positions of the aircraft along a potential aircraft trajectory based on a prediction model; and
generate a plurality of wind corrected positions of the aircraft based on the plurality of wind independent positions, on the lateral component, and on the longitudinal component;
generate a longitudinal position offset based on the longitudinal component and a lateral position offset based on the lateral component according to:
WindLat=dt*WindKnots*Math.Cos(WindHeading*0.0174533)/(3600*60), where Dt is the time interval, WindKnots is a speed of the moving air mass in knots, and WindHeading is a direction of the moving air mass in degrees;
generate the lateral position offset and the longitudinal position offset further based on a time interval of calculations used for the prediction model;
offset each of the plurality of wind independent positions to generate a corresponding wind corrected position of the plurality of wind corrected positions at each time interval used in the prediction model;
generate a next consecutive position of the plurality of wind independent positions based on a current wind corrected position of the plurality of wind corrected positions at each time interval.

US Pat. No. 10,930,164

AIRCRAFT FLIGHT ENVELOPE PROTECTION AND RECOVERY AUTOPILOT

Gulfstream Aerospace Corp...

1. A vehicle system for a vehicle, the vehicle system comprising:a storage device for storing instructions for converting between airspeed types; and
one or more data processors configured to execute the instructions to:
select a potential vehicle path relative to a current vehicle movement condition;
estimate a modeled movement condition of the vehicle along the potential vehicle path, wherein estimating the modeled movement condition includes:
calculating an energy state of the vehicle on the potential vehicle path; and
estimating a speed of the vehicle on the potential vehicle path based at least in part on the energy state; and
determine whether the modeled movement condition violates a vehicle limit.

US Pat. No. 10,919,640

CONVERSION BETWEEN CALIBRATED AIRSPEED AND TRUE AIRSPEED IN TRAJECTORY MODELING

Gulfstream Aerospace Corp...

1. An avionics system for an aircraft, the avionics system comprising:a storage device for storing instructions for converting between airspeed types; and
one or more data processors configured to execute the instructions to:
generate a calibrated airspeed of the aircraft;
convert the calibrated airspeed to an actual true airspeed of the aircraft;
determine an initial approximate relationship between the calibrated airspeed and a computed true airspeed as a function of a pressure altitude of the aircraft;
generate an adjusted approximate relationship based on the actual true airspeed and the initial approximate relationship at a chosen pressure altitude; and
estimate a future airspeed of the aircraft based on the adjusted approximate relationship and a future altitude.

US Pat. No. 10,902,748

MODULAR AIRCRAFT DISPLAY ARRANGEMENT AND METHOD FOR ASSEMBLING THE SAME

Gulfstream Aerospace Corp...

1. A modular aircraft display arrangement comprising:a fuselage display structure comprising:
a tubular wall extending about a longitudinal axis, at least partially surrounding an interior display space, and having a first opening section formed through the tubular wall; and
a fuselage base portion that includes a first track section positioned transverse to the longitudinal axis adjacent to the first opening section, wherein the tubular wall extends generally upward from the fuselage base portion about the interior display space; and
a first removable display module comprising a first aircraft interior display and configured to be advanced substantially transverse to the longitudinal axis through the first opening section to a first display position to expose the first aircraft interior display within the interior display space, wherein the fuselage base portion is configured to support the first removable display module, and wherein the first track section operatively engages the first removable display module to facilitate advancing the first removable display module to the first display position.

US Pat. No. 10,889,380

SEAT MAZE ASSEMBLIES FOR AIRCRAFT

Gulfstream Aerospace Corp...

1. An aircraft interior, comprising:a floor;
a seat base fixed to the floor;
a seat frame selectively fixed to the seat base and including a frame rail circumscribing the seat base to define a bounding area in which the seat base may translate freely in longitudinal and lateral directions of the aircraft relative to the seat frame;
a seat body mounted on the seat frame and including an arm portion;
an obstacle separate from the seat base, separate from the seat frame, and proximate the arm portion of the seat body at an obstacle location; and
a seat maze configured to guide the seat frame around a clearance area within the bounding area to restrict free translation of the seat base to maintain a predetermined clearance between the arm portion and the obstacle, the seat maze comprising:
a guide plate fixed to the seat base and disposed at least partially in the bounding area at a fixed location relative to the obstacle;
a bearing block fixed to the frame rail opposing the guide plate and extending into the bounding area, the bearing block comprising:
an interior member disposed inside the frame rail;
an exterior member opposing the interior member across the frame rail; and
a fastener configured to compress the interior member and the exterior member and to mount the bearing block to the seat frame at varying locations on the frame rail, wherein the bearing block is fixed on the frame rail at a location that is based on the obstacle location,
 wherein the guide plate and the bearing block cooperate to define the clearance area.

US Pat. No. 10,874,822

AIRCRAFT SEAT ASSEMBLY INCLUDING A VIBRATION PRODUCING APPARATUS AND METHOD FOR FABRICATING THE SAME

Gulfstream Aerospace Corp...

1. An aircraft seat assembly for supporting a seat occupant, the aircraft seat assembly comprising:a seat structure;
a seat cushion supported by the seat structure; and
a vibration producing apparatus configured to produce vibrations, and wherein the vibration producing apparatus is disposed one of adjacent to and within the seat structure for transferring the vibrations to the seat occupant, wherein the seat structure includes a seat substructure that is configured to couple to a seat track, wherein the vibration producing apparatus is disposed within the seat substructure, and wherein the vibration producing apparatus is an audio speaker.

US Pat. No. 10,829,194

DRAINAGE SYSTEM FOR AN AIRCRAFT

Gulfstream Aerospace Corp...

1. A drainage system for an aircraft, the drainage system comprising:a drain tube defining an orifice; and
a cover movable between a first cover position and a second cover position, the cover configured to overlay the orifice when the cover is in the first cover position, the cover configured to expose the orifice when the cover is in the second cover position, wherein the cover is configured to cooperate with a freestream air flow for moving the cover from the first cover position to the second cover position.

US Pat. No. 10,703,484

AIRCRAFT SEAT ASSEMBLY INCLUDING A VIBRATION MITIGATING APPARATUS AND METHOD FOR FABRICATING THE SAME

Gulfstream Aerospace Corp...

1. An aircraft seat assembly for supporting a seat occupant, the aircraft seat assembly comprising:a seat structure;
a seat cushion supported by the seat structure; and
a vibration mitigating apparatus operatively coupled to the seat structure to one of reduce and prevent vibrations from transferring to the seat occupant, wherein the vibration mitigating apparatus is configured to one of actively cancel or reduce the vibrations by producing destructive interference vibrations that are out of phase with the vibrations, and wherein the aircraft seat assembly further comprises a controller that is in communication with the vibration mitigating apparatus and that is configured to receive an input signal and to generate a command signal in response to the input signal for instructing the vibration mitigating apparatus to produce the destructive interference vibrations.