Methods and systems are described herein for predicting collisions between uncrewed vehicles and preventing those collisions. A collision prevention system may generate collision spheroids for a multitude of uncrewed vehicles. Those collision spheroids may represent a plurality of three-dimensional points around each uncrewed vehicle. When the collision prevention system determines that collision spheroids corresponding to two uncrewed vehicles intersect, the collision prevention system may determine that a collision is imminent and may attempt to prevent the collision by causing one or both uncrewed vehicles to change velocity.
Systems, devices, and methods including a vendors ecosystem (104) configured to provide a software component; an account portal (101) configured to: determine existence of any issues based on whether the provided software component passes a laboratory field test; report issues to the at least one external software developer; receive an updated software component from the at least one external software developer fixing the reported issues; and release the software component if no issues are found indicated that the test was passed; and an end user operation system (114) configured to: determine an existence of any issues based on whether the released software component passes a frontline field test to certify the software component; report any issues from the frontline field test to the external software developer; and deploy the certified software component on one or more devices if no issues from the frontline field test are found.
G06F 9/06 - Arrangements for program control, e.g. control units using stored programs, i.e. using an internal store of processing equipment to receive or retain programs
In one possible embodiment, a propeller adapter is provided which includes a base having at least one fastener hole therethrough and a propeller alignment boss extending upward from the base. Opposing capture walls extend upward from the base, each of the opposing capture walls have a lip extending inward to capture and retain corresponding opposing outside edges of a root portion of a propeller therein upon seating of the propeller root portion between the opposing blade capture walls.
Systems, devices, and methods for an aircraft autopilot guidance control system (100, 300) for guiding an aircraft having a body, the system comprising: a processor (101) configured to determine if a yaw angle difference and a pitch angle difference meet corresponding angle thresholds; a skid-to-turn module (105) configured to generate a skid-to-turn signal if the corresponding angle thresholds are met; a bank-to-turn module (102) configured to generate a bank-to-turn signal having a lower bandwidth than the generated skid-to-turn signal; a rudder integrator module (104) configured to add a rudder integrator feedback signal to the bank-to-turn signal, where the rudder integrator feedback signal is proportional to a rudder integrator; and a filter module (103) configured to filter the generated bank-to-turn signal, wherein the filter module (103) comprises a low-pass filter configured by a set of gains to pass the bank-to-turn signal if a side force on the body meets a side force threshold (111).
Systems, devices, and methods including a leading edge tubular member (114); an upper tubular member (110); a lower tubular member (112); one or more upper rib members (124) connected between the leading edge tubular member (114) and the upper tubular member (110); one or more lower rib members (126) connected between the leading edge tubular member (114) and the lower tubular member (112); a rigid sandwich shell (102) disposed between the upper tubular member (110) and the leading edge tubular member (114); and a sandwich shear web (104) disposed between the upper tubular member (110) and the lower tubular member (112); where the rigid sandwich shell (102) and the sandwich shear web (104) form a D-shape.
Systems, devices, and methods including one or more rib mounting flanges (200a, 200b, 200c, 200d, 200e), where each rib mounting flange comprises: a spar opening (202a) configured to receive a main spar (110) of a wing panel (100); and one or more holes (204a) for receiving cross-bracing cables (114); and one or more holes (205a) for connecting the rib mounting flange to an adjacent rib mounting flange.
Systems, devices, and methods for: an unmanned aerial vehicle (UAV); at least one sensorless motor comprising a set of windings and a rotor; at least one propeller connected to the at least one sensorless motor; a microcontroller in communication with the at least one sensorless motor, wherein the microcontroller is configured to: determine a rotation rate of the at least one propeller; determine a rotation direction of the at least one propeller; provide an output to stop the at least one propeller and provide an output to start the at least one propeller.
H02P 1/18 - Arrangements for starting electric motors or dynamo-electric converters for starting dynamo-electric motors or dynamo-electric converters for starting an individual DC motor
8.
METHODS AND SYSTEMS FOR RETAINING LATERAL CONTROL OF AN UNMANNED AERIAL VEHICLE DURING LANDING
Systems, devices, and methods including an unmanned aerial vehicle (UAV) (101); one or more inner wing panels (107) of the UAV; one or more outer wing panels (109) of the UAV; at least one inboard propeller (140) attached to at least one engine (110) disposed on the one or more inner wing panels; at least one tip propeller (141) attached to at least one engine (110) disposed on the one or more outer wing panels; at least one microcontroller (420) configured to: determine an angular position of the at least one inboard propeller; and send a signal to halt rotation of the at least one inboard propeller such that the at least one inboard propeller is held in an attitude that provides for clearance of the propeller blade to the ground upon landing.
Systems, devices, and methods for a five-phase inverter motor (110) comprising: a stator (112) comprising: at least one armature (116); at least five teeth (138); a rotor (120) comprising at least four magnets (122); at least five inverters (420); where four magnets of the at least four magnets are associated with five teeth of the at least five teeth.
H02P 25/22 - Multiple windingsWindings for more than three phases
H02K 21/12 - Synchronous motors having permanent magnetsSynchronous generators having permanent magnets with stationary armatures and rotating magnets
H02K 21/14 - Synchronous motors having permanent magnetsSynchronous generators having permanent magnets with stationary armatures and rotating magnets with magnets rotating within the armatures
H02P 27/06 - Arrangements or methods for the control of AC motors characterised by the kind of supply voltage using variable-frequency supply voltage, e.g. inverter or converter supply voltage using DC to AC converters or inverters
10.
SYSTEMS AND DEVICES FOR AN RF SIGNAL CARRYING CABLE OF A MULTI-PACK LAUNCHER SYSTEM
Systems, devices, and methods including a launch control box (126); a multi- pack launcher (MPL) box (102); and a cable (104) connecting the launch control box and the MPL box, where the cable comprises: an outer jacket (119), a shielded braid (108), a first wire (110A), a second wire (110B), a third wire (110C), and a fourth wire (110D), where the first wire (110A) and the second wire (110B) are shielded by the shielded braid (108), where the third wire (110C) and the fourth wire (110D) are outside of the shielded braid (108), and where the third wire (110C) and the fourth wire (110D) act as an antenna.
Systems, devices, and methods for a ground support system (100) for an unmanned aerial vehicle (UAV) including: at least one handling fixture (130), where each handling fixture (103) is configured to support at least one wing panel (107) of the UAV (101); and at least one dolly (150), where each dolly is configured to receive at least one landing pod (113) of the UAV, and where each landing pod supports at least one wing panel of the UAV; where the at least one handling fixture and the at least one dolly are configured to move and rotate two or more wing panels to align the two or more wing panels with each other for assembly of the UAV; and where the at least one dolly (150) further allows for transportation of the UAV (101) over uneven terrain.
B64F 5/50 - Handling or transporting aircraft components
B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
B60P 3/40 - Vehicles adapted to transport, to carry or to comprise special loads or objects for carrying long loads, e.g. with separate wheeled load-supporting elements
B60P 7/12 - Securing to vehicle floor or sides the load being tree-trunks, beams, drums, tubes, or the like
B61D 3/16 - Wagons or vans adapted for carrying special loads
B64C 1/26 - Attaching the wing or tail units or stabilising surfaces
B23Q 1/26 - Movable or adjustable work or tool supports characterised by constructional features relating to the co-operation of relatively movable membersMeans for preventing relative movement of such members
B66F 7/16 - Lifting frames, e.g. for lifting vehiclesPlatform lifts with platforms supported directly by jacks by one or more hydraulic or pneumatic jacks
B66F 7/22 - Lifting frames, e.g. for lifting vehiclesPlatform lifts with tiltable platforms
B66F 9/00 - Devices for lifting or lowering bulky or heavy goods for loading or unloading purposes
B64C 1/12 - Construction or attachment of skin panels
B65D 85/68 - Containers, packaging elements or packages, specially adapted for particular articles or materials for machines, engines or vehicles in assembled or dismantled form
B60D 1/01 - Traction couplings or hitches characterised by their type
B60D 1/28 - Traction couplingsHitchesDraw-gearTowing devices characterised by arrangements for particular functions for preventing unwanted disengagement, e.g. safety appliances
B64F 1/00 - Ground or aircraft-carrier-deck installations
B64F 1/32 - Ground or aircraft-carrier-deck installations for handling freight
B62B 3/02 - Hand carts having more than one axis carrying transport wheelsSteering devices thereforEquipment therefor involving parts being adjustable, collapsible, attachable, detachable, or convertible
B62B 3/04 - Hand carts having more than one axis carrying transport wheelsSteering devices thereforEquipment therefor involving means for grappling or securing in place objects to be carriedLoad handling equipment
B66F 7/08 - Lifting frames, e.g. for lifting vehiclesPlatform lifts with platforms supported by levers for vertical movement hydraulically or pneumatically operated
Systems, devices, and methods including at least one flight control computer (FCC) (113) associated with at least one UAV (108), where the at least one FCC is configured to: determine a direction of travel of the at least one UAV relative to the Sun; adjust a UAV airspeed to a first airspeed if the determined direction of travel is towards the Sun; and adjust the UAV airspeed to a second airspeed if the determined direction of travel is away the Sun; where the first airspeed is greater than the second airspeed to maximize solar capture of a solar array (110) covering at least a portion of the UAV.
Systems, devices, and methods including at least one computing device (108) associated with a ground control station (104), the at least one computing device configured to: determine a starting position for an unmanned aerial vehicle (UAV) descent based on one or more local weather conditions; determine a flight pattern for landing the UAV based on the determined starting position for the UAV; and modify the determined flight pattern based on a change in the one or more local weather conditions and a current position of the UAV.
Systems, devices, and methods including: at least one unmanned aerial vehicle (UAV) (101); at least one flight control computer (FCC) (110) associated with each UAV, where the FCC controls movement of each UAV; at least one computing device (108) associated with a ground control station (104); where the at least one FCC maintains a first flight pattern (103) of a respective UAV of the at least one UAV above the ground control station; where the at least one computing device is configured to transmit a transition signal (168) to the at least one FCC to transition the respective UAV of the at least one UAV from the first flight pattern to a second flight pattern (105) in response to a wind speed exceeding a set threshold relative to a flight speed of the respective UAV of the at least one UAV.
Systems, devices, and methods for a fleet of three or more unmanned aerial vehicles (UAVs) (101A-E), where each UAV of the fleet of UAVs comprise a respective flight control computer (FCC) (110); at least one computing device (108) at a ground control station (104), where each computing device is in communication with each FCC, and where each computing device is associated with at least one operator (106A-C); where the fleet of UAVs above the threshold altitude (118) are in communication with the first computing device monitored by at least one operator such that a ratio of operators to UAVs above the threshold altitude exceeds a 1:1 ratio; and where the first UAV below the threshold altitude is in communication with the second computing device monitored by at least one operator such that a ratio of operators to UAVs below the threshold altitude does not exceed the 1:1 ratio.
Systems, devices, and methods including: at least one unmanned aerial vehicle (UAV) (108A,B); at least one battery pack (114) comprising at least one battery (120); and at least one motor (112) of the at least one UAV, where the at least one battery is configured to transfer energy to the at least one motor; where power from the at least one motor is configured to ascend (124) the at least one UAV to a second altitude (142) when the at least one battery is at or near capacity, and where the second altitude is higher than the first altitude; and where power from the at least one motor is configured to descend (128) the at least one UAV to the first altitude after the Sun has set to conserve energy stored in the at least one battery.
Systems, devices, and methods including a battery pack (114) comprising: a case (116); and a battery (120) disposed in the case, where the battery comprises two or more modules (121, 123), where each module (121, 123) comprises two or more sets of battery cells (122, 125), and where each set of the two or more sets of battery cells is separated from an adjacent set of the two or more sets of battery cells by at least one heater (124) and at least one balancer (126).
In at least one embodiment, provided is a battery pack for a vehicle including a thin firebox for enclosing batteries and containing thermal runaway gases, thermal insulation surrounding the firebox, and a vent hole extending through the firebox and the thermal insulation to an exterior of the vehicle with vent hole plug and a pressure relief frangible vent cover at least partially covering the vent hole plug to retain it within the vent hole.
In one embodiment, a solar powered high altitude long endurance aircraft power bus architecture is provided which includes a main DC power bus, with a battery connected to the main DC power bus. This embodiment includes a plurality of solar panels coupled to the main DC power bus via a plurality of DC to DC converters such that each of the plurality of solar panels is coupled to the main power bus via one DC to DC converter of the plurality of DC to DC converters. A plurality of propeller drive units are coupled to the main DC power bus via a plurality of inverters such that each of the plurality of propeller drive units is coupled via an inverter to the main DC power bus.
In one embodiment a solar array circuit is provided capable of being utilized in a high altitude long endurance aircraft. The solar array circuit includes a solar array string having a plurality of solar cells connected in series. Multiple solar array strings are connected in parallel to form a solar array channel. A plurality of MOSFET switches are provided, each being connected in series to an output of the plurality of solar cells of a solar array string so as to allow each of the plurality of solar strings within the solar array channel to be independently disconnected and connected within the solar array channel.
In at least one embodiment, provided is a battery pack for a vehicle including battery pack for a vehicle, the battery pack having a firebox for enclosing batteries, an electronics compartment, thermal insulation surrounding the firebox and the electronics compartment, and heat pipes. The heat pipes may include firebox heat pipes contacting the firebox on an evaporator end and extending to an exterior surface of the battery pack on a condenser end, and electronics compartment heat pipes extending from within the electronics compartment on an evaporators end and extending through the thermal insulation to the exterior surface of the battery pack on a condenser end.
In one implementation in a high altitude long endurance solar powered aircraft, a method for controlling a solar cell array is provided which includes determining an operating point of the of the solar array, including regulating a current output of the solar array, monitoring a power output of the solar array, monitoring a voltage output of the solar array, and varying the current output of the solar array in response to the monitoring of the voltage output to maximize the power output of the solar array.
G05F 1/67 - Regulating electric power to the maximum power available from a generator, e.g. from solar cell
B64C 39/02 - Aircraft not otherwise provided for characterised by special use
G05F 1/26 - Regulating voltage or current wherein the variable is actually regulated by the final control device is AC using bucking or boosting transformers as final control devices combined with discharge tubes or semiconductor devices
H02S 40/34 - Electrical components comprising specially adapted electrical connection means to be structurally associated with the PV module, e.g. junction boxes
23.
SYSTEMS AND METHODS FOR DISTRIBUTED CONTROL COMPUTING FOR A HIGH ALTITUDE LONG ENDURANCE AIRCRAFT
Systems, devices, and methods including a first flight control computer (FCC) (112) of two or more FCCs (112, 113); a second FCC (113) of the two or more FCCs; at least one selector (182) in communication with the first FCC; and at least one watchdog window (180) in communication with the at least one selector (182), where the at least one watchdog window monitors a performance of the first FCC (112) based on an electrical pulse (192, 194, 196) emitted by the FCC (112); where the at least one watchdog window is configured to detect a fault pulse of the electrical pulse emitted by the first FCC; and where the selector is configured to toggle to the second FCC based on the detected fault pulse emitted by the first FCC.
G06F 11/08 - Error detection or correction by redundancy in data representation, e.g. by using checking codes
G06F 11/18 - Error detection or correction of the data by redundancy in hardware using passive fault-masking of the redundant circuits, e.g. by quadding or by majority decision circuits
24.
BATTERY PACK WITH HEATER/VOLTAGE EQUALIZER AND METHOD FOR HIGH ALTITUDE LONG ENDURANCE AIRCRAFT
In at least one embodiment, a battery pack for a high altitude long endurance aircraft including a plurality of cells, a thin sheet heater between two of the plurality of cells, a balance circuit connected to the plurality of cells to the thin sheet heater, a battery monitor circuit connected to the balance circuit for balancing charging, and a thermal monitor circuit connected to the thin sheet heater. In at least one implementation, a method is provided for a battery pack for a high altitude long endurance aircraft, which includes determining whether a battery pack needs thermal adjustment, adjusting a temperature of the battery pack using a thin sheet heater interposed between two cells of the battery pack, and balancing charging to at least one battery cell using the thin sheet heater.
G01K 13/00 - Thermometers specially adapted for specific purposes
G01R 31/36 - Arrangements for testing, measuring or monitoring the electrical condition of accumulators or electric batteries, e.g. capacity or state of charge [SoC]
H02J 7/00 - Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
H01M 10/48 - Accumulators combined with arrangements for measuring, testing or indicating the condition of cells, e.g. the level or density of the electrolyte
25.
SYSTEM AND METHOD FOR IMPROVED SOLAR CELL ARRAY EFFICIENCY IN HIGH ALTITUDE LONG ENDURANCE AIRCRAFT
In one embodiment, a solar array circuit for a high altitude long endurance aircraft, which includes a solar string having a plurality of solar cells connected in series. The solar string having a MOSFET switch connected in parallel with one or more solar cells in the solar string. A method comprising monitoring an output of a solar string, detecting whether a solar string is functioning within an acceptable range of operation, determining whether any of the solar cells in the solar string are functioning within an acceptable range of operation and bypassing any of the solar cells within the string that are not functioning within the acceptable range of operation so as to improve an efficiency of the solar string.
H02S 40/34 - Electrical components comprising specially adapted electrical connection means to be structurally associated with the PV module, e.g. junction boxes
H01L 31/042 - PV modules or arrays of single PV cells
H01L 31/044 - PV modules or arrays of single PV cells including bypass diodes
H02J 7/35 - Parallel operation in networks using both storage and other DC sources, e.g. providing buffering with light sensitive cells
26.
SYSTEM AND METHOD FOR SOLAR CELL ARRAY COMMUNICATION
In one implementation, a method for a solar cell array is provided, the method includes emitting a communication message from the solar cell array by reverse biasing the solar cell array so as to cause at least a portion of the solar array to emit a detectable amount of radiation corresponding to the communication message. In one embodiment a solar cell array circuit is provided including a solar string comprising a plurality of solar cells coupled together, a charge storage device coupled to a power bus, and a bidirectional boost-buck converter having a first and second pair of MOSFETs connected in series between positive and negative rails of the power bus with an inductor coupled from between the first and second paired MOSFETs to a charging output of the solar string.
In at least one embodiment, In at least one embodiment, provided is a battery pack for a vehicle, the battery pack including a battery cage comprising ends, wherein at least one of the ends is slidable with respect to an opposing end, battery cells seated within the cage, and wherein the cage comprising a string and pulley system including a plurality of pulleys mounted with the ends at upper and lower portions of the ends, a string connected between two ends of a spring and extending around the pulleys such that the spring tensions the string so as to bias the at least one end of the battery cage toward the opposing end.
Systems, devices, and methods for receiving, by a processor (1424) having addressable memory (1427), data representing a geographical area for imaging by one or more sensors of an aerial vehicle (1302); determining one or more straight-line segments covering the geographical area (1304); determining one or more waypoints located at an end of each determined straight-line segment (1306), where each waypoint comprises a geographical location, an altitude, and a direction of travel; determining one or more turnarounds (1308) connecting each of the straight-line segments, where each turnaround comprises one or more connecting segments; and generating, by the processor, a flight plan for the aerial vehicle (1314) comprising: the determined one or more straight-line segments and the determined one or more turnarounds connecting each straight-line segment.
G01C 23/00 - Combined instruments indicating more than one navigational value, e.g. for aircraftCombined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration
Systems, devices, and methods that may include: determining one or more take-off variables (700) for a vertical take-off and landing (VTOL) aerial vehicle (300); increasing an altitude of the VTOL aerial vehicle to a first altitude (706), where increasing the altitude comprises substantially vertical flight of the VTOL aerial vehicle; performing a first pre-rotation check of the VTOL aerial vehicle (708); adjusting a pitch of the VTOL aerial vehicle to a first pitch angle via motor control (710); adjusting the pitch of the VTOL aerial vehicle to a second pitch angle via at least one of: motor control and one or more effectors (712); and adjusting the pitch of the VTOL aerial vehicle to a third pitch angle via the one or more effectors (714), where the third pitch angle is substantially perpendicular to a vertical plane.
B64C 27/20 - Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
B64C 27/22 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
B64C 27/24 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with rotor blades fixed in flight to act as lifting surfaces
B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
B64C 27/28 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
B64C 27/30 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with provision for reducing drag of inoperative rotor
B64C 27/54 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
30.
METHODS AND SYSTEMS FOR UTILIZING DUAL GLOBAL POSITIONING SYSTEM (GPS) ANTENNAS IN VERTICAL TAKE-OFF AND LANDING (VTOL) AERIAL VEHICLES
Systems, devices, and methods for a vertical take-off and landing (VTOL) aerial vehicle (800) having a first GPS antenna (810) and a second GPS antenna (816), where the second GPS antenna is disposed distal from the first GPS antenna; and an aerial vehicle flight controller (550), where the flight controller is configured to: utilize a GPS antenna signal via the GPS antenna switch from the first GPS antenna or the second GPS antenna; receive a pitch level of the aerial vehicle from the one or more aerial vehicle sensors in vertical flight or horizontal flight; determine if the received pitch level is at a set rotation from vertical or horizontal; and utilize the GPS signal not being utilized via the GPS antenna switch if the determined pitch level is at or above the set rotation.
A method and system including: defining a geographic area (220, 502); receiving a plurality of images (202, 204, 206, 208, 210, 212, 214, 216); determining a plurality of image points (510); partitioning the geographic area into a plurality of image regions (512) based on the plurality of image points; and stitching the plurality of images into a combined image (520) based on the plurality of image regions.
A method and system including: an aerial vehicle (1102) including: a first camera (1108) comprising a first sensor having at least red, green, and blue color channels, where the blue color channel is sensitive to near-infrared (NIR) wavelengths; a first optical filter (1109) disposed in front of the first sensor, wherein the first optical filter is configured to block wavelengths below green, between red and NIR, and longer wavelength NIR; a processor (1114) having addressable memory in communication with the first camera, where the processor is configured to: capture at least one image of vegetation from the first camera; provide red, green, and NIR color channels from the captured image from the first camera; and determine at least one vegetative index based on the provided red, green, and NIR color channels.
H04N 3/14 - Scanning details of television systemsCombination thereof with generation of supply voltages by means not exclusively optical-mechanical by means of electrically scanned solid-state devices
33.
SYSTEM AND METHOD FOR INTERCEPTION AND COUNTERING UNMANNED AERIAL VEHICLES (UAVS)
Systems, devices, and methods for identifying (302) a target aerial vehicle (104), deploying (304) an interceptor aerial vehicle (102) comprising at least one effector (134), maneuvering the interceptor aerial vehicle to a position to engage the target aerial vehicle (306), deploying the at least one effector to intercept the target aerial vehicle (312), and confirming that the target aerial vehicle has been intercepted (314).
An aircraft including a wing system, a plurality of control surfaces, a camera mounted on a camera pod, and a control system. The camera pod is configured to vary the orientation of the camera field of view only in yaw, relative to the aircraft, between a directly forward-looking orientation and a side-looking orientation. The control system controls the control surfaces such that they induce a significant aircraft yaw causing an identified target to be within the field of view of the camera with the camera in the directly forward-looking orientation.
Systems, devices, and methods for an extruded wing protection and control surface (126) comprising: a channel (206) proximate a leading edge (202) of the control surface, a knuckle (210) disposed about the channel, a leading void (212), a trailing void (214), and a separator (216) dividing the leading void and the trailing void; and a plurality of notches (200) disposed in the extruded control surface proximate the leading edge of the control surface.
Systems, devices, and methods for a safety system including: selecting an unmanned aerial vehicle (UAV) command (602, 604, 606) on a controller (104), the controller comprising a first processor (1324) with addressable memory (1327); presenting a first activator (430) and a second activator (420) on a display (400) of the controller for the selected UAV command, wherein the second activator is a slider (410); and sending the UAV command to a UAV (100) if the first activator and the second activator are selected, the UAV comprising a second processor (1324) with addressable memory (1327).
G05D 1/00 - Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
G06F 19/00 - Digital computing or data processing equipment or methods, specially adapted for specific applications (specially adapted for specific functions G06F 17/00;data processing systems or methods specially adapted for administrative, commercial, financial, managerial, supervisory or forecasting purposes G06Q;healthcare informatics G16H)
H04N 7/18 - Closed-circuit television [CCTV] systems, i.e. systems in which the video signal is not broadcast
H04N 21/236 - Assembling of a multiplex stream, e.g. transport stream, by combining a video stream with other content or additional data, e.g. inserting a URL [Uniform Resource Locator ] into a video stream, multiplexing software data into a video streamRemultiplexing of multiplex streamsInsertion of stuffing bits into the multiplex stream, e.g. to obtain a constant bit-rateAssembling of a packetised elementary stream
37.
VERTICAL TAKE-OFF AND LANDING (VTOL) WINGED AIR VEHICLE WITH COMPLEMENTARY ANGLED ROTORS
Systems, devices, and methods for an aircraft having a fuselage (110); a wing (120) extending from both sides of the fuselage; a first pair of motors (132b, 133b) disposed at a first end of the wing; and a second pair of motors (142b, 143b) disposed at a second end of the wing; where each motor is angled (381, 382, 391, 392) to provide a component of thrust by a propeller (134, 135, 144, 145) attached thereto that for a desired aircraft movement applies a resulting torque additive to the resulting torque created by rotating the propellers.
B64C 29/02 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
A lidar system, including a base, a sensor body, and a motor having a shaft. The motor is affixed to the base, and can drive the sensor body in rotation with respect to the base. An LED device and a light sensor are each mounted upon the sensor body. A data processing device is also mounted upon the sensor body, and is programmed to produce range information based upon the sensor data. The shaft carries two slip rings. The LED, the sensor and the data processing device all receive electrical power via the two slip rings. The data processing device is configured to transmit the range information via the two slip rings using pulse width modulation.
In one possible embodiment, a system capable of a self-propagating data link includes an unmanned vehicle having a data link transceiver and at least one deployable data link transceiver. The unmanned vehicle having a deployment means for deploying the at least one deployable data link transceiver.
A method of targeting, which involves capturing a first video of a scene about a potential targeting coordinate by a first video sensor (102) on a first aircraft (100); transmitting the first video (232) and associated potential targeting coordinate by the first aircraft; receiving the first video on a first display in communication with a processor, the processor also receiving the potential targeting coordinate; selecting the potential targeting coordinate to be an actual targeting coordinate (226) for a second aircraft (116) in response to viewing the first video on the first display; and guiding a second aircraft toward the actual targeting coordinate; where positive identification of a target (114) corresponding to the actual targeting coordinate is maintained from selection of the actual targeting coordinate.
G01C 22/00 - Measuring distance traversed on the ground by vehicles, persons, animals or other moving solid bodies, e.g. using odometers or using pedometers
41.
BATTERY WATERING EVENT DETECTION USING A TEMPERATURE SENSOR
A method of battery cell monitoring includes measuring a temperature of an electrolyte (block 700) in a battery cell using a temperature sensor, outputting from the temperature sensor a plurality of electrolyte temperature signals (block 710) indicative of the temperature of the electrolyte over time, providing the plurality of electrolyte temperature signals to a system controller (block 710), determining by the system controller a sudden transition in the electrolyte temperature signals (block 720), and logging a watering event data indication (block 725) in a memory in response to calculating the sudden transition.
G01R 31/36 - Arrangements for testing, measuring or monitoring the electrical condition of accumulators or electric batteries, e.g. capacity or state of charge [SoC]
H01M 2/36 - Arrangements for filling, topping-up or emptying cases with or of liquid, e.g. for filling with electrolytes, for washing-out
H01M 10/48 - Accumulators combined with arrangements for measuring, testing or indicating the condition of cells, e.g. the level or density of the electrolyte
42.
SYSTEM MONITORING POWER CONNECTOR AND CABLE HEALTH
A method of protecting an electric vehicle (EV) charger connector 200 from excessive heat includes monitoring the internal temperature of an electrical connector (block 1500), the electrical connector 200 having pilot and pilot return signal lines (235, 240), reducing a voltage between the pilot and pilot return signal lines (block 1515) in response to the internal temperature exceeding a first threshold (block 1505), and reducing charging current provided through the electrical connector in response to the change in voltage (block 1520) so that the internal temperature exceeding the first threshold will result in a reduction of charging current through the connector.
A shock resistant fuselage system includes first and second fuselage side walls (804, 806), each of the first and second fuselage side walls (804, 806) having a plurality of guide posts (802, 1006), and a printed circuit board (PCB) 800 rigidly attached to at least one of the first and second fuselage side walls (804, 806), the PCB 800 having a plurality of guide slots 1008, each of the plurality of guide posts (802, 1006) slideably seated in a respective one of the plurality of guide slots 1008 so that elastic deformation of the PCB 800 is guided by the guide slots 1008 between the first and second fuselage side walls (804, 806).
A vertical take-off and landing (VTOL) unmanned aerial vehicle (UAV) storage and launch system includes a UAV pod (108) having a UAV pod processor (114) and a UAV (102) selectively enclosed in the UAV pod (108), the UAV (102) having only two rotors (202).
A method of unmanned aerial vehicle (UAV) operation, including: receiving from a customer a first data request (400), the first data request (400) having: 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 (404), and deploying the UAV pod (802).
A method of migrating unmanned aerial vehicle operations between geographic survey areas, including: uploading a first plurality of flight missions into a first UAV pod; deploying the UAV pod; autonomously launching the UAV and providing first survey data from the UAV to the UAV pod; autonomously migrating the UAV from the first UAV pod to a second UAV pod; receiving a second plurality of flight missions in a second UAV pod; providing the UAV with one of the second plurality of flight missions from the second UAV pod; autonomously launching the UAV and providing a second survey data from the UAV to the second UAV pod; where the autonomous migrating of the UAV to accomplish the first and second survey data happens autonomously and without active human intervention.
G01C 23/00 - Combined instruments indicating more than one navigational value, e.g. for aircraftCombined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration
47.
POD COVER SYSTEM FOR A VERTICAL TAKE-OFF AND LANDING (VTOL) UNMANNED AERIAL VEHICLE (UAV)
An unmanned aerial vehicle (UAV) storage and launch system includes a UAV pod 108 having an open position and a closed position, the closed position establishing an interior 106 that is weather resistant to an environment external to the UAV pod 108 and a vertical takeoff and landing (VTOL) UAV 102 enclosed in the UAV pod 108 so that the UAV pod 108 in the closed position provides a weather resistant interior 106 for the VTOL UAV 102.
An unmanned aerial vehicle (UAV) storage and launch system, including: a UAV pod 600 having an interior 700; and a telescoping UAV landing surface 702 disposed in the interior 700 of the UAV pod 600; where the telescoping UAV landing surface 702 may translate up toward a top opening 704 of the UAV pod 600, translate down into an interior 700 of the UAV pod 600, or rotate relative to the UAV pod 600.
A vertical take-off and landing (VTOL) unmanned aerial vehicle (UAV) system including: a rearward facing tang 216 extending from a rear fuselage portion 218 of a VTOL UAV 102, one or more metallic contacts 224 disposed on an exterior surface of the tang 216, a UAV pod 108 including a landing surface 104; and an opening 105 disposed in the landing surface 104 to receive the tang 216.
A system having a damper (102) with six or more indentations (202, 204, 206, 208, 214, 216, 218, 220) on alternating sides (201, 215) of the damper, where each indentation is open to an outer circumferential surface (211) of the damper and extends over halfway through a width (223) of the damper, and six or more slots (210), each slot open to an undulating inner circumferential surface (213) of the damper and extending through the width of the damper.
Systems, devices, and methods for determining, by a processor (304), an unmanned aerial system (UAS) (200) position relative to at least one flight boundary (206, 208, 210); and effecting, by the processor, at least one flight limitation of a UAS if the determined UAS position crosses the at least one flight boundary.
A method of charging an electric vehicle (EV) includes receiving a user's authentication code in an electric vehicle service equipment (EVSE) from a user's mobile device [block 402], comparing in the EVSE the user's authentication code to a whitelist having a plurality of authorized user authentication codes [block 404], 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 [blocks 406, 408] so that a user's authentication code is authenticated to enable the EV charging transaction without concurrent access to an EVSE-related remote server.
Systems, devices, and methods for impacting, by a small unmanned aerial vehicle (SUAV) (109), a net (124) having at least three sides; and converting the kinetic energy of the SUAV (109) into at least one of: elastic potential energy of one or more tensioned elastic cords (128, 130) connected to at least one corner of the net (124), gravitational potential energy of a frame member (104) connected to at least one corner of the net (124), rotational kinetic energy of the frame member (104) connected to at least one corner of the net (124), and elastic potential energy of the frame member (104) connected to at least one corner of the net (124).
A system having: a processor (1024) and addressable memory (1027), where the processor (1024) is configured to: receive (206) a geographic data defining a selected geographical area; receive (206) an operating mode associated with the selected geographical area, where the received operating mode restricts at least one of: a viewing of a UAV data and a recording of the UAV data by at least one user device; and broadcast (208) the UAV data to the at least one user device based on the selected geographical area and the received operating mode.
A remote targeting system includes a weapon (110), a display (120) on the weapon (110), a radio frequency (RF) receiver (140), a sensor (150) remote from the weapon (110), wherein the sensor (150) is configured to provide image metadata of a predicted impact point B on the weapon display (120), and a targeting device (130) including a data store (537) having ballistic information associated with a plurality of weapons and associated rounds, and a fire control controller (532) wherein the fire control controller (532) determines a predicted impact point B based on the ballistic information, elevation data received from an inertial measurement unit (534), azimuth data received from a magnetic compass (535), position data received from a position determining component (536), wherein the fire control controller (532) is in communication with the inertial measurement unit (534), the magnetic compass 535, and the position determining component (536).
G06G 7/80 - Analogue computers for specific processes, systems, or devices, e.g. simulators for gun-layingAnalogue computers for specific processes, systems, or devices, e.g. simulators for bomb aimingAnalogue computers for specific processes, systems, or devices, e.g. simulators for guiding missiles
A method of driving an isolated converter 200 includes opening a first bi-directional switch 206 on an input side of a transformer 214, accepting current into a resonant capacitor 210 connected across the first bi-directional switch 206 to reduce voltage across the first bi-directional switch 206 in response to said opening the first bi-directional switch 206, reversing current out of the resonant capacitor 210, and closing the first bi-directional switch 206 as voltage across the first bi-directional switch 206 is approximately zero volts.
A flight control apparatus for fixed-wing aircraft includes a first port wing (115) and first starboard wing (120), a first port swash plate (145) coupled between a first port rotor 155) and first port electric motor (135), the first port electric 5 motor (135) coupled to the first port wing (115), and a first starboard swash plate (150) coupled between a first starboard rotor (130) and first starboard electric motor (140), the first starboard electric motor (140) coupled to the first starboard wing (120).
B64C 29/02 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
58.
ELECTRIC PLUG ADAPTER HAVING SOCKET KEY SAFETY SYSTEM
An electric vehicle ("EV") charger plug adapter apparatus (800) includes an adapter housing (805), a socket (810) extending into a first side (820) of the adapter housing (805), the socket configuration defined by a first technical standard for use with at least one of a first current or voltage rating, a plug (130) extending from a second side (150) of the adapter housing (805), the plug configuration defined by a second technical standard for use with at least one of a second current or voltage rating, and a key (827) extending from the first side (820) of the adapter housing (805), wherein the key (827) prevents seating of a second plug (815) into the socket if the second plug does not have a complementary key socket (330) to fit the key (827).
An unmanned aerial vehicle (UAV) launch tube (100) that has at least one layer of prepeg substrate disposed about an aperture (106) to form a tube, a sabot (110) disposed in an interior of said tube (100), said sabot (110) having a first clasp tab (126), and a clasp (124) detachably coupled to said first clasp tab and contacting an inner circumferential wall (102) of said tube (100) so that said clasp (124) is rotationally constrained by the inner circumferential wall (102) and said first clasp tab (126).
An electric vehicle service equipment (EVSE) system includes an EVSE case having a front plug face, a rear face, and left and right gripping sides that collectively define a trapezoidal prism cross section, the left and right gripping sides further having left and right convex gripping portions, respectively, a relay positioned within the EVSE case, and a controller positioned within the EVSE case and in communication with the relay, the controller responsive to a pilot duty signal, when a pilot duty signal is present.
In at least one embodiment, provided is an electric vehicle supply equipment having a line power contactor including a first line power input and a second line power input and a first line power output and a second line power output. It further has a welded contactor detector with a contactor sense circuit, the sense circuit having a first line shunt resistor network connected from the first line power contactor output to ground and a second line shunt resistor network connected from the first line power contactor output to ground. In another embodiment provided is an EVSE including a welded contactor detector with a contactor sense circuit having a bias resistor connected between the hot line relay input and the neutral line relay output.
In some embodiments, the present invention includes the use of one or more electric power supply system, or systems, and the electric vehicle, or vehicles, connected thereto, to provide load-based utility grid frequency regulation by varying the amount of power drawn by the vehicle or vehicles.
H02J 3/04 - Circuit arrangements for ac mains or ac distribution networks for connecting networks of the same frequency but supplied from different sources
63.
LAUNCH TUBE RESTRAINT SYSTEM FOR UNMANNED AERIAL VEHICLE (UAV)
An unmanned aerial launch vehicle (UAV) launch apparatus is disclosed that includes a UAV (400) having an exterior surface, an aerial vehicle (AV) tab (510) extending from the exterior surface, a tube (440) containing the UAV (400), the tube (440) including a tab stop (515) configured to controllably hinder travel of the AV tab (510) past the tab stop (515), and a pair of opposing tab guides (700, 705) configured to position the AV tab (510) for travel over the tab stop (515).
F41F 3/04 - Rocket or torpedo launchers for rockets
F41A 15/00 - Cartridge extractors, i.e. devices for pulling cartridges or cartridge cases at least partially out of the cartridge chamberCartridge ejectors, i.e. devices for throwing the extracted cartridges or cartridge cases free of the gun
B64F 1/04 - Ground or aircraft-carrier-deck installations for launching aircraft
B64C 1/00 - FuselagesConstructional features common to fuselages, wings, stabilising surfaces or the like
A vehicle having a wing, a forward propeller configured for forward flight, and an aft propeller configured for submerged travel in a rearward direction. The vehicle center of mass is aft of its floating center of buoyancy, and center of mass and the floating center of buoyancy lie between the first and second propellers. The vehicle has a natural floating orientation in which the vehicle, while floating, has its first propeller located in the air and positioned for initiating airborne flight in a forward direction, and in which the vehicle has its second propeller located in the liquid and positioned for initiating submerged travel in a rearward direction.
A water-tight or air-tight accessible compartment has a removable hatch sealed at the edge with elastically conformable opposing seals, with elongate communication elements extending into the compartment between the opposing seals, seals conforming to the topology formed between the compartment edge and the elongate communication elements.
A rotorcraft including a fuselage, one or more motor-driven rotors for vertical flight, and a control system. The motors drive the one or more rotors in either of two directions of rotation to provide for flight in either an upright or an inverted orientation. An orientation sensor is used to control the primary direction of thrust, and operational instructions and gathered information are automatically adapted based on the orientation of the fuselage with respect to gravity. The rotors are configured with blades that invert to conform to the direction of rotation.
B64C 27/28 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
67.
ELECTRIC VEHICLE CHARGER DISPLAY SYSTEM FOR DISTANT AND LOCAL VIEWING
An electric vehicle (EV) charger system, includes an EV charger (100), the EV charger (100) having a distance display (105) disposed at a top portion (115) of the EV charger (100), the EV charger (100) configured to display a non-alphanumeric representation of a plurality of modes of the EV charger (100) on the distance display (105) for viewing by an observer remote from the EV charger (100), and a near display (110) disposed at a position on the EV charger (100) that is below the distance display (105), the EV charger (100) configured to display alphanumeric information on the near display (110) for viewing by a user proximal to the EV charger (100).
A system and method for transmitting still images and a video feed from an unmanned aerial vehicle to a ground station is disclosed. The system includes an aircraft including a digital camera to capture still and video images of an object. A video encoder is coupled to the camera to provide a video output including video packets. A file server is coupled to the camera to provide an image output including image data packets. A multiplexer is coupled to the video and still image output. The multiplexer produces a data transmission including video and image data packets. A transmitter sends the data transmission to the ground station. The ground station receives the data transmission and demultiplexes the packets into separate video and image data packets. The ground control station may select the ratio the video stream images in relation to the still image to be transmitted from the aircraft.
In one embodiment, a ball turret assembly for supporting a camera includes 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 first guide disposed at least partially circumferentially on the first shaft proximally to the first exit port is provided, and a cable extends along the interior region of the first shaft and exits 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.
A turret assembly for attachment on the undersurface of an aircraft that reduces performance limitations due to gimbal lock and reduces the cross section profile of the assembly. The assembly includes a roll actuator including a drive shaft. A yoke having a cross member is coupled to the drive shaft and a pair of prongs. The yoke is rotated via the roll actuator and drive shaft along a roll axis oriented substantially parallel to the body of the aircraft. A turret is mounted on the prongs of the yoke. A tilt actuator is contained within the turret. The tilt actuator tilts the turret on a tilt axis relative to the yoke. The tilt axis is perpendicular to the roll axis.
An unmanned aerial vehicle (UAV) includes a fuselage, a gimbal-mounted turret having one or more degrees of freedom relative to the fuselage, a camera disposed in the gimbal- mounted turret for motion therewith in the one or more degrees of freedom, and a central video image processor disposed exteriorly of the gimbal-mounted turret, the central video image processor configured to receive and process image data from the camera.
H04N 3/16 - Scanning details of television systemsCombination thereof with generation of supply voltages by means not exclusively optical-mechanical by deflecting electron beam in cathode-ray tube
A water resistant and electromagnetically shielded turret assembly, suitable for attachment to the undersurface of an unmanned surveillance aircraft. The turret, in its several variations, may contain one or more cameras, and may contain an internal positioning motor, which can be easily accessible for servicing.
An aircraft apparatus is disclosed that has a fuselage boom (102) having proximal (110) and distal (103) ends, a wing (108) coupled to a proximal end (110) of the fuselage boom (102) and at least one transparent stabilizer (104, 106) coupled to a distal end (103) of the fuselage boom (102).
A motor assembly that includes a motor (102) having a motor casing (112), a rotatable shaft (100) extending from said motor casing (112) to a shaft length and a hub (106) coupled to said rotatable shaft (100), the hub (106) having a circumferential skid surface (107) disposed immediately proximal to the motor casing (112) and having a channel configured to seat a propeller, when a propeller is present, wherein a bending moment applied to the shaft (100) through the hub (106) results in the circumferential skid surface (107) contacting said motor casing (112).
A motor assembly that includes a motor (102) having a rotatable shaft (100), a hub (106) coupled to the rotatable shaft (100), the hub (106) having a propeller indexer (118) to receive a propeller (104), when the propeller (104) is present, a sensor trigger (108) rotatable with the shaft (100) and positioned at a propeller offset angle θPROP from the propeller indexer (118), and a sensor (110) coupled to the motor and positioned to detect the sensor trigger (108) so that the propeller indexer (118) may be positioned at the propeller offset angle θPROP from the sensor (110) through rotation of the shaft (100) so that said sensor (110) is proximate to the sensor trigger (108).
An aircraft defining an upright orientation and an inverted orientation, a ground station; and a control system for remotely controlling the flight of the aircraft. The ground station has an auto-land function that causes the aircraft to invert, stall, and controllably land in the inverted orientation to protect a payload and a rudder extending down from the aircraft. In the upright orientation, the ground station depicts the view from a first aircraft camera. When switching to the inverted orientation: (1 ) the ground station depicts the view from a second aircraft camera, (2) the aircraft switches the colors of red and green wing lights, extends the ailerons to act as inverted flaps, and (3) the control system adapts a ground station controller for the inverted orientation. The aircraft landing gear is an expanded polypropylene pad located above the wing when the aircraft is in the upright orientation.
In an energy management and conversion system for charging an electric vehicle, plural energy sources are coupled to a DC bus through respective converters, and respective voltage set points are provided for the respective converters, each converter controlling flow of energy between the DC bus and the respective energy source by determining whether the voltage of the DC bus is less than the respective voltage set point.
A system for managing heat transfer is provided by the present disclosure, which in one form includes a cavity (16) having an inner wall portion (24), at least one heat-generating component (20) disposed within the cavity, and a plurality of heat conducting members (30) disposed adjacent one another. Each heat conducting member includes a resilient core (32) and an outer shell (34) wrapped around at least a portion of the resilient core. The outer shell is made of a material having a relatively high thermal conductivity, and the plurality of heat conducting members are positioned between the heat-generating component and the inner wall portion of the cavity.
A heat transfer system is provided by the present disclosure that includes, in one form, a structural member having an upper skin (52), a lower skin (54), and a foam core (56) disposed between the upper skin and the lower skin. At least one heat conducting array (60) extends through the foam core and between the upper skin and the lower skin, the heat conducting array defining at least one upper cap (62), at least one lower cap (64), and a wall portion (66) extending between the upper cap and the lower cap, the upper cap being disposed proximate a heat source (20). A heat conducting spreader (68) is disposed between the lower cap of the heat conducting array and the lower skin of the structural member.
In one implementation, a method is provided for contactor monitoring and control in electric vehicle supply equipment, which includes updating an open error count and a close error count based on a detected condition of the contactor. The method also includes determining a detected state of the contactor by comparing the open error count and the close error count to maximum and minimum values. The method further includes performing at least one of controlling the state of the contactor based on the determined contactor state, or providing a visual indicator based on the determined contactor state.
A pitot tube system having a pitot tube containing a porous hydrophobic fabric that blocks water and contaminants from reaching a pressure sensor. The distance in the pitot tube between the fabric and a front orifice of the tube is less than 2.4 times the height of the orifice, and preferably less than or equal to.38 times the height. The section of the tube through which the fabric extends defines an opening characterized by a minimum dimension greater than.15 inches, and preferably being at least.21 inches. The tube is a removable structure that attaches to a mount that forms a passage for communicating the pressure in the tube. That passage contains a second porous hydrophobic fabric that also blocks water and contaminants from reaching a pressure sensor.
An aircraft defining an upright orientation and an inverted orientation, a ground station; and a control system for remotely controlling the flight of the aircraft. The ground station has an auto-land function that causes the aircraft to invert, stall, and controllably land in the inverted orientation to protect a payload and a rudder extending down from the aircraft. In the upright orientation, the ground station depicts the view from a first aircraft camera. When switching to the inverted orientation: (1 ) the ground station depicts the view from a second aircraft camera, (2) the aircraft switches the colors of red and green wing lights, extends the ailerons to act as inverted flaps, and (3) the control system adapts a ground station controller for the inverted orientation. The aircraft landing gear is an expanded polypropylene pad located above the wing when the aircraft is in the upright orientation.
An asymmetric brushless direct current (DC) motor (100) having a stator (104) having a plurality of magnets (108) and a rotor (202) having a plurality of armatures (204) where the vector sum of magnetic forces between each armature (204) and each respective magnet (208) is zero at every angular rotation position of the rotor (202) with respect to the stator (104) in the motor's (100) non-energized state.
An electric motor controller system (400) for modulating requested motor torque via oscillating the instantaneous torque, including a bi-stable torque controller (419); a proportional-integral (PI) velocity controller (416); a proportional-integral-differential (PID) position controller (413); and sinusoidal zero-velocity table mapping (421).
In one implementation a method is provided for filtering a detected pilot signal. The method includes storing a pilot signal sample in a first in first out memory, sorting the pilot signal samples, and determining an average value of a subgroup of the sorted pilot signal samples. The method further includes controlling application of utility power to an electric vehicle based on the average value of the subgroup.
In one implementation, a method is provided to detect a ground fault. This includes applying a pulsed test impedance and detecting a utility power voltage with and without the pulsed test impedance applied. It further includes detecting a test current through the pulsed test impedance to ground and determining whether a ground fault exists based on the detected test current and the detected utility power voltage with and without the pulsed test impedance applied.
An energy management system for controlling electric vehicle charging by managing plural local energy sources to optimize charging speed and minimize energy cost and provide backup power in the event of a utility grid power outage.
In electric vehicle supply equipment (EVSE), interruption of charging due to overheating is prevented by adjusting the pulse duty cycle on the control pilot conductor communicating the maximum allowed current level to the electric vehicle, the adjustment being performed whenever the EVSE temperature exceeds a predetermined threshold temperature below the maximum operating temperature as a function of the approach of the temperature to the maximum operating temperature.
H02J 7/02 - Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries for charging batteries from AC mains by converters
A system comprising an unmanned aerial vehicle (UAV) (100) having wing elements (141, 142) and tail elements (143, 144) configured to roll to angularly orient the UAV (100) by rolling so as to align a longitudinal plane of the UAV, in its late terminal phase, with a target. A method of UAV body re-orientation comprising: (a) determining by a processor (940) a boresight angle error correction value (850) bases on distance between a target point (812) and a boresight point (820) of a body-fixed frame; and (b) effecting a UAV maneuver comprising an angular role rate component translating the target point (812) to a re-oriented target point (814) in the body-fixed frame, to maintain the offset angle via (850) the offset angle correction value.
A flapping wing driving apparatus includes at least one crank gear capstan (1207) rotatably coupled to a crank gear (1202), the at least one crank gear capstan (1207) disposed radially offset from a center of rotation (1204) of the crank gear (1202); a first wing capstan (1212) coupled to a first wing (1800), the first wing capstan (1212) having a first variable-radius drive pulley portion (1226); and a first drive linking member (1208) configured to drive the first wing capstan (1221), the first drive linking member (1208) windably coupled between the first variable-radius drive pulley portion (1226) and one of the at least one crank gear capstan (1207); wherein the first wing capstan (1212) is configured to non-constantly, angularly rotate responsive to a constant angular rotation of the crank gear (1202).
In various implementations, method is provided for reducing noise in a pilot signal, which may include sampling the pilot signal and creating a first data set comprising the samples of the pilot signal samples. It may also include selecting a first subset from the first data set and averaging the first subset to produce a first tier averaged output of the selected first subset. It may further include creating a second data set of the first tier averaged outputs and selecting a second subset from the second data set and averaging the second subset to produce the pilot signal output. In various embodiments, this method may further include, or separately include generating the pilot signal with a modulation rate within an allowable range and offset from a central modulation rate of the allowable range.
Methods and devices for testing an electric vehicle direct charge device (110) via a quick (direct) charger connector (410) for low and zero voltage testing (640) according to a direct charge protocol of an electric vehicle (EV) or an EV simulator. A first jumper pin (471) is disposed between the ground terminal (450) and the charging permission terminal (440) of a direct charger connector (410). A second jumper pin (472) is disposed between the positive power supply terminal (420) and the negative power supply terminal (430) of the direct charger connector (410).
A portable electric vehicle supply equipment (EVSE) kit or system includes a docking connector having a docking head engagable with the charging port of an electric vehicle and a barrel or handle fixed to the docking head and having a barrel electrical connector. An EVSE controller is embedded within the docking connector. An electric power cable has a first connector for engaging the barrel electrical connector and a second connector at an opposite end of the cable for connection to an electrical utility receptacle. The embedded EVSE controller enables the docking connector to function as an EVSE unit.
A system and method for managing information relating to one or more electric vehicles (EVs) associated with a subscriber who is a member of one or more subscriber networks that provide EV charging services includes associating a plurality of the subscriber networks with a network administrator, and performing an information exchange in which information relating to an EV is delivered from a first subscriber network to a second subscriber network.
An electric vehicle ("EV") charging cable apparatus is disclosed that includes a charging cable segment (300) having first and second ends (305, 310), the charging cable segment having a power line segment (610) and a data line segment (620, 630, 635, 640, 645, 650); a first element (600) disposed at the first end of the charging cable segment, the first element configured to receive a direct current (DC) electric vehicle connector; a DC electric vehicle connector (605) disposed at the second end of the charging cable segment; and a tap coupled to at least one of the power line segment and the data line segment (320) so that the at least one of the power line segment and the data line segment are tapped for external access.
H02J 7/14 - Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries for charging batteries from dynamo-electric generators driven at varying speed, e.g. on vehicle
96.
HEAT SINK ACCESS PANEL FOR ELECTRIC VEHICLE SERVICE EQUIPMENT
A heat sink apparatus includes a plurality of spaced-apart vanes (402) extending between first and second opposing walls (408, 404), each of the plurality of spaced-apart vanes (402) being non-planar, a hinged access panel (106) of an electric vehicle service equipment, and at least one fan (702) coupled between the first opposing wall (404) and the access panel (106), the at least one fan (702) disposed in complementary opposition to at least one fan aperture (608) in the first opposing wall (408) to communicate air across the plurality of spaced-apart vanes (402).
F28D 1/06 - Heat-exchange apparatus having stationary conduit assemblies for one heat-exchange medium only, the media being in contact with different sides of the conduit wall, in which the other heat-exchange medium is a large body of fluid, e.g. domestic or motor car radiators with the heat-exchange conduits forming part of, or being attached to, the tank containing the body of fluid
97.
RANDOM RESTART APPARATUS AND METHOD FOR ELECTRIC VEHICLE SERVICE EQUIPMENT
An electric vehicle (EV) charger restart method include determining a respective restart delay time (Tdel) for each of one or more electric vehicle chargers (block 214), each respective restart delay time (Tdel)) comprising a respective delay time increment based on a generated random number and a group time interval for reset (Tint) (block 212), and initiating a restart of at least one of the one or more electric vehicle chargers, if an existing time (Tnow) is greater than an established time line start time (TPOK) plus Tdel) (blocks 210, 218).
In one possible embodiment, an amphibious unmanned aerial vehicle is provided, which includes a fuselage comprised of a buoyant material. Separators within the fuselage form separate compartments within the fuselage. Mounts associated with the compartments for securing waterproof aircraft components within the fuselage. The compartments each have drainage openings in the fuselage extending from the interior of the fuselage to the exterior of the fuselage.
In one implementation, the method for processor based automated testing of ground fault interrupt circuit for electric vehicle supply equipment is provided. In one implementation the method includes providing a simulated ground fault signal to a ground fault interrupt circuit and detecting at a processor that the ground fault interrupt circuit sensed the simulated ground fault signal. The method further includes commanding from the processor a utility power contactor to close while the ground fault interrupt circuit is disabling closing of the contactor and verifying the utility power contactor is not closed in response to commanding the utility power contactor to close.
B60K 28/10 - Safety devices for propulsion-unit control, specially adapted for, or arranged in, vehicles, e.g. preventing fuel supply or ignition in the event of potentially dangerous conditions responsive to conditions relating to the vehicle
100.
UAV PAYLOAD MODULE CAMERA ASSEMBLY AND RETRACTION MECHANISM
In one possible embodiment, a UAV payload module retraction mechanism is provided including a payload pivotally attached to a housing. A biasing member is mounted to bias the payload out of the housing and a winch is attached to the payload. An elongated flexible drawing member is coupled between the housing and the winch, the elongated drawing flexible member being capable of being drawn by the winch to retract the payload within the housing.
patents
