US Pat. No. 9,187,184

SYSTEMS AND DEVICES FOR REMOTELY OPERATED UNMANNED AERIAL VEHICLE REPORT-SUPPRESSING LAUNCHER WITH PORTABLE RF TRANSPARENT LAUNCH TUBE

AEROVIRONMENT, INC., Mon...

1. An article comprising:
a sabot engaged with an unmanned aerial vehicle (UAV) within a launcher volume defined by an inner wall, the sabot dimensioned
to provide a pressure seal at the inner wall and tethered to the inner wall.

US Pat. No. 9,479,048

RESONANT ISOLATED ACTIVE POWER FACTOR CORRECTION (PFC) RECTIFIER

AEROVIRONMENT, INC., Sim...

1. A method of driving an isolated converter, comprising:
opening a first bi-directional switch on an input side of a transformer;
accepting current into a resonant capacitor connected across the first bi-directional switch to reduce voltage across the
first bi-directional switch (SW) in response to the opening of the first bi-directional switch;

reversing current out of the resonant capacitor; and
closing the first bi-directional switch as voltage across the first bi-directional switch crosses zero volts.

US Pat. No. 9,404,936

WATER RESISTANT AIRCRAFT PITOT DEVICE

AeroVironment Inc., Simi...

1. An aircraft that flies through a relative airflow, and that is characterized by a maximum standard angle of attack in a
standard steady-state flight condition, comprising:
a pitot device for use in the airflow, including
a pitot housing forming a cavity having a housing external orifice,
an air-permeable fabric extending across a section of the cavity and defining a barrel and an internal chamber, and
a pressure sensor configured to sense information regarding the pressure within the internal chamber,
wherein the pitot device barrel is at a level orientation or lower when the aircraft is flying at the maximum standard angle
of attack.

US Pat. No. 9,421,875

ELECTRIC VEHICLE SUPPLY EQUIPMENT WITH TEMPERATURE CONTROLLED CURRENT

AeroVironment, Inc., Sim...

1. An electric vehicle supply equipment (EVSE) system for charging an electric vehicle, comprising:
a utility connector for receiving electrical power and containing a first pair of power conductors;
a docking connector containing a second pair of power conductors, said docking connector being engagable with a charging port
of an electric vehicle;

a pair of contactors providing an interruptable connection between said first and second pairs of power conductors;
a microprocessor and a memory coupled to said microprocessor, said pair of contactors being controlled by said microprocessor;
a control pilot conductor extending through said docking connector;
a pulse generator coupled to said control pilot conductor and having a pulse duty cycle controlled by said microprocessor;
a temperature sensor having an output representative of a present temperature, said output coupled to said microprocessor;
said memory containing: (a) a nominal pulse duty cycle corresponding to a nominal value of maximum allowable current, (b)
a predetermined threshold temperature, and (c) set of program instructions executable by said microprocessor whenever said
present temperature exceeds said predetermined threshold temperature to reduce the pulse duty cycle of said pulse generator
from said nominal pulse duty cycle to an adjusted pulse duty cycle by a reduction factor that is a function of an increase
of said present temperature above said predetermined threshold temperature.

US Pat. No. 9,750,161

HEAT TRANSFER SYSTEM FOR AIRCRAFT STRUCTURES

AeroVironment, Inc., Mon...

1. A heat transfer system comprising:
an aircraft panel comprising:
an upper skin;
a lower skin; and
a foam core disposed between the upper skin and the lower skin;
at least one heat conducting array extending through the foam core and between the upper skin and the lower skin, the at least
one heat conducting array defining at least one upper cap in contact with the upper skin, at least one lower cap, and a wall
portion extending between the at least one upper cap and the at least one lower cap, the at least one upper cap being disposed
proximate avionics; and

a heat conducting spreader disposed between the at least one lower cap of the at least one heat conducting array and the lower
skin of the aircraft panel,

where the heat conducting array is configured to dissipate heat from the avionics by transferring heat from the at least one
upper cap, through the wall portion, to the at least one lower cap, and to the heat conducting spreader, through the lower
skin.

US Pat. No. 9,496,750

STORED ENERGY AND CHARGING APPLIANCE

AEROVIRONMENT, INC., Mon...

1. A device comprising:
an electrical input configured to detachably connect to a power source;
an electrical output module configured to charge and detachably connect to an electric vehicle (EV);
an energy store mounted on a service vehicle, said energy store configured to detachably connect to the EV and store power
provided by the power source; and

wherein the energy store is configured to store energy supplied from the electrical input having a first power level and the
electrical output module is configured to, via the energy store, supply power to the EV at a second power level, wherein the
second power level is greater than the first power level.

US Pat. No. 9,476,251

WATER-TIGHT COMPARTMENT WITH REMOVABLE HATCH AND TWO-SIDED GEL SEAL FOR MULTIPLE CONDUIT ACCESS

AeroVironment, Inc., Mon...

1. An accessible sealable compartment in a body having an exterior body surface, and comprising:
a compartment interior and a compartment sealing surface adjacent a top edge of said compartment interior;
a hatch body having a hatch sealing surface congruent with and facing said compartment sealing surface;
wherein at least one of the hatch sealing surface and the compartment sealing surface having a congruent channel defined therein;
a hatch-to-compartment fastening structure;
a gasket between said compartment sealing surface and said hatch sealing surface and disposed in said congruent channel;
at least one elongate communication member having a portion lying between said compartment sealing surface and said hatch
sealing surface, said at least one elongate communication member extending into said compartment interior from a location
outside of said compartment interior via the congruent channel therethrough, said channel having a congruent wall conforming
to the at least one elongate communication member;

wherein said gasket comprising a first viscous gel gasket on said compartment sealing surface continuously around a periphery
of the compartment and a second viscous gel gasket on said hatch sealing surface continuously around a periphery of the hatch
and wherein said first and second viscous gel gaskets meet to form a watertight seal between the compartment sealing surface
and the hatch sealing surface; and

wherein at least one of the first or second viscous gel gaskets extends into the congruent wall in the channel.

US Pat. No. 9,309,006

UAV PAYLOAD MODULE CAMERA ASSEMBLY AND RETRACTION MECHANISM

AeroVironment, Inc., Sim...

1. A UAV payload module retraction mechanism apparatus comprising:
a) a payload module housing;
b) a payload pivotally attached to the housing;
c) a winch attached to the payload;
d) a biasing member mounted to bias the payload out of the housing; and
e) an elongated flexible drawing member coupled between the housing and the winch, the elongated flexible drawing member connected
to the winch such that the elongated flexible drawing member is drawn onto the winch for retracting the payload within the
housing and the elongated flexible drawing member is extended from the winch for releasing the payload from the housing.

US Pat. No. 9,267,440

POWERPLANT AND RELATED CONTROL SYSTEM AND METHOD

AeroVironment, Inc., Sim...

1. A powerplant, comprising:
an engine configured to react a first reactant with a gaseous stream of second reactant to produce energy and an exhaust stream,
the engine being configured for use in a range of ambient conditions, wherein the gaseous stream of second reactant is provided
to the engine at a flow rate;

a compressor configured to pressurize the gaseous stream of second reactant supplied to the engine;
a turbine, wherein the compressor is driven in rotation by a driving force from the turbine, and wherein the turbine is propelled
by the exhaust stream;

an afterburner in the exhaust stream intermediate the engine and the turbine, the afterburner being configured to react reactants
in the exhaust stream; and

a control system configured to restart the engine in at least some ambient conditions of the range of ambient conditions by
controlling the operation of the afterburner to add energy to the turbine such that the compressor is driven at a speed that
provides for the gaseous stream of second reactant to be provided to the engine at a flow rate at or above a threshold level.

US Pat. No. 9,156,362

PORTABLE CHARGING CABLE WITH IN-LINE CONTROLLER

AeroVironment, Inc., Mon...

1. An EVSE cord comprising:
plural insulated conductors and a flexible outer sheath enclosing said plural insulated conductors,
an EVSE docking connector on a docking end of the cord and a utility plug on a utility end of the cord,
said cord being divided into a docking section terminated at said docking connector and a utility section terminated at said
utility connector,

an in-line EVSE controller and a housing enclosing said controller, said housing sealed with said flexible outer sheath and
disposed at an intermediate section of said cord between said docking and utility sections;

a control pilot conductor in said docking section of said cord, wherein said in-line EVSE controller comprises:
a microprocessor comprising a serial port;
an analog buffer coupled between said microprocessor and said control pilot conductor;
a pulse generator coupled to said control pilot conductor and having a duty cycle controlled by said microprocessor; and
a temperature sensor having a temperature output coupled to said microprocessor, said temperature output representing a present
temperature.

US Pat. No. 9,308,825

ELECTRIC VEHICLE DOCKING CONNECTOR WITH EMBEDDED EVSE CONTROLLER

AeroVironment, Inc., Sim...

1. An electric vehicle supply equipment (EVSE) kit for charging an electric vehicle through a charging port of the electric
vehicle, comprising:
a docking connector comprising:
a head having a head end engagable with the charging port of the electric vehicle;
a barrel comprising a barrel docking end and a barrel cable end, said barrel docking end attached to said head;
a first plurality of conductors extending into said barrel from said barrel cable end and a second plurality of conductors
extending into said head from said head end;

an embedded EVSE controller inside said docking connector connected between said first and second pluralities of conductors;
and

wherein the EVSE controller is configured to:
monitor a sensed utility supply voltage;
determine whether the sensed utility voltage is closer to a first level or a second level;
establish an allowable voltage range based upon which level is determined for the sensed utility voltage;
set a maximum current limit in accordance with the allowable voltage range based upon a predetermined correlation;
adjust a control pilot pulse duty cycle to a level corresponding the maximum current limit;
monitor a current flow and the sensed utility voltage;
generate a fault alarm and trouble code if the current flow is above the maximum current limit; and
generate a fault alarm and trouble code if the sensed voltage utility voltage deviates outside the allowable range.

US Pat. No. 9,211,947

UNMANNED AERIAL VEHICLE ANGULAR REORIENTATION

AEROVIRONMENT, INC., Sim...

1. An unmanned aerial vehicle (UAV) comprising:
a processor having addressable memory, the processor configured to:
determine a body roll angle error based on a target location in a body reference frame and an orientation of the UAV in the
body reference frame; and

determine one or more aileron actuator commands based on the determined body roll angle error;
wherein the processor of the UAV is further configured to bank-to-turn, and to transition to reorient in attitude based on
an estimated range-to-go and an angular position of the target relative to the UAV.

US Pat. No. 9,156,551

TILT-BALL TURRET WITH GIMBAL LOCK AVOIDANCE

AeroVironment, Inc., Mon...

1. A turret assembly for attachment on the undersurface of an aircraft, the assembly comprising:
a roll actuator including a drive shaft;
a yoke having a cross member coupled to the drive shaft and a pair of prongs, the yoke being rotated via the roll actuator
and drive shaft along a roll axis oriented substantially parallel to the body of the aircraft;

a turret mounted on the prongs of the yoke;
a tilt actuator within the turret, the tilt actuator tilting the turret on a tilt axis relative to the yoke, the tilt axis
being perpendicular to the roll axis;

a fairing containing the roll actuator, the fairing coupled to the undersurface of the aircraft behind the turret; anda wiring harness for delivery of electrical signals between the turret and the fairing, the wiring harness including one or
more wires having a first portion that extends through the drive shaft and a second portion that is mounted exteriorly of
a first prong of the yoke, between the first prong and the turret.

US Pat. No. 9,084,276

DYNAMIC TRANSMISSION CONTROL FOR A WIRELESS NETWORK

AeroVironment, Inc., Mon...

13. A method for communicating on a wireless network having a plurality of nodes, the method comprising:
selecting a node to function as a dynamic arbiter for dynamically controlling communication of at least one non-arbiter node
of the plurality of nodes on the wireless network, wherein selecting a node comprises selecting an unmanned aerial vehicle
as the arbiter such that the unmanned aerial vehicle dynamically controls an operation of the at least one non-arbiter nodes
by defining communications operation cycles and allocating a bandwidth to the at least one non-arbiter nodes on a cycle by
cycle basis in response to requests for bandwidth from the at least one non-arbiter nodes, and by varying the operation cycles
based on the requests for bandwidth from the at least one non-arbiter nodes, and by defining the duration of an operation
cycle by varying the frame length in response to requests for bandwidth from the at least one non-arbiter nodes and by beginning
a new frame if a non-arbiter node does not need an entire slot;

receiving at the unmanned aerial vehicle requests for a desired bandwidth from the at least one non-arbiter node;
adjusting dynamically the bandwidth allocated to the at least one non-arbiter node based on the requests, comprising using
the unmanned aerial vehicle to define operation cycles and assign a transmission start time and duration for each cycle to
the at least one non-arbiter node;

wherein using the unmanned aerial vehicle to define further comprises defining a duration of an operation cycle by varying
a frame length in response to requests for bandwidth from the at least one client nodes and to begin a new frame if a client
node does not need an entire slot; and

wherein selecting a node to function as an arbiter comprises powering up the unmanned aerial vehicle and monitoring for an
existing DDL session and assuming the role of arbiter if no DDL session is in progress.

US Pat. No. 9,267,974

CONTACTOR HEALTH MONITOR CIRCUIT AND METHOD

AeroVironment, Inc., Sim...

1. A method for determining contactor health, the method comprising:
a) measuring a differential voltage between a first utility line voltage and a second utility line voltage on a primary side
of a contactor and on a secondary side of the contactor;

b) wherein the measuring is performed with both an unloaded current and with a load current;
c) wherein both the unloaded and loaded measurements at the primary side and the secondary side are made with the contactor
closed;

d) determining a difference between a secondary unloaded voltage and a secondary loaded voltage and subtracting a difference
between a primary unloaded voltage and a primary loaded voltage to provide a contactor voltage drop; and

e) determining the contactor resistance by dividing the contactor voltage drop by the loaded current.

US Pat. No. 9,120,555

ACTIVE DIHEDRAL CONTROL SYSTEM FOR A TORISIONALLY FLEXIBLE WING

AeroVironment Inc., Monr...

1. A flying wing aircraft, comprising:
a laterally extending wing having a spanwise axis;
wherein the wing has high torsional flexibility about the spanwise axis;
a plurality of independently actuatable control surfaces;
wherein the control surfaces are spaced apart along the span of the wing and connected thereto;
a plurality of sensors connected to the wing; and
a control system programmed to actively control the plurality of control surfaces based upon structural information data received
from the plurality of sensors;

wherein the control system independently actuates the control surfaces to alter local lift of wing portions at the location
of each control surface in order to alter the dihedral of the wing.

US Pat. No. 9,108,713

ELEVON CONTROL SYSTEM

AeroVironment, Inc., Mon...

1. An aerial vehicle comprising:
a fuselage, comprising a housing;
a first airfoil, rotatably attached to the fuselage housing, the first airfoil comprising a first control surface resiliently
mounted to the first airfoil, wherein the first control surface is articulated at a lineal joint about the first airfoil;
and

a first actuator horn, disposed in the fuselage housing, the first actuator horn extendible via a first fuselage housing aperture,
wherein the first actuator horn is extendible to oppose and contact the first control surface.

US Pat. No. 9,511,859

INVERTIBLE AIRCRAFT

AeroVironment, Inc., Sim...

1. A method of gathering intelligence prior to entering a room, comprising:
a) delivering a rotorcraft into the room, the rotorcraft including a fuselage defining a vertical dimension with respect to
the fuselage, one or more rotors generally oriented for vertical thrust with respect to the fuselage,

one or more motors attached to the one or more rotors such that they drive the one or more rotors in rotation, and
a control system that controls the speed and changeable direction with which the one or more motors drives the one or more
rotors in rotation,

b) controlling the direction of rotor rotation based on the orientation of the rotorcraft with respect to gravity once the
rotorcraft has come to rest in the room;

c) instructing the rotorcraft to fly; and
d) scanning the room using a sensor on the rotorcraft to gather intelligence.

US Pat. No. 9,203,783

ACTIVE MULTI-PATH NETWORK REDUNDANCY WITH PERFORMANCE MONITORING

AEROVIRONMENT, INC., Mon...

1. A method of redundant message processing, comprising:
assigning, by a processor of an originator node:
a frame sequence number to a frame of a first packet of a dual redundant set;
an originator identification number to the frame of the first packet of the dual redundant set;
the frame sequence number to a frame of a second packet of the dual redundant set; and
the originator identification number to the frame of the second packet of the dual redundant set;
tagging, by a first routing switch, the first packet of the dual redundant set as a first virtual local area network (VLAN);
tagging, by a second routing switch, the second packet of the dual redundant set as a second VLAN;
recording, by a processor of a destination node:
the frame sequence number and originator number of a first received packet of the dual redundant set comprising the first
packet and the second packet;

dropping, by the processor of the destination node:
a second received packet of the dual redundant set having the recorded frame sequence number and the recorded originator number.

US Pat. No. 9,199,733

INVERTIBLE AIRCRAFT

AeroVironment Inc., Monr...

1. A rotor for use with a motor with a shaft configured to drive the rotor in either of two opposite directions of rotation,
comprising:
one or more blades, each blade having a longitudinal blade axis;
an inversion mechanism configured to rotate each of the one or more blades around the longitudinal blade axis between a first
position oriented for efficient thrust in a first direction parallel to the two directions of motor rotation, and a second
position oriented for efficient thrust in a second direction parallel to the two directions of rotation of the motor, the
first and second directions of thrust being in opposite directions.

US Pat. No. 9,586,673

SYSTEM FOR ALIGNING A PROPELLER

AEROVIRONMENT, INC., Sim...

1. A method of securing a propeller, comprising:
commutating a sensor trigger by commutating a shaft of a motor, said motor having stators and rotors;
commutating a propeller indexer by commutating said shaft, said propeller indexer configured to align a propeller, when a
propeller is present, at an angular position that is a propeller offset angle ?PROP from said sensor trigger as referenced by a center of rotation of said shaft;

sensing said sensor trigger as said sensor trigger rotates to a point adjacent a sensor fixedly coupled to said motor; and
switching a control signal to rotatably hold said rotors driving said rotatable shaft in response to said sensor sensing said
sensor trigger;

wherein said propeller indexer may be held in position at the propeller offset angle ?PROP from the sensor by commutating said shaft and holding the rotors so that the sensor is proximate to the sensor trigger; and

wherein said propeller propels an aircraft having an aircraft wing, and wherein said sensing said sensor trigger step further
comprises sensing said sensor trigger as said propeller aligns with the aircraft wing.

US Pat. No. 9,470,477

LAUNCH TUBE RESTRAINT SYSTEM FOR UNMANNED AERIAL VEHICLE (UAV)

AEROVIRONMENT, INC., Sim...

1. An unmanned aerial launch vehicle (UAV) launch apparatus, comprising:
a UAV having an exterior surface;
an aerial vehicle (AV) tab extending from the exterior surface; and
a tube containing the UAV, the tube comprising:
a tab stop configured to hinder travel of the AV tab past the tab stop; and
a tab guide configured to position the AV tab for travel over the tab stop.

US Pat. No. 9,404,750

HIGH ALTITUDE, LONG ENDURANCE, UNMANNED AIRCRAFT AND METHODS OF OPERATION THEREOF

AEROVIRONMENT, INC., Mon...

1. A method of satellite sensor interdiction, comprising:
deploying a first high altitude, long endurance (HALE) unmanned aircraft comprising a satellite tracker and a directable electromagnetic
(EM) radiation emitter in cooperation with the satellite tracker;

acquiring, by the satellite tracker, a satellite having an onboard EM sensor;
tracking, by the satellite tracker, the acquired satellite;
emitting interdicting EM radiation, by the directable EM radiation emitter, to the tracked satellite;
prior to the step of emitting by the first HALE unmanned aircraft, deploying a second HALE unmanned aircraft comprising a
satellite tracker;

signaling by the first HALE unmanned aircraft to the second HALE unmanned aircraft, the location of the tracked satellite;
acquiring, by the satellite tracker of the second HALE unmanned aircraft, the satellite tracked by the first HALE unmanned
aircraft; and

tracking, by the satellite tracker of the second HALE unmanned aircraft, the satellite tracked by the first HALE unmanned
aircraft.

US Pat. No. 9,090,335

UNMANNED AERIAL VEHICLE DRAG AUGMENTATION BY REVERSE PROPELLER ROTATION

AeroVironment, Inc., Mon...

1. An air vehicle comprising:
at least one propeller, each propeller comprising at least one blade having a constant pitch angle;
at least one propeller motor configured to reverse propeller direction of rotation of the at least one propeller while the
air vehicle is in flight; and

an autopilot configured to maintain airspeed of the air vehicle above stall conditions using the propeller motor while the
air vehicle is in flight.

US Pat. No. 9,067,287

METHOD OF MANUFACTURING A HEAT TRANSFER SYSTEM FOR AIRCRAFT STRUCTURES

AEROVIRONMENT, INC., Mon...

11. A method of manufacturing a heat transfer system comprising:
preparing a heat conducting array by perforating at least a portion of the heat conducting array;
placing the heat conducting array around foam elements;
placing a lower skin over one surface area of the foam elements;
placing an upper skin over an opposite surface area of the foam elements to create a structural assembly; and
forming the structural assembly under heat and pressure,
wherein a material of the foam elements extends through the perforated portion of the heat conducting array during the forming
step.

US Pat. No. 9,511,858

INVERTED-LANDING AIRCRAFT

AeroVironment, Inc., Sim...

1. An unmanned aircraft system, comprising:
an aircraft including a wing having an upper surface and a lower surface defining an upright orientation for normal aircraft
flight and an inverted orientation for inverted flight, the upper surface being gravitationally above the lower surface while
in the upright orientation, and the lower surface being gravitationally above the upper surface while in the inverted orientation;

a remote-control station;
a remote-control control system configured for a user to remotely control the flight of the aircraft using the remote-control
station;

a first camera oriented to view downward and forward while the aircraft is in the upright orientation; and
a second camera oriented to view downward and forward while the aircraft is in the inverted orientation;
wherein the remote-control station is provided with an auto-land function that instructs the control system to operate the
control surfaces such that the aircraft conducts an inverting maneuver in which the aircraft rotates from the upright orientation
to the inverted orientation; and

wherein the control system is configured to relay images from the first camera to the remote-control station while the aircraft
is in the upright orientation, and to relay images from the second camera to the remote-control station while the aircraft
is in the inverted orientation, and wherein the remote-control station is configured to display the relayed images from the
first camera to the user during flight in the upright orientation, and is further configured to display the relayed images
from the second camera to the user during flight in the inverted orientation.

US Pat. No. 9,365,124

EVSE KIT INCLUDING A PORTABLE CHARGING CABLE, AN IN-LINE EVSE CONTROLLER AND AN INTERFACE TOOL

AEROVIRONMENT, INC., Sim...

1. An EVSE kit, comprising:
(A) an EVSE cord, comprising:
(1) an EVSE docking connector on a docking end of the cord and a utility plug on a utility end of the cord, said docking connector
containing a control pilot conductor,

(2) an in-line EVSE controller and a housing enclosing said controller, said controller comprising a microprocessor having
a serial port, said serial port coupled to said control pilot conductor;

(B) an interface tool, comprising:
(1) a tool enclosure,
(2) an EV connector mounted on said tool enclosure, said EV connector adapted to receive said EVSE docking connector and comprising
a conductor pin that is connected to said control pilot conductor whenever said EV connector of said tool enclosure is mated
with said EVSE docking connector of said EVSE cord,

(3) a serial port connector mounted on said tool enclosure and adapted to receive a serial port connector from an external
digital device, said interface tool further comprising a serial data path between said conductor pin and said serial port
connector of said tool enclosure.

US Pat. No. 9,080,903

WATER RESISTANT AIRCRAFT PITOT DEVICE

AeroVironment Inc., Monr...

1. A pitot device for use in an airflow, comprising:
a pitot housing forming a cavity having a housing external orifice characterized by a housing external-orifice height;
an air-permeable fabric extending across a section of the cavity and defining an internal chamber; and
a pressure sensor configured to sense information regarding the pressure within the internal chamber;
wherein the distance within the cavity between the air-permeable fabric and the housing external orifice is less than 2.4
times the housing external-orifice height.

US Pat. No. 9,059,485

REACTIVE REPLENISHABLE DEVICE MANAGEMENT

AEROVIRONMENT, INC., Mon...

1. A method for dynamic control of one or more devices based on device measurement data received from the one or more devices,
the method comprising:
receiving device measurement data from:
a replenishable device,
a replenisher associated with the replenishable device, and
a vehicle associated with the replenishable device, the device measurement data including (a) identification data, (b) historical
data, and (c) real-time data for each of the replenishable device, the replenisher, and the vehicle;

updating a usage profile associated with vehicle energy usage using the device measurement data received from the replenishable
device, the replenisher, and the vehicle, the usage profile comprising performance data of both the replenishable device and
the vehicle gathered over a period of time; and

analyzing the usage profile to determine whether vehicle energy usage is sub-optimal, wherein when it is determined that vehicle
energy usage is sub-optimal, an automatic controller of a remote device manager which is remote from and operationally coupled
to the vehicle automatically controls a performance level of the vehicle.

US Pat. No. 9,208,689

DEEP STALL AIRCRAFT LANDING

AeroVironment Inc., Monr...

1. A method of rapidly descending an aircraft to land at a landing location, the aircraft having a wing including an upper
surface and a lower surface defining an upright orientation for normal aircraft flight, and an inverted orientation for inverted
flight, the upper surface being gravitationally above the lower surface while in the upright orientation, and the lower surface
being gravitationally above the upper surface while in the inverted orientation, comprising:
(a) controlling the operation of one or more control surfaces to approach the landing location while the aircraft is flying
in the upright orientation;

(b) controlling the operation of the one or more control surfaces to invert the aircraft such that it is controllably moving
in an inverted orientation;

(c) controlling the operation of the one or more control surfaces to at least partially stall the wing while in the inverted
orientation to provide for the aircraft to rapidly descend; and

(d) estimating the altitude of the aircraft by (1) estimating the rate of descent, (2) monitoring an image of the ground,
and (3) calculating an estimated altitude using a rate of change of the monitored ground image and the estimated rate of descent.

US Pat. No. 9,756,764

THERMAL MANAGEMENT SYSTEM FOR AN AIRCRAFT AVIONICS BAY

AeroVironment, Inc., Mon...

1. A system for managing heat transfer comprising:
a cavity having an inner wall portion;
at least one heat-generating component disposed within the cavity; and
a plurality of heat conducting members disposed adjacent one another, each heat conducting member comprising:
a resilient core; and
an outer shell wrapped around at least a portion of the resilient core, the outer shell comprising a material having a relatively
high thermal conductivity,

wherein the plurality of heat conducting members are positioned between the heat-generating component and the inner wall portion
of the cavity;

a structural member disposed proximate the inner wall portion of the cavity and comprising:
an upper skin;
a lower skin; and
a foam core disposed between the upper skin and the lower skin;
at least one heat conducting array extending through the foam core and between the upper skin and the lower skin, the heat
conducting array defining at least one upper cap, at least one lower cap, and a wall portion extending between the upper cap
and the lower cap, the upper cap being disposed proximate a heat source; and

a heat conducting spreader disposed between the lower cap of the heat conducting array and the lower skin of the structural
member,

wherein the heat conducting array dissipates heat from the heat-generating component by transferring heat from the at least
one upper cap, through the wall portion, to the at least one lower cap, to the heat conducting spreader, through the lower
skin, and out to an atmosphere.

US Pat. No. 9,597,976

INTEGRATED BATTERY UNIT WITH COOLING AND PROTECTION EXPEDIENTS FOR ELECTRIC VEHICLES

AEROVIRONMENT, INC., Mon...

1. An integrated battery unit (IBU) for coupling a battery pack to an electric battery charger, the battery pack having one
or more battery cells for providing power to the electric vehicle by way of a motor controller coupled to the IBU through
controller connection cables, the IBU comprising:
battery connection cables electrically connecting the IBU to the battery pack;
a housing for attachment to the battery pack and accommodation in a battery compartment in the electric vehicle in which the
battery pack is removably disposed;

a connector for removably coupling the controller connection cables to the IBU; and
a disconnector disposed in the housing and including a charging receptacle in communication with the exterior of the housing,
the charging receptacle electrically connected to the battery connection cables and operable to electrically isolate the vehicle
motor controller from the battery charger when the battery charger is mated to the charging receptacle for fast charging the
battery pack.

US Pat. No. 9,288,513

SYSTEM AND METHOD OF HIGH-RESOLUTION DIGITAL DATA IMAGE TRANSMISSION

AeroVironment, Inc., Mon...

1. A system for transmitting still images and a video feed to a remote location, the system comprising:
an aircraft including a digital video camera to capture still images and video frames of an object;
a video encoder coupled to the camera to provide a video output including video packets;
a file server coupled to the camera to provide a still image output including image data packets;
a multiplexer coupled to the video output and the still image output, the multiplexer producing a data transmission including
the video packets and the image data packets; and

a transmitter to send the data transmission to the remote location;wherein the still image is one of a plurality of still images captured by the camera, the image data packets including an
identifier field identifying the still image associated with the image data packet.

US Pat. No. 9,650,133

POWER AND COMMUNICATION INTERFACE FOR VERTICAL TAKE-OFF AND LANDING (VTOL) UNMANNED AERIAL VEHICLES (UAVS)

AEROVIRONMENT, INC., Sim...

1. A vertical take-off and landing (VTOL) unmanned aerial vehicle (UAV) system comprising:
a rearward facing tang extending from a rear fuselage portion of a VTOL UAV;
one or more metallic contacts disposed on an exterior surface of the tang;
a UAV pod comprising a landing surface; and
an opening disposed in the landing surface to receive the tang.

US Pat. No. 9,748,809

STATOR WINDING HEAT SINK CONFIGURATION

AeroVironment, Inc., Mon...

1. A motor comprising:
a) a rotor; and
b) a stator comprising:
i) front cooling fins thermally coupled to a front of the stator;
ii) rear cooling fins thermally coupled to a rear portion of the stator;
iii) a winding between the front and rear cooling fins;
iv) a front stator yoke mounted onto a front distal end of the winding, the front cooling fins being mounted to the front
stator yoke; and

v) wherein the stator comprises a generally circular configuration disposed about a central axis defining the generally circular
configuration, and wherein the front of the stator is spaced apart from the rear portion of the stator along the central axis.

US Pat. No. 9,669,947

SMALL UNMANNED AERIAL VEHICLE (SUAV) SHIPBOARD RECOVERY SYSTEM

AEROVIRONMENT, INC., Sim...

1. A method comprising:
impacting, by a small unmanned aerial vehicle (SUAV), a net having at least three sides; and
converting the kinetic energy of the SUAV into at least one of: elastic potential energy of one or more tensioned elastic
cords connected to the net, gravitational potential energy of a frame member connected to the net, rotational kinetic energy
of the frame member connected to the net, and elastic potential energy of the frame member connected to the net;

wherein the frame member is a boom, wherein the boom is connected to a gooseneck connector having a vertical hinge and a horizontal
hinge, and wherein the net is connected to a mast at a position distal from a portion of the mast connected to the gooseneck
connector.

US Pat. No. 9,561,764

REMOTE DEVICE CONTROL AND POWER SUPPLY

AeroVironment, Inc., Mon...

1. A system for supplying power to a remote auxiliary load located in an aircraft,
a power plant configured to place a high voltage onto a high gage wire;
an actuator interface controller comprising a power supply, the power supply being interconnected with the high gage wire
and a low gage wire, the high gage wire being of higher gage wiring than the low gage wire, where the high gage wire acts
as a high voltage power bus and provides the high voltage to the power supply;

the power supply being configured to step down the high voltage received to a first low voltage that is lower than the high
voltage on the high voltage power bus, and to place the first low voltage onto the low gage wire that acts as a low voltage
power bus;

the low voltage power bus is interconnected with a remote auxiliary load and provides the first low voltage to the remote
auxiliary load;

a local processor located in the actuator interface controller, the local processor being interconnected with a control network
via an optic fiber interface;

where the actuator interface controller is electrically interchangeable with other actuator interface controllers, and the
local processor of the actuator interface controller includes mission specific software that facilitates control of the remote
auxiliary load, such that depending on a particular mission, one actuator interface controller with a first mission specific
software may be physically replaced by a second actuator interface controller with a second mission specific software; and

where the power supply is configured to provide a second low voltage to the local processor.

US Pat. No. 9,365,088

UAV HAVING HERMETICALLY SEALED MODULARIZED COMPARTMENTS AND FLUID DRAIN PORTS

AeroVironment, Inc., Sim...

1. An amphibious unmanned aerial vehicle comprising:
a) a fuselage constructed of a buoyant material;
b) separators within the fuselage forming separate battery, payload, and avionics compartments within the fuselage, the compartments
comprising;

(1) the battery compartment comprising a drainage channel comprising at least one weep hole through the fuselage;
(2) the payload compartment comprising an open bottom; and
(3) the avionics compartment comprising a drainage channel comprising at least one weep hole through the fuselage; and
c) mounting surfaces within the battery, payload, and avionics compartments for mounting a battery module, a payload module,
and an avionics module within the fuselage.

US Pat. No. 9,112,377

REMOTE DEVICE CONTROL AND POWER SUPPLY

AEROVIRONMENT, INC., Mon...

1. A system for supplying power to a remote auxiliary load located in an aircraft,
a power plant configured to place a high voltage onto a high gage wire;
an actuator interface controller comprising a power supply, the power supply being interconnected with the high gage wire
and a low gage wire, the high gage wire being of higher gage wiring than the low gage wire, where the high gage wire acts
as a high voltage power bus and provides the high voltage to the power supply;

the power supply being configured to step down the high voltage received to a low voltage that is lower than the high voltage
on the high voltage power bus, and to place the low voltage onto the low gage wire that acts as a low voltage power bus;

the low voltage power bus is interconnected with a remote auxiliary load and provides the low voltage to the remote auxiliary
load; and

a local processor located in the actuator interface controller, the local processor being interconnected with a control network
via an optic fiber interface;

where the actuator interface controller is electrically interchangeable with other actuator interface controllers, and the
local processor of the actuator interface controller includes mission specific software that facilitates control of the remote
auxiliary load, such that depending on a particular mission, one actuator interface controller with a first mission specific
software may be physically replaced by a second actuator interface controller with a second mission specific software.

US Pat. No. 9,075,289

ROLL-TILT BALL TURRET CAMERA HAVING COILED DATA TRANSMISSION CABLE

AeroVironment, Inc., Mon...

1. A ball turret assembly for supporting a camera, comprising:
a first shaft rotatable about a first axis relative to a first fixed point, the first shaft having an axially-extending interior
region in communication with an exterior of the first shaft by way of a first exit port;

a cable extending along the interior region of the first shaft and exiting the first shaft at the first exit port, the cable
looping at least partially around the first shaft and affixed at the first fixed point, the cable loop contracting or expanding
with rotation of the first shaft and

a first guide for conforming and guiding the cable loop during said contracting or expanding, the first guide disposed at
least partially circumferentially on the first shaft proximally to the first exit port.

US Pat. No. 9,735,980

FAULT-TOLERANT, FRAME-BASED COMMUNICATION SYSTEM

AEROVIRONMENT, INC., Mon...

1. A system comprising:
a source node;
a first routing switch configured to output, via at least one port, a frame received from the source node and tagged with
a first virtual local area network (VLAN) designator, said first routing switch having a first table for directed port routing,
wherein said first routing switch is configured to exclude from output a received frame having a second VLAN designator;

a second routing switch configured to output, via at least one port, a frame received from the source node and tagged with
the second VLAN designator wherein said second routing switch is configured to exclude from output a received frame having
the first VLAN designator; and

a first destination node in communication with the first and second routing switches.

US Pat. No. 9,557,362

METHOD AND MEANS FOR CONTACTOR MONITORING IN ELECTRIC VEHICLE SUPPLY EQUIPMENT

AeroVironment, Inc., Mon...

1. A method for contactor monitoring and control in electric vehicle supply equipment, the method comprising:
a) updating contactor error counts based on a detected condition of a contactor comprising:
i) updating an open error count; and
ii) updating a close error count;
b) determining a detected state of the contactor by comparing the open error count and the close error count to maximum and
minimum values; and

c) performing at least one of: (i) controlling the state of the contactor based on the determined contactor state; or (ii)
providing a visual indicator based on the determined contactor state.

US Pat. No. 9,533,599

PORTABLE CHARGING CABLE WITH IN-LINE CONTROLLER

AeroVironment, Inc., Mon...

1. An EVSE cord comprising:
plural insulated conductors and a flexible outer sheath enclosing said plural insulated conductors,
an EVSE docking connector on a docking end of the cord and a utility plug on a utility end of the cord,
an in-line EVSE controller coupled between said docking and utility ends;
a control pilot conductor in said docking connector, wherein said in-line EVSE controller comprises:
a microprocessor comprising a serial port;
an analog buffer coupled between said microprocessor and said control pilot conductor;
a pulse generator coupled to said control pilot conductor and having a duty cycle controlled by said microprocessor; and
a temperature sensor having a temperature output coupled to said microprocessor, said temperature output representing a present
temperature.

US Pat. No. 9,270,154

FLUX CONCENTRATOR FOR IRONLESS MOTORS

AeroVironment, Inc., Mon...

1. A magnet array for a motor comprising a first array of permanent magnets being arranged such that flux from the permanent
magnets substantially cancels on an opposite side of the first array, the array further comprising flux concentrators located
at poles on a reinforcing side of the first array, wherein the first array is positioned opposite a second array of permanent
magnets with an ironless winding therebetween, the ironless winding being a winding without an iron core associated therewith,
the second array comprising flux concentrators located at poles on a reinforcing side of the second array such that the flux
from the permanent magnets of the first and second arrays concentrates through respective flux concentrators before extending
and mutually reinforcing across the winding, the second array being arranged such that the flux from the permanent magnets
of the second array substantially cancels on a side of the second array opposite the winding, wherein each of the flux concentrators
on the reinforcing side of the first array and each of the flux concentrators on the reinforcing side of the second array
have substantially a same width along their thicknesses as a respective permanent magnet pole therebehind, and wherein the
ironless winding comprises conductor bundles comprising a generally rectangular cross-section arranged such that a long side
of the generally rectangular cross-section is transverse to a direction of magnetic field lines between the flux concentrators
of first and second arrays.

US Pat. No. 9,112,785

FAULT-TOLERANT, FRAME-BASED COMMUNICATION SYSTEM

AEROVIRONMENT, INC., Mon...

1. A system comprising:
a source node;
a first routing switch of four or more routing switches configured to output, via at least one port, a frame received from
the source node and tagged with a first virtual local area network (VLAN) designator, said first routing switch having a first
table for directed port routing, wherein said first routing switch is configured to exclude from output a received frame having
a second VLAN designator;

a second routing switch of the four or more routing switches configured to output, via at least one port, a frame received
from the source node and tagged with the second VLAN designator, said second routing switch having a second table for directed
port routing, wherein said second routing switch is configured to exclude from output a received frame having the first VLAN
designator; and

a first destination node of two or more destination nodes configured to receive at least one of: the frame output by the first
routing switch and the frame output by the second routing switch.

US Pat. No. 9,672,748

DEEP STALL AIRCRAFT LANDING

AeroVironment, Inc., Sim...

1. A method of rapidly descending an aircraft to land at a landing location, the aircraft having a wing including an upper
surface and a lower surface defining an upright orientation for normal aircraft flight, and an inverted orientation for inverted
flight, the upper surface being gravitationally above the lower surface while in the upright orientation, and the lower surface
being gravitationally above the upper surface while in the inverted orientation, comprising:
(a) controlling the operation of one or more control surfaces to approach the landing location while the aircraft is flying
in the upright orientation;

(b) controlling the operation of the one or more control surfaces to invert the aircraft such that it is controllably moving
in an inverted orientation;

(c) after step (b), controlling the operation of the one or more control surfaces to at least partially stall the wing while
in the inverted orientation to provide for the aircraft to rapidly descend; and

(d) during step (c), controlling a rate of the descent by controlling depth of the wing stall.

US Pat. No. 9,673,673

MOTOR AIR FLOW COOLING

AeroVironment, Inc., Mon...

1. An aircraft electric motor cooling system comprising:
a) an airflow path through a spinner comprising:
i) a first airflow path between an inner rotor and a stator;
ii) a second airflow path between an outer rotor and the stator; and
iii) a third airflow path along an outer surface of the outer rotor; and
b) rear cooling fins thermally coupled to a back end of the stator, wherein the rear cooling fins are sized so as to extend
into an air stream of an aircraft.

US Pat. No. 9,365,123

ELECTRIC VEHICLE SUPPLY EQUIPMENT WITH TEMPERATURE CONTROLLED CURRENT

AEROVIRONMENT, INC., Sim...

1. An electric vehicle supply equipment (EVSE) system for charging an electric vehicle, comprising:
a utility connector for receiving electrical power and containing a first pair of power conductors;
a docking connector containing a second pair of power conductors, said docking connector being engagable with a charging port
of an electric vehicle;

a pair of contactors providing an interruptible connection between said first and second pairs of power conductors;
a microprocessor and a memory coupled to said microprocessor, said pair of contactors being controlled by said microprocessor;
a control pilot conductor extending through said docking connector, said microprocessor being capable of controlling voltage
on said control pilot conductor;

a pulse generator coupled to said control pilot conductor and having a pulse duty cycle controlled by said microprocessor;
a temperature sensor having an output representative of a present temperature, said output coupled to said microprocessor;
said memory containing: (a) a nominal pulse duty cycle corresponding to a nominal value of maximum allowable current, (b)
a predetermined threshold temperature, and (c) set of program instructions executable by said microprocessor whenever said
present temperature exceeds said predetermined threshold temperature to reduce the pulse duty cycle of said pulse generator
from said nominal pulse duty cycle to an adjusted pulse duty cycle by a reduction factor that is a function of an increase
of said present temperature above said predetermined threshold temperature.

US Pat. No. 9,719,411

POWERPLANT AND RELATED CONTROL SYSTEM AND METHOD

AeroVironment, Inc., Sim...

1. A powerplant, comprising:
an engine configured to react a first reactant with a gaseous stream of second reactant to produce energy and an exhaust stream,
wherein the gaseous stream of second reactant is provided to the engine at a flow rate;

a compressor configured to pressurize the gaseous stream of second reactant supplied to the engine;
a turbine, wherein the compressor is driven in rotation by a driving force from the turbine, and wherein the turbine is propelled
by the exhaust stream; and

an electrical generator configured to be driven by energy extracted from the exhaust stream.

US Pat. No. 9,669,925

AIR VEHICLE FLIGHT MECHANISM AND CONTROL METHOD FOR NON-SINUSOIDAL WING FLAPPING

AEROVIRONMENT, INC., Mon...

1. A flapping wing driving apparatus, comprising:
at least one crank gear capstan rotatably coupled to a crank gear, the at least one crank gear capstan disposed radially offset
from a center of rotation of the crank gear;

a first wing capstan coupled to a first wing, the first wing capstan having a first variable-radius drive pulley portion;
and

a first drive linking member configured to drive the first wing capstan, the first drive linking member windably coupled between
the first variable-radius drive pulley portion and one of the at least one crank gear capstan;

wherein the first wing capstan is configured to non-constantly, angularly rotate responsive to a constant angular rotation
of the crank gear.

US Pat. No. 9,608,460

REMOTE RECHARGEABLE MONITORING SYSTEM AND METHOD

AEROVIRONMENT, INC., Mon...

1. A rechargeable battery system comprising:
a battery pack including one or more batteries, the battery pack further having integrated therewith, as a single physical
unit:

one or more sensors for sensing an operational parameter of the battery pack,
a wireless transmitter, and,
a battery monitor and identifier module coupled to at least one of the sensors and operable to provide operational information
of the battery pack, based on the sensed operational parameter, to the wireless transmitter;

a battery charger that is coupleable and decoupleable from the battery pack and operable to deliver power from a power source
to the battery pack when an electrical connection is established between the battery charger and the battery pack; and

a remote server coupleable to the battery charger through a network and including a first communication device configured
to receive the operational information delivered wirelessly by the wireless transmitter irrespective of the coupleable and
decoupleable state of the battery charger to the battery pack.

US Pat. No. 9,705,346

ELECTRIC VEHICLE CHARGING STATION WITH CABLE RETAINING ENCLOSURE

AeroVironment, Inc., Mon...

1. An enclosure for a charging station comprising a peripheral casing configured to retain a charging cable on an upward facing
surface of the peripheral casing between a first portion of the peripheral casing and a charging station mounting surface,
wherein the upward facing surface is continuously curved across the upward facing surface and configured such that the contiuously
curved upward facing surface has a substantially same radius of curvature as a longitudinal axis of a charging cable received
thereon.

US Pat. No. 9,705,377

MOTOR MOUNT AND DAMPER

AEROVIRONMENT, INC., Mon...

1. A system comprising:
a damper, the damper comprising:
six or more indentations on alternating sides of the damper, wherein each indentation is open to an outer circumferential
surface of the damper and extends over halfway through a width of the damper; and

six or more slots, each slot open to an undulating inner circumferential surface of the damper and extending through the width
of the damper; and

a motor mount, the motor mount comprising six or more tabs disposed about an aperture in a same plane extending parallel to
a front face of the motor mount;

wherein the six or more tabs of the motor mount are seated in the six or more indentations of the damper to self-encapsulate
the outer circumferential surface of the damper in the motor mount; and

wherein an air space remains in each of the six or more indentations after the six or more tabs are seated in the six or more
indentations of the damper for further compression of the damper against each of the six or more tabs.

US Pat. No. 9,340,302

AIRCRAFT GROUNDING SYSTEM

AeroVironment, Inc., Sim...

1. A system comprising:
an air vehicle configured to adhere with an adhesive to an external surface;
an adhesive anchoring assembly of the air vehicle configured to adhere, via the adhesive, to an air vehicle landing surface
external to the air vehicle; and

at least one cylinder of the adhesive anchoring assembly configured to rotate relative to the air vehicle, the at least one
cylinder comprising an attachment joint disposed on one end of the at least one cylinder proximate to the air vehicle and
a brush assembly disposed on a distal end of the at least one cylinder.

US Pat. No. 9,787,610

ACTIVE MULTI-PATH NETWORK REDUNDANCY WITH PERFORMANCE MONITORING

AEROVIRONMENT, INC., Mon...

1. A method of redundant message processing, comprising:
tagging, by a first routing switch, a first packet of a dual redundant set as a first virtual local area network (VLAN);
tagging, by a second routing switch, a second packet of the dual redundant set as a second VLAN; and
dropping, by a processor of a destination node:
a received packet of the dual redundant set having a frame sequence number associated with an originator identifier if the
frame sequence number of the received packet is less than or equal to a stored highest sequence number associated with the
originator identifier.

US Pat. No. 9,776,706

SYSTEM FOR PROTECTING A ROTATABLE SHAFT OF A MOTOR FROM EXCESSIVE BENDING MOMENTS

AEROVIRONMENT, INC., Sim...

1. A motor apparatus, comprising:
a motor having a motor casing;
a rotatable shaft extending from said motor casing to a shaft length; and
a rotatable hub coupled to said rotatable shaft, said rotatable hub having a circumferential skid surface disposed immediately
proximal to said motor casing and having a channel configured to seat a propeller;

wherein a bending moment applied to said shaft through said hub results in a bending of said shaft such that said circumferential
skid surface contacts said motor casing during at least a portion of a rotation of said rotatable shaft.

US Pat. No. 9,834,305

VERTICAL TAKEOFF AND LANDING (VTOL) AIR VEHICLE

AEROVIRONMENT, INC., Sim...

1. A flight control apparatus for a fixed-wing aircraft, comprising:
a first port wing and a first starboard wing;
a first port swash plate coupled between a first port rotor and a first port electric motor, the first port electric motor
coupled to the first port wing;

a first starboard swash plate coupled between a first starboard rotor and a first starboard electric motor, the first starboard
electric motor coupled to the first starboard wing;

a second port wing and second starboard wing;
a second port swash plate coupled between a second port rotor and second port electric motor, the second port electric motor
coupled to the second port wing;

a second starboard swash plate coupled between a second starboard rotor and second starboard electric motor, the second starboard
electric motor coupled to the second starboard wing; and

a horizontal stabilizer coupled to a fuselage and an elevator rotatably coupled to the horizontal stabilizer, the fuselage
coupled between the first port wing and second starboard wing;

wherein first starboard and first port rotor pitch, yaw and roll moments are accomplished without the benefit of control surfaces
on a wing.

US Pat. No. 9,776,709

UNMANNED AERIAL VEHICLE ANGULAR REORIENTATION

AEROVIRONMENT, INC., Sim...

1. A method of unmanned aerial vehicle (UAV) body re-orientation comprising:
determining, by a processor, a boresight offset angle error correction value based on a distance between a target point and
a boresight point of a body-fixed image frame; and

effecting, by the processor, an onboard control surface actuation maneuver comprising an angular roll component to translate
the target point in the body-fixed image frame to thereby maintain an offset angle via the boresight offset angle correction
value.

US Pat. No. 9,834,307

HIGH ALTITUDE, LONG ENDURANCE, UNMANNED AIRCRAFT AND METHODS OF OPERATION THEREOF

AEROVIRONMENT, INC., Sim...

1. A method comprising:
acquiring, by a first satellite tracker of a first high altitude, long endurance (HALE) unmanned aircraft, a satellite having
an onboard electromagnetic (EM) sensor;

tracking, by the first satellite tracker of the first HALE unmanned aircraft, the acquired satellite;
signaling, by the first HALE unmanned aircraft to a second HALE unmanned aircraft, the location of the tracked satellite;
emitting interdicting EM radiation, by a directable EM radiation emitter of the first HALE unmanned aircraft in cooperation
with the first satellite tracker, to the tracked satellite;

acquiring, by a second satellite tracker of the second HALE unmanned aircraft, the satellite tracked by the first HALE unmanned
aircraft; and

tracking, by the second satellite tracker of the second HALE unmanned aircraft, the satellite tracked by the first HALE unmanned
aircraft.

US Pat. No. 9,825,497

COMPRESSED MOTOR WINDING

AeroVironment, Inc., Mon...

1. A motor winding comprising a high density multi-conductor wire bundle comprising a compacted Litz wire bundle comprising:
a) a serpentine configuration comprising a central portion and end turns;
b) wherein the central portion comprises compacted Litz wire and wherein the end turns comprise non-compacted rectangular
cross section Litz wire; and

c) wherein the motor winding comprises a coreless winding.

US Pat. No. 9,764,819

ACTIVE DIHEDRAL CONTROL SYSTEM FOR A TORSIONALLY FLEXIBLE WING

AeroVironment, Inc., Sim...

1. An aircraft characterized by a flight envelope, comprising:
a laterally extending wing;
a plurality of pitch-control devices, each pitch-control device being mounted at a separate lateral location along the wing,
and each pitch-control device being configured to apply pitch-control torque at its lateral location, wherein the wing is
characterized by a torsional flexibility high enough to allow the plurality of pitch control devices to control localized
pitch at their lateral wing locations to a degree substantial enough to be significant for flight control throughout the flight
envelope;

sensors determining the relative localized pitches at the plurality of lateral locations along the wing; and
a control system programmed to control the plurality of pitch-control devices based upon the sensed relative localized pitches
at the plurality of lateral locations.

US Pat. No. 9,816,785

INTERACTIVE WEAPON TARGETING SYSTEM DISPLAYING REMOTE SENSED IMAGE OF TARGET AREA

AEROVIRONMENT, INC., Mon...

1. A device, comprising:
a fire control controller;
an inertial measurement unit in communication with the fire control controller, the inertial measurement unit configured to
provide elevation data to the fire control controller;

a magnetic compass in communication with the fire control controller, the magnetic compass operable to provide azimuth data
to the fire control controller;

a navigation unit in communication with the fire control controller, the navigation unit configured to provide position data
to the fire control controller; and

a data store in communication with the fire control controller, the data store having ballistic information associated with
a plurality of weapons and associated rounds;

wherein the fire control controller determines a predicted impact point of a selected weapon and associated round based on
the stored ballistic information, the provided elevation data, the provided azimuth data, and the provided position data;
and

wherein the fire control controller transmits information comprising the determined predicted impact point to a sensor controller
on an aerial vehicle housing a remote sensor to direct the pointing of the remote sensor of the aerial vehicle.

US Pat. No. 9,829,155

CRYOGENIC LIQUID TANK

AeroVironment, Inc., Sim...

1. A storage tank configured to store a cryogenic liquid, the storage tank being characterized by a gravitational bottom and
a gravitational top, comprising:
a lateral wall that defines and substantially surrounds a fluid storage space, the lateral wall forming an inner shell characterized
by a direct-lateral-contact surface area that is configured to be in direct lateral contact with the cryogenic liquid, wherein
the direct-lateral-contact surface area of the inner shell is laterally surrounded by an insulator characterized by a thermal
conductivity that is different near the gravitational top of the direct-lateral-contact surface area than it is near the gravitational
bottom of the direct-lateral-contact surface area.

US Pat. No. 10,104,809

THERMAL MANAGEMENT SYSTEM FOR AN AIRCRAFT AVIONICS BAY

AeroVironment Inc., Monr...

1. A system for managing heat transfer comprising:a heat-generating component; and
a plurality of heat conducting members disposed adjacent one another, each heat conducting member comprising:
a resilient core; and
an outer shell wrapped around at least a portion of the resilient core, the outer shell comprising a material having a relatively high thermal conductivity,
wherein the plurality of heat conducting members are positioned between the heat-generating component and a structural surface;
a structural member disposed proximate the structural surface and comprising:
an upper skin;
a lower skin; and
a foam core disposed between the upper skin and the lower skin;
at least one heat conducting array extending through the foam core and between the upper skin and the lower skin, the heat conducting array defining at least one upper cap, at least one lower cap, and a wall portion extending between the upper cap and the lower cap, the upper cap being disposed proximate a heat source; and
a heat conducting spreader disposed between the lower cap of the heat conducting array and the lower skin of the structural member,
wherein the heat conducting array dissipates heat from the heat-generating component by transferring heat from the at least one upper cap, through the wall portion, to the at least one lower cap, to the heat conducting spreader, through the lower skin, and out to an atmosphere.

US Pat. No. 9,849,788

REACTIVE REPLENISHABLE DEVICE MANAGEMENT

AEROVIRONMENT, INC., Mon...

1. A computer-implemented method for dynamic control of one or more devices based on device measurement data received from
the one or more devices, the method comprising:
receiving, at a remote device, device measurement data from:
a replenishable device,
a replenisher associated with the replenishable device, and
a vehicle associated with the replenishable device, the device measurement data
including (a) identification data, (b) historical data, and (c) real-time data for each
of the replenishable device, the replenisher, and the vehicle;
updating a usage profile associated with vehicle energy usage using the device measurement data received from the replenishable
device, the replenisher, and the vehicle, the usage profile comprising performance data of both the replenishable device and
the vehicle gathered over a period of time; and

analyzing the usage profile to determine whether vehicle energy usage is sub-optimal, wherein when it is determined that vehicle
energy usage is sub-optimal, an automatic controller automatically controls an attribute or an operation of the vehicle.

US Pat. No. 9,850,004

UAV PAYLOAD MODULE CAMERA ASSEMBLY AND RETRACTION MECHANISM

AeroVironment, Inc., Mon...

1. A UAV payload module retraction mechanism apparatus comprising:
a) a payload module housing;
b) a payload pivotally attached to the housing;
c) a winch attached to the payload;
d) a biasing member mounted to bias the payload out of the housing; and
e) an elongated flexible drawing member coupled between the housing and the winch, the elongated flexible drawing member being
capable of being drawn by the winch to retract the payload within the housing.

US Pat. No. 9,981,563

ELECTRIC VEHICLE SUPPLY EQUIPMENT WITH TEMPERATURE CONTROLLED CURRENT

AeroVironment, Inc., Mon...

1. An electric vehicle supply equipment (EVSE) system for charging an electric vehicle, comprising:a utility connector comprising a first pair of power conductors;
a docking connector comprising a second pair of power conductors, said docking connector being engagable with a charging port of an electric vehicle;
a pair of contactors between said first and second pairs of power conductors;
a processor and a memory accessible by said processor, said pair of contactors under control of said processor;
a control pilot conductor extending through said docking connector;
a pulse generator coupled to said control pilot conductor and having a pulse duty cycle controlled by said processor;
a temperature sensor having an output representative of a present temperature, said output coupled to said processor;
said memory containing: (a) a nominal pulse duty cycle corresponding to a nominal value of maximum allowable current, (b) a predetermined threshold temperature, said processor programmed to reduce the pulse duty cycle of said pulse generator from said nominal pulse duty cycle by a reduction factor that is a function of an increase of said present temperature above said predetermined threshold temperature.

US Pat. No. 9,882,313

ELECTRICAL PLUG ADAPTER HAVING SOCKET KEY SAFETY SYSTEM

AEROVIRONMENT, INC., Sim...

1. A system, comprising:
an adapter comprising:
a socket defined by a first technical standard and comprising a neutral socket, a power socket, and a ground socket;
a plug defined by a second technical standard and comprising a neutral blade, a power blade, and a ground blade;
at least one key extending out from a face of the socket; and
an adapter housing, wherein the socket and the plug are disposed on opposing sides of the adapter housing;
an electric vehicle (“EV”) power adapter, the EV power adapter comprising:
a second plug compatible with the first technical standard and comprising a second neutral blade, a second power blade, and
a second ground blade; and

at least one complementary key socket extending inward from a face of the second plug, wherein the at least one complementary
key socket is aligned with the at least one key of the adapter;

wherein the socket of the adapter is configured to receive the second plug wherein the at least one complementary key socket
is aligned with the at least one key of the adapter, wherein the at least one complementary key socket is configured to receive
the at least one key so as to electrically couple the second neutral blade to the neutral socket and the neutral blade, electrically
couple the second power blade to the power socket and the power blade, and electrically couple the second ground blade to
the ground socket and the ground blade.

US Pat. No. 9,957,065

AIRCRAFT GROUNDING SYSTEM

AEROVIRONMENT, INC., Sim...

1. A method comprising:adhering an air vehicle with an adhesive to an external surface;
wherein adhering the air vehicle further comprises: adhering an adhesive anchoring assembly of the air vehicle, via the adhesive, to an air vehicle landing surface external to the air vehicle; and
wherein adhering the adhesive anchoring assembly of the air vehicle further comprises:
rotating at least one cylinder of the adhesive anchoring assembly relative to the air vehicle, the at least one cylinder comprising an attachment joint disposed on one end of the at least one cylinder proximate to the air vehicle and a brush assembly disposed on a distal end of the at least one cylinder.

US Pat. No. 9,950,790

AIR VEHICLE FLIGHT MECHANISM AND CONTROL METHOD

AEROVIRONMENT, INC., Mon...

1. An air vehicle, comprising:a processor;
at least one drive motor in communication with the processor;
a first flapping wing in communication with one of the at least one drive motor; and
a second flapping wing in communication with one of the at least one drive motors;
wherein the processor and the at least one drive motor are configured to drive the first and second flapping wings to provide lift and control moments without the benefit of either horizontal or vertical stabilizers;
wherein the processor is configured to provide commands resulting in first and second wing movement selected from the group consisting of: variable differential sweep angles of deflection of the first and second flappable wings in the course of respective sweep angles of travel, variable differential luffing of the respective first and second flapping wings, and variable and differential angular velocity of the respective first and second flapping wings.

US Pat. No. 9,873,524

POWER AND COMMUNICATION INTERFACE FOR VERTICAL TAKE-OFF AND LANDING (VTOL) UNMANNED AERIAL VEHICLES (UAVS)

AEROVIRONMENT, INC., Sim...

1. A method comprising:
receiving a rearward facing tang extending from a rear fuselage portion of a vertical take-off and landing (VTOL) unmanned
aerial vehicle (UAV) in an opening disposed in a landing surface of a UAV pod; and

securing the tang of the VTOL UAV to the UAV pod via a locking armature disposed in the opening disposed in the landing surface,
wherein the locking armature detachably couples the tang to the UAV pod.

US Pat. No. 9,873,526

LAUNCH TUBE RESTRAINT SYSTEM FOR UNMANNED AERIAL VEHICLE (UAV)

AEROVIRONMENT, INC., Mon...

1. An unmanned aerial launch vehicle (UAV) launch apparatus, comprising:
a UAV;
a tube containing the UAV, wherein the tube has an open end;
a cap positioned over the open end of the tube; and
a strap extending through at least one strap guide and restraining the cap;
wherein the strap extends around the entire tube.

US Pat. No. 9,880,563

GEOGRAPHIC SURVEY SYSTEM FOR VERTICAL TAKE-OFF AND LANDING (VTOL) UNMANNED AERIAL VEHICLES (UAVS)

AEROVIRONMENT, INC., Sim...

1. A method of unmanned aerial vehicle (UAV) operation, comprising:
receiving from a customer a first data request, the first data request comprising:
a first geographic coverage area; and
a refresh rate for the first geographic coverage area;
planning a first plurality of flight missions to accomplish the first data request;
uploading flight missions data representing the first plurality of flight missions into a UAV pod;
deploying the UAV pod;
providing a two-rotor UAV with flight mission data for one of the first plurality of flight missions from the UAV pod;
launching the two-rotor UAV from the UAV pod to perform the one of the first plurality of flight missions;
receiving the two-rotor UAV on the UAV pod; and
receiving in the UAV pod a first flight survey data obtained from the one of the first plurality of flight missions from the
two-rotor UAV.

US Pat. No. 9,914,364

SYSTEM FOR CHARGING AN ELECTRIC VEHICLE (EV)

AEROVIRONMENT, INC., Mon...

1. A method of charging an electric vehicle (EV), comprising:
receiving a user's authentication code in an electric vehicle service equipment (EVSE) from a user's mobile device;
comparing in the EVSE the user's authentication code to a whitelist having a plurality of authorized user authentication codes;
and

enabling an electric vehicle (EV) charging transaction serviced by the EVSE in response to the comparing of the user's authentication
code to the whitelist;

wherein a user's authentication code is authenticated to enable the EV charging transaction without concurrent access by the
EVSE to an EVSE-related remote server;

providing power through a power cable in response to enabling the EV charging transaction;
receiving a second occurrence of the user's authentication code in the EVSE from the user's mobile device; and
sending by the EVSE an electrical current indication to the user's mobile device of a previous EV charging transaction in
response to receiving the second occurrence of the user's authentication code.

US Pat. No. 9,902,489

AIRCRAFT SYSTEM FOR REDUCED OBSERVER VISIBILITY

AEROVIRONMENT, INC., Sim...

1. An aircraft apparatus, comprising:
a fuselage boom having proximal and distal ends;
a wing coupled to the proximal end of said fuselage boom;
a first transparent stabilizer coupled to a distal end of said fuselage boom;
a servo housed in said distal end of said fuselage boom, said servo having a servo arm; and
a servo horn slidably coupled to said first transparent stabilizer to slidably receive and detachably couple said servo arm
to said first transparent stabilizer.

US Pat. No. 10,042,360

UNMANNED AIRCRAFT TURN AND APPROACH SYSTEM

AeroVironment, Inc., Sim...

1. An unmanned aircraft system including an aircraft, comprising:a wing system configured to carry the majority of the aircraft weight when in flight;
a plurality of control surfaces configured to control aircraft pitch, aircraft roll and aircraft yaw in flight;
a camera characterized by a field of view, the camera being mounted on a camera pod, wherein the camera pod is only provided with actuators that vary the orientation of the camera field of view in yaw, relative to the aircraft, between a directly forward-looking orientation and a directly side-looking orientation; and
a control system programmed to control the control surfaces, and further programmed to control the camera pod to only change the camera orientation in yaw, relative to the aircraft;
wherein the control system is programmed with a commit function for use when the camera is observing an identified target that is not directly in front of the aircraft; and
wherein the commit function controls the camera orientation in yaw such that the camera continuously maintains the identified target within its field of view.

US Pat. No. 9,957,044

AIR VEHICLE FLIGHT MECHANISM AND CONTROL METHOD

AEROVIRONMENT, INC., Mon...

1. A wing comprising:a mast engaging a fitment;
a spar engaging the fitment substantially perpendicular to the mast, the spar rotatably coupled to the mast to selectively decrease an angle of the spar relative to the mast;
a mast tube disposed about a portion of the mast;
a spar tube disposed about a portion of the spar;
a scrim attached to the spar tube and the mast tube;
a yoke engaging a rear of the spar; and
a first batten disposed on the scrim and extending in a direction radially from an intersection of the spar and the mast, the first batten having a distal end proximate to an edge of the airfoil;
wherein the yoke is tiltable to decrease the substantially perpendicular angle between the spar and mast resulting in increased luffing of the scrim.

US Pat. No. 9,941,757

FLUX CONCENTRATOR FOR IRONLESS MOTOR

AeroVironment, Inc., Mon...

1. A magnet array for a motor comprising an array of permanent magnets being arranged such that flux from the permanent magnets reinforce on one side of the array and substantially cancel on an opposite side of the array, wherein the magnets are arranged such that the magnetic moments of adjacent magnets are oriented in directions separated by about 45 degrees, and such that a magnet within the array comprises a magnetic moment oriented generally perpendicular to the reinforcing side of the array, and comprising an ironless winding adjacent to the array comprising conductor bundles having a generally rectangular cross-section arranged such that a long side of the generally rectangular cross-section is transverse to a direction of magnetic field lines of the magnet having the generally perpendicular magnetic moment.

US Pat. No. 9,915,692

UTILITY GROUND DETECTION

AeroVironment, Inc., Mon...

1. A missing utility ground detection circuit comprising:
a) a pair of balanced resistors each connected to receive utility power from a different one of a pair of utility power lines,
the balanced resistors being connected together at a summing node to be capable of summing a utility voltage from the pair
of utility power lines;

b) an unbalance resistor connected so as to shunt voltage from only one line of the pair of utility power lines so as to unbalance
the pair of utility power lines to allow detection of a missing utility ground when a utility ground is not present;

c) a summing amplifier comprising:
1) a first input coupled to the summing node;
2) a second input coupled to a second reference voltage; and
3) an output;
d) an averaging circuit connected at the output of the summing amplifier; and
e) a comparator comprising a first input connected to the averaging circuit a second input connected to a threshold voltage.

US Pat. No. 9,964,574

RESIDUAL CURRENT DETECTING (RCD) AND GROUND IMPEDANCE MONITORING TRANSFORMER AND CONTROL METHODS

AEROVIRONMENT, INC., Mon...

1. A transformer comprising:a first drive winding wound on a first core, wherein the first drive winding is driven with a first high frequency square wave current;
a second drive winding wound on a second core, wherein the second drive winding is driven with a second high frequency square wave current, and wherein the second high frequency square wave current has an opposite polarity of the first high frequency square wave current;
a sense winding wound across the first and second cores; and
a compensation winding wound across the first and second cores;
wherein one or more utility lines are threaded through a middle of the first and second cores, wherein a common mode current in the one or more utility lines causes one or more pulses to appear on the sense winding, wherein a current on the compensation winding is adjusted until the one or more pulses on the sense winding are cancelled out, and wherein the common mode current on the one or more utility lines is the adjusted current on the compensation winding multiplied by a turn ratio between the compensation winding and the sense winding.

US Pat. No. 10,103,592

STATOR WINDING HEAT SINK CONFIGURATION

AeroVironment, Inc., Mon...

1. A motor comprising:a) a rotor; and
b) a stator comprising:
i) a winding; and
ii) a front stator yoke mounted onto a front end of the winding;
iii) front cooling fins mounted to the front yoke, the front cooling fins have a solid front annular face, the front cooling fins being oriented radially and extending laterally between the front annular face and the front stator yoke;
iv) a rear stator yoke mounted onto a rear end of the winding;
v) rear cooling fins mounted to the rear yoke the rear cooling fins have a solid outer annular face, the rear cooling fins oriented radially and extend radially between the rear stator yoke and the outer annular face; and
vi) wherein the front cooling fins are separated by the winding from the rear cooling fins.

US Pat. No. 10,194,551

MOUNTING SYSTEM FOR MECHANICAL-SHOCK RESISTANT PRINTED CIRCUIT BOARD (PCB)

AEROVIRONMENT, INC., Sim...

1. A shock resistant fuselage system, comprising:first and second fuselage side walls, each of the first and second fuselage side walls having a plurality of guide posts and at least one fixed post;
a printed circuit board (PCB) rigidly attached to at least one of the first and second fuselage side walls, the PCB having a plurality of guide slots and at least one mounting hole, wherein each of the plurality of guide posts is slideably seated in a respective one of the plurality of guide slots, and wherein each fixed post of the least one fixed post is fixedly seated in a respective one of the at least one mounting hole; and
a plurality of electrical components mounted to the PCB such that a larger proportion of larger electrical components of the plurality of electrical components are mounted at a PCB front end than a PCB rear end;
wherein elastic deformation of the PCB is guided by the guide slots between the first and second fuselage side walls.

US Pat. No. 10,138,001

UAV PAYLOAD MODULE CAMERA ASSEMBLY AND RETRACTION MECHANISM

AeroVironment, Inc., Mon...

1. A UAV comprising:a) a payload module comprising a deployable payload; and
b) a retraction mechanism apparatus capable of moving the payload from a stowed position within a UAV to a deployed position extending out of the UAV, the retraction mechanism being configured such that the payload retracts back into the UAV upon contact with a landing surface if the payload is not retracted before the UAV contacts the landing surface so as to reduce at least one of: (1) a probability, or (2) a severity of damage to a deployed payload upon landing.

US Pat. No. 9,988,147

VERTICAL TAKEOFF AND LANDING (VTOL) AIR VEHICLE

AEROVIRONMENT, INC., Mon...

1. A flight control apparatus for a fixed-wing aircraft, comprising:a first port wing and a first starboard wing;
a first port swash plate coupled between a first port rotor and a first port electric motor, the first port electric motor coupled to the first port wing;
a first starboard swash plate coupled between a first starboard rotor and a first starboard electric motor, the first starboard electric motor coupled to the first starboard wing; and
a horizontal stabilizer coupled to a fuselage and an elevator rotatably coupled to the horizontal stabilizer, the fuselage coupled between the first port wing and the first starboard wing.

US Pat. No. 10,046,864

SMALL UNMANNED AERIAL VEHICLE (SUAV) SHIPBOARD RECOVERY SYSTEM

AEROVIRONMENT, INC., Sim...

12. A small unmanned aerial vehicle (SUAV) recovery system comprising:a net having at least three corners; and
a boom connected to at least one corner of the net; and
a mast, wherein the mast is stationary;
a connector, wherein the mast and the boom are connected at the connector;
wherein energy of an impact of the SUAV into the net is progressively transferred by at least one of: a vertical rotation of the boom in a direction towards the impact of the SUAV, and a horizontal rotation of the boom in a direction away from the impact of the SUAV.

US Pat. No. 10,038,225

BATTERY WATERING EVENT DETECTION USING A TEMPERATURE SENSOR

AEROVIRONMENT, INC., Sim...

1. A method of battery cell monitoring, comprising:measuring a temperature of an electrolyte in a battery cell using a temperature sensor;
outputting from the temperature sensor a plurality of electrolyte temperature signals indicative of the temperature of the electrolyte over time;
providing the plurality of electrolyte temperature signals to a system controller;
determining by the system controller a sudden transition in the electrolyte temperature signals;
logging a watering event data indication in a memory in response to calculating the sudden transition; and
determining whether the battery cell has been adequately maintained over time based on the logged watering event data.

US Pat. No. 10,065,737

AIR VEHICLE FLIGHT MECHANISM AND CONTROL METHOD FOR NON-SINUSOIDAL WING FLAPPING

AEROVIRONMENT, INC., Mon...

1. A flapping wing method, comprising:rotating a crank capstan about an axis of rotation; and
pulling a first drive cable with the crank capstan, the first drive cable windably coupled to a variable-radius drive pulley portion fixed on a rotatable first wing capstan to cause the rotatable first wing capstan to rotate, the rotatable first wing capstan coupled to a first wing;
wherein the first wing capstan is configured to non-constantly, angularly rotate responsive to a constant angular rotation of the crank capstan.

US Pat. No. 10,094,165

WATER-TIGHT COMPARTMENT WITH REMOVABLE HATCH AND TWO-SIDED GEL SEAL FOR MULTIPLE CONDUIT ACCESS

AeroVironment, Inc., Mon...

1. An accessible compartment in a body of a craft, said body having an exterior body surface, said accessible compartment comprising:a side wall and a floor defining a compartment interior, said side wall being transverse to said exterior body surface;
a compartment shoulder at a top edge of said side wall and comprising a compartment shoulder surface transverse to said side wall, said compartment shoulder surface being depressed below said exterior body surface to define a step surrounding said compartment shoulder;
at least one elongate communication element adjacent said compartment shoulder and extending into said compartment interior along a direction transverse to said top edge of said side wall;
a hatch comprising a hatch body having a hatch body edge that is congruent with said step and a hatch shoulder comprising a hatch shoulder surface facing said compartment shoulder surface;
a first sealing gasket between said compartment shoulder surface and said hatch shoulder surface, said first sealing gasket comprising a conformable material of a conformability corresponding to an exclusion size of a diameter of one of: (a) a gas molecule, or (b) a liquid molecule;
a first fastening structure on said compartment shoulder and a second fastening structure on said hatch shoulder;
wherein said first sealing gasket has a first side attached to one of: (a) said hatch shoulder surface or (b) said compartment shoulder surface, said first sealing gasket further having a second side opposite said first side, said conformable material comprising a first conformable layer, said first sealing gasket further comprising a first non-adhesive layer on said second side covering said first conformable layer;
wherein said compartment shoulder surface comprises a compartment inner shoulder surface and a compartment outer shoulder surface, said first sealing gasket being attached to said compartment inner shoulder surface, and said first fastener structure comprising fastener holes through said compartment outer shoulder surface adapted to receive respective fasteners;
wherein said hatch shoulder surface comprises a hatch inner shoulder surface and a hatch outer shoulder surface, said first sealing gasket being attached to said hatch inner shoulder surface, and said second fastener structure comprising fastener holes through said hatch outer shoulder surface, whereby said first and second gaskets are between the compartment and hatch inner shoulder surfaces; and
wherein said compartment inner shoulder surface and said hatch inner shoulder surface are ramped with respect to one another whereby to slope away from one another in a direction away from said compartment interior.

US Pat. No. 10,081,441

TILT-BALL TURRET WITH GIMBAL LOCK AVOIDANCE

AEROVIRONMENT, INC., Mon...

1. An aircraft having a sensor for viewing at or below the ground horizon, the aircraft comprising:a fuselage; and
a turret assembly coupled to the fuselage, the turret assembly including:
a roll actuator including a drive shaft;
a yoke having a pair of prongs coupled to the drive shaft, the yoke being rotatable via the roll actuator and drive shaft along a roll axis oriented substantially parallel to a center axis of the aircraft;
a turret mounted on the prongs of the yoke for rotation along atilt axis perpendicular to the roll axis;
a tilt actuator operable to tilt the turret about the tilt axis; and
the sensor housed in the turret for tilting therewith about the tilt axis and rolling therewith about the roll axis; and
a wiring harness for delivery of electrical signals to and from the turret, the wiring harness including one or more wires having a first portion that extends through the drive shaft and a second portion that is mounted exteriorly of a first prong of the yoke, between the first prong and the turret,
wherein when the aircraft is flying level, the roll axis extending forward of the aircraft is aimed at an angle above the ground horizon, such that gimbal lock is avoided when the field of view of the sensor is directed below the ground horizon.

US Pat. No. 10,189,581

UAV PAYLOAD MODULE CAMERA ASSEMBLY AND RETRACTION MECHANISM

AeroVironment, Inc., Mon...

1. A UAV comprising, a housing,a) a payload module comprising a deployable payload; and
b) a retraction mechanism apparatus capable of moving the payload from a stowed position within a UAV to a deployed position extending out of the UAV, the retraction mechanism being configured such that the payload retracts back into the UAV upon contact with a landing surface if the payload is not retracted before the UAV contacts the landing surface so as to reduce at least one of: (1) a probability, or (2) a severity of damage to a deployed payload upon landing.

US Pat. No. 10,138,801

POWERPLANT AND RELATED CONTROL SYSTEM AND METHOD

AeroVironment, Inc., Sim...

1. A powerplant, comprising:an engine configured to react a first reactant with a gaseous stream of second reactant to produce energy and an exhaust stream;
a first-stage turbocharger including a first-stage turbine driven by an exhaust stream of the engine and a first-stage compressor configured to compress the second stream of gaseous reactant for the engine;
a second-stage turbocharger including a second-stage turbine driven by the exhaust stream of the engine and a second-stage compressor configured to compress the second stream of gaseous reactant for the engine, wherein the second-stage compressor is intermediate the first-stage compressor and the engine, wherein the second-stage turbine is intermediate the first-stage turbine and the engine;
a first-stage afterburner in the exhaust stream intermediate the first-stage turbine and the second-stage turbine; and
a second-stage afterburner in the exhaust stream intermediate the second-stage turbine and the engine; and
a control system programmed to control the operation of the first-stage and second-stage afterburners.

US Pat. No. 10,196,150

SYSTEM FOR ALIGNING A PROPELLER

AEROVIRONMENT, INC., Sim...

1. A method, comprising:rotating a sensor trigger by rotating a shaft of a motor;
sensing the sensor trigger as the sensor trigger rotates to a point adjacent a sensor fixedly coupled to a casing of the motor; and
holding a propeller in alignment with a wing of an aircraft by a control signal to the motor;
wherein the propeller is substantially aligned with the wing of the aircraft when the sensor trigger and the sensor are aligned.

US Pat. No. 10,124,909

SYSTEMS AND DEVICES FOR REMOTELY OPERATED UNMANNED AERIAL VEHICLE REPORT-SUPPRESSING LAUNCHER WITH PORTABLE RF TRANSPARENT LAUNCH TUBE

AEROVIRONMENT, INC., Mon...

1. A system comprising:a launcher having a launcher volume defined by a launcher wall, the launcher wall comprising a continuous radio-frequency (RF) permeable material;
a receiver disposed within the launcher volume, the receiver receiving wireless communication via one or more RF signals received wirelessly through the launcher wall of the launcher, in a pre-launch state.

US Pat. No. 10,247,518

INTERACTIVE WEAPON TARGETING SYSTEM DISPLAYING REMOTE SENSED IMAGE OF TARGET AREA

AEROVIRONMENT, INC., Mon...

1. A device comprising:a fire control controller, wherein the fire control controller determines a predicted impact point of a selected weapon and associated round, and wherein the fire control controller transmits information on the predicted impact point to a sensor controller on an aerial vehicle housing a remote sensor to direct the pointing of the remote sensor of the aerial vehicle.

US Pat. No. 10,239,639

LAUNCH TUBE RESTRAINT SYSTEM FOR UNMANNED AERIAL VEHICLE (UAV)

AEROVIRONMENT, INC., Mon...

1. An unmanned aerial launch vehicle (UAV) launch apparatus, comprising:a tube, wherein the tube has an open end;
a cap positioned over the open end of the tube;
a strap extending through at least one strap guide and restraining the cap;
wherein the strap extends around the entire tube; and
a gas generator configured to provide a launching force wherein the launching force is at least sufficient to enable a UAV to translate axially out of the tube.

US Pat. No. 10,209,707

SAFETY SYSTEM FOR OPERATION OF AN UNMANNED AERIAL VEHICLE

AEROVIRONMENT, INC., Mon...

1. A method comprising:selecting an unmanned aerial vehicle (UAV) command on a controller, the controller comprising a first processor with addressable memory;
presenting a first activator and a second activator on a display of the controller for the selected UAV command, wherein the second activator is a slider; and
sending the UAV command to a UAV if the first activator and the second activator are selected, the UAV comprising a second processor with addressable memory.

US Pat. No. 10,266,258

AIR VEHICLE FLIGHT MECHANISM AND CONTROL METHOD

AEROVIRONMENT, INC., Mon...

1. An air vehicle apparatus, comprising:first and second flapping control surfaces;
wherein the first and second flapping control surfaces are capable of providing hovering and control moments without the benefit of additional control surfaces; and
wherein the hovering and control moments are selected from at least one of: variable differential sweep angles of deflection of the first and second flapping control surfaces in the course of respective sweep angles of travel, variable differential luffing of the respective first and second flapping control surfaces, and variable and differential angular velocity of the respective first and second flapping control surfaces.

US Pat. No. 10,259,577

VERTICAL TAKEOFF AND LANDING (VTOL) AIR VEHICLE

AEROVIRONMENT, INC., Sim...

1. A flight control apparatus for a fixed-wing aircraft, comprising:a first port wing and a first starboard wing;
a first port electric motor coupled to the first port wing;
a first port swash plate coupled between a first port rotor and the first port electric motor, wherein the first port swash plate provides single-axis cyclic pitch control of the first port rotor;
a first starboard electric motor coupled to the first starboard wing; and
a first starboard swash plate coupled between a first starboard rotor and the first starboard electric motor, wherein the first starboard swash plate provides single-axis cyclic pitch control of the first starboard rotor;
wherein a fuselage is coupled between the first port wing and the first starboard wing.

US Pat. No. 10,227,129

AIRCRAFT SYSTEM FOR REDUCED OBSERVER VISIBILITY

AEROVIRONMENT, INC., Sim...

1. An aircraft apparatus, comprising:a boom;
a stabilizer coupled to said boom;
a servo housed in said boom, said servo having a servo arm; and
a servo horn slidably coupled to said stabilizer to slidably receive and detachably couple said servo arm to said stabilizer.

US Pat. No. 10,204,522

DEEP STALL AIRCRAFT LANDING

AeroVironment, Inc., Sim...

1. An unmanned aircraft system, comprising:an aircraft including a wing having an upper surface and a lower surface defining an upright orientation for normal aircraft flight and an inverted orientation for inverted flight, the upper surface being gravitationally above the lower surface while in the upright orientation, and the lower surface being gravitationally above the upper surface while in the inverted orientation, and further including one or more repeatedly controllable control surfaces;
a remote-control station; and
a remote-control control system configured for a user to remotely control the flight of the aircraft using the remote-control station;
wherein the remote-control station is provided with an auto-land function that instructs the control system to automatically control the one or more repeatedly controllable control surfaces such that the aircraft conducts an inverting maneuver in which the aircraft rotates from the upright orientation to the inverted orientation, and such that the wing is at least partially stalled while the aircraft is in the inverted orientation;
and further comprising landing gear, wherein the landing gear is located above the wing and positioned for landing in the inverted orientation.