Systems, devices, and methods including a leading edge tubular member; an upper tubular member; a lower tubular member; one or more upper rib members connected between the leading edge tubular member and the upper tubular member; one or more lower rib members connected between the leading edge tubular member and the lower tubular member; a rigid sandwich shell disposed between the upper tubular member and the leading edge tubular member; and a sandwich shear web disposed between the upper tubular member and the lower tubular member; where the rigid sandwich shell and the sandwich shear web form a D-shape.
Systems, devices, and methods including one or more rib mounting flanges, where each rib mounting flange comprises: a spar opening configured to receive a main spar of a wing panel; one or more holes for receiving cross-bracing cables; and one or more holes for receiving cross-bracing cables; and one or more holes for connecting the rib mounting flange to an adjacent rib mounting flange.
Systems, devices, and methods for determining, by a processor, an unmanned aerial system position relative to at least one flight boundary; and effecting, by the processor, at least one flight limitation of a flight limiting device if the determined unmanned aerial system position crosses the at least one flight boundary.
A payload delivery device configured to deliver an aircraft deployed payload along a flight path to a predetermined landing destination includes a support member configured to be removably attached to the payload, a flight control and navigation system module configured to control orientation of the plurality of control surfaces while the payload is travelling along the flight path to the predetermined landing destination, a control surface assembly module including a plurality of control surfaces, a rotor assembly including a plurality of rotor blades having a central axis of rotation, and a collective control assembly module including at least one collective servomotor configured to control a plurality of control linkages connected to the plurality of rotor blades.
B64U 30/293 - Foldable or collapsible rotors or rotor supports
B64U 70/20 - Launching, take-off or landing arrangements for releasing or capturing UAVs in flight by another aircraft
B64U 101/60 - UAVs specially adapted for particular uses or applications for transporting passengersUAVs specially adapted for particular uses or applications for transporting goods other than weapons
A payload delivery device configured to deliver an aircraft deployed payload along a flight path to a predetermined landing destination includes a support member configured to be removably attached to the payload, a flight control and navigation system module configured to control orientation of the plurality of control surfaces while the payload is travelling along the flight path to the predetermined landing destination, a control surface assembly module including a plurality of control surfaces, a rotor assembly including a plurality of rotor blades having a central axis of rotation, and a collective control assembly module including at least one collective servomotor configured to control a plurality of control linkages connected to the plurality of rotor blades.
B64U 30/293 - Foldable or collapsible rotors or rotor supports
B64U 70/20 - Launching, take-off or landing arrangements for releasing or capturing UAVs in flight by another aircraft
B64U 101/60 - UAVs specially adapted for particular uses or applications for transporting passengersUAVs specially adapted for particular uses or applications for transporting goods other than weapons
10.
SYSTEMS AND METHODS FOR STARTING A SENSORLESS MOTOR
Systems, devices, and methods for: an unmanned aerial vehicle (UAV); at least one sensorless motor of the UAV, the 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 if at least one of: the determined rotation rate is not a desired rotation rate and the determined rotation direction is not a desired rotation direction; and provide an output to start the at least one propeller if the at least one propeller is stopped at the desired rotation rate and the desired rotation direction.
G01P 3/48 - Devices characterised by the use of electric or magnetic means for measuring angular speed by measuring frequency of generated current or voltage
B64C 39/02 - Aircraft not otherwise provided for characterised by special use
An unmanned aerial vehicle (UAV) launch tube that comprises at least one inner layer of prepreg substrate disposed about a right parallelepiped aperture, at least one outer layer of prepreg substrate disposed about the right parallelepiped aperture, and one or more structural panels disposed between the at least one inner layer of prepreg substrate and the at least one outer layer of prepreg substrate.
A method of targeting, which involves capturing a first video of a scene about a potential targeting coordinate by a first video sensor on a first aircraft; transmitting the first video 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 for a second aircraft 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 corresponding to the actual targeting coordinate is maintained from selection of the actual targeting coordinate.
F41G 9/00 - Systems for controlling missiles or projectiles, not provided for elsewhere
G01C 11/06 - Interpretation of pictures by comparison of two or more pictures of the same area
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 for a fleet of three or more unmanned aerial vehicles (UAVs), where each UAV of the fleet of UAVs comprise a respective flight control computer (FCC); at least one computing device at a ground control station, where each computing device is in communication with each FCC, and where each computing device is associated with at least one operator; where the fleet of UAVs above the threshold altitude 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 for a ground support system for an unmanned aerial vehicle (UAV) including: at least one handling fixture, where each handling fixture is configured to support at least one wing panel of the UAV; and at least one dolly, where each dolly is configured to receive at least one landing pod 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 further allows for transportation of the UAV over uneven terrain.
Systems, devices, and methods including an unmanned aerial vehicle (UAV); one or more inner wing panels of the UAV; one or more outer wing panels of the UAV; at least one inboard propeller attached to at least one engine disposed on the one or more inner wing panels; at least one tip propeller attached to at least one engine disposed on the one or more outer wing panels; at least one microcontroller 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.
Disclosed herein are system and method for controlling an unmanned aerial vehicle (UAV) tethered from a mobile platform, the UAV system comprising: a UAV comprising one or more sensors, and one or more propellers; a tether attached to the UAV and to the mobile platform; a digital processing device comprising an operating system configured to perform executable instructions and a memory; and a computer program including instructions executable by the digital processing device to automatically control the UAV relative to the mobile platform comprising: a software module identifying the mobile platform; a software module estimating a real-time state of the mobile platform; and a software module automatically controlling three-dimensional real-time motion of the UAV based on the real-time state estimation of the mobile platform and data collected from the one or more sensors, such that the UAV is maintained at a predetermined position relative to the mobile platform.
B64U 70/93 - Portable platforms for use on a land or nautical vehicle
G01L 5/04 - Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes for measuring tension in flexible members, e.g. ropes, cables, wires, threads, belts or bands
H04W 4/40 - Services specially adapted for particular environments, situations or purposes for vehicles, e.g. vehicle-to-pedestrians [V2P]
B64U 101/31 - UAVs specially adapted for particular uses or applications for imaging, photography or videography for surveillance
18.
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 having a first GPS antenna and a second GPS antenna, where the second GPS antenna is disposed distal from the first GPS antenna; and an aerial vehicle flight controller, 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 ganged servo flight control system for an unmanned aerial vehicle is provided. The flight control system may include a swashplate having first, second, and third connection portions; a first control assembly connected to the first connection portion of the swashplate; a second control assembly connected to the second connection portion of the swashplate; and a third control assembly connected to the third connection portion of the swashplate. The first control assembly may include two or more servo-actuators connected to operate in cooperation with each other.
B64C 27/605 - Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical including swash plate, spider or cam mechanisms
B64C 13/50 - Transmitting means with power amplification using electrical energy
B64C 27/625 - Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical including rotating masses or servo rotors
B64U 20/70 - Constructional aspects of the UAV body
B64U 40/10 - On-board mechanical arrangements for adjusting control surfaces or rotorsOn-board mechanical arrangements for in-flight adjustment of the base configuration for adjusting control surfaces or rotors
B64U 50/31 - Supply or distribution of electrical power generated by photovoltaics
B64U 101/30 - UAVs specially adapted for particular uses or applications for imaging, photography or videography
20.
SYSTEM FOR DETACHABLY COUPLING AN UNMANNED AERIAL VEHICLE WITHIN A LAUNCH TUBE
An unmanned aerial vehicle launch tube that has a tube, a sabot disposed in an interior of said tube, said sabot having a first clasp tab, and a clasp detachably coupled to said first clasp tab and contacting an inner circumferential wall of said tube so that said clasp is rotationally constrained by the inner circumferential wall and said first clasp tab.
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 video camera to capture still images and video frames 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 a still image output including image data packets. A multiplexer is coupled to the video output and the still image output. The multiplexer produces a data transmission including the video packets and the 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.
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
H04N 21/414 - Specialised client platforms, e.g. receiver in car or embedded in a mobile appliance
H04N 21/434 - Disassembling of a multiplex stream, e.g. demultiplexing audio and video streams or extraction of additional data from a video streamRemultiplexing of multiplex streamsExtraction or processing of SIDisassembling of packetised elementary stream
An aircraft apparatus is disclosed that has a fuselage boom having proximal and distal ends, a wing coupled to a proximal end of the fuselage boom and at least one transparent stabilizer coupled to a distal end of the fuselage boom.
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.
An aerial payload vehicle descent arrest system, method operating and device, including an aerial payload vehicle configured to descend along a predetermined flightpath toward a target destination, a descent state detection system configured to receive sensor output information from a plurality of sensors, to compute a sensed distance to the target destination based on sensor output information from at least two sensors of the plurality of sensors, and to generate a descent arrest device trigger signal based on a sensed altitude, and a descent arrest device configured to receive the descent arrest device trigger signal from the descent state detection system and to decelerate the aerial payload vehicle before a payload from the aerial payload vehicle is delivered to the target destination.
B64U 20/30 - Constructional aspects of UAVs for safety, e.g. with frangible components
B64U 101/69 - UAVs specially adapted for particular uses or applications for transporting passengersUAVs specially adapted for particular uses or applications for transporting goods other than weapons the UAVs provided with means for airdropping goods, e.g. deploying a parachute during descent
25.
Roll-biased skid-to-turn terminal guidance with rudder integrator feedback
Systems, devices, and methods for an aircraft autopilot guidance control system for guiding an aircraft having a body, the system comprising: a processor configured to determine if a yaw angle difference and a pitch angle difference meet corresponding angle thresholds; a skid-to-turn module configured to generate a skid-to-turn signal if the corresponding angle thresholds are met; a bank-to-turn module configured to generate a bank-to-turn signal having a lower bandwidth than the generated skid-to-turn signal; a rudder integrator module 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 configured to filter the generated bank-to-turn signal, wherein the filter module 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.
An electric motor controller system for modulating requested motor torque via oscillating the instantaneous torque, including a bi-stable torque controller; a proportional-integral (PI) velocity controller a proportional-integral-differential (PID) position controller; and sinusoidal zero-velocity table mapping.
H02P 6/10 - Arrangements for controlling torque ripple, e.g. providing reduced torque ripple
B60L 15/20 - Methods, circuits or devices for controlling the propulsion of electrically-propelled vehicles, e.g. their traction-motor speed, to achieve a desired performanceAdaptation of control equipment on electrically-propelled vehicles for remote actuation from a stationary place, from alternative parts of the vehicle or from alternative vehicles of the same vehicle train for control of the vehicle or its driving motor to achieve a desired performance, e.g. speed, torque, programmed variation of speed
27.
Safety System for Operation of an Unmanned Aerial Vehicle
Systems, devices, and methods for a safety system including: 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.
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 a ground support system for an unmanned aerial vehicle (UAV) including: at least one handling fixture, where each handling fixture is configured to support at least one wing panel of the UAV; and at least one dolly, where each dolly is configured to receive at least one landing pod 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 further allows for transportation of the UAV over uneven terrain.
A method of unmanned aerial vehicle (UAV) flight includes providing horizontal thrust in-line with the direction of forward flight of the UAV using at least one electric motor, providing primary vertical lift for the UAV during the forward flight using a fixed and non-rotating wing, repositioning the at least one electric motor to provide vertical thrust during transition of the UAV to vertical flight for descent, landing the UAV on a surface using a vertical approach after the motor repositioning, and deploying an anchor to secure the UAV to a surface.
Systems, devices, and methods for receiving image data; transferring the captured image data to a server having a processor and addressable memory via a network-connected computing device; storing the captured image data on the server; generating captured image metadata based on the stored captured image data; providing access to the captured image data and captured image metadata via an image management component; displaying, by the image management component, the captured image data; and filtering, by the image management component, the captured image data based on the generated captured image metadata.
A method of targeting, which involves capturing a first video of a scene about a potential targeting coordinate by a first video sensor on a first aircraft; transmitting the first video 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 for a second aircraft 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 corresponding to the actual targeting coordinate is maintained from selection of the actual targeting coordinate.
F41G 9/00 - Systems for controlling missiles or projectiles, not provided for elsewhere
G01C 11/06 - Interpretation of pictures by comparison of two or more pictures of the same area
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
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.
A motor assembly that includes a motor having a motor casing, a rotatable shaft extending from said motor casing to a shaft length and a hub coupled to said rotatable shaft, the hub having a circumferential skid surface disposed immediately proximal to the motor casing and having a channel configured to seat a propeller, when a propeller is present, wherein a bending moment applied to the shaft through the hub results in the circumferential skid surface contacting said motor casing.
H02K 7/00 - Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
H02K 7/14 - Structural association with mechanical loads, e.g. with hand-held machine tools or fans
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.
Systems, devices, and methods for receiving, by a processor having addressable memory, data representing a geographical area for imaging by one or more sensors of an aerial vehicle; determining one or more straight-line segments covering the geographical area; determining one or more waypoints located at an end of each determined straight-line segment, where each waypoint comprises a geographical location, an altitude, and a direction of travel; determining one or more turnarounds 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 comprising: the determined one or more straight-line segments and the determined one or more turnarounds connecting each straight-line segment.
Systems, devices, and methods for determining a predicted impact point of a selected weapon and associated round based on stored ballistic information, provided elevation data, provided azimuth data, and provided position data.
Systems, devices, and methods including: a latching mechanism comprising: a first latch configured to attach to a door of an unmanned aerial vehicle (UAV); a second latch configured to attach to a portion of the UAV distal from the first latch; a string connected between the first and second latch, where the string secures the door shut; at least two radio modules in communication with a ground control station; and at least two burn wires in contact with a portion of the string between the first latch and the second latch; where current from a backup battery passes to at least one burn wire when the burn signal is received, where the burn wire causes the connection between the first latch and the second latch to be broken and the door of the UAV is separated from the UAV, and where the parachute is deployed when the door of the UAV is separated from a rest of the UAV.
In one possible embodiment, a wireless network with dynamic transmission control is provided that includes a multiple of nodes. The nodes include an arbiter and multiple client nodes. The arbiter is configured to control an operation of the client nodes by defining communications operation cycles and allocating a bandwidth to each of the client nodes on a cycle by cycle basis in response to requests for bandwidth from the client nodes.
Systems, devices, and methods for an aircraft having a fuselage; a wing extending from both sides of the fuselage; a first pair of motors disposed at a first end of the wing; and a second pair of motors disposed at a second end of the wing; where each motor is angled to provide a component of thrust by a propeller attached thereto that for a desired aircraft movement applies a resulting torque additive to the resulting torque created by rotating the propellers.
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 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
B64D 27/06 - Aircraft characterised by the type or position of power plants of piston type within, or attached to, wings
B64U 70/80 - Vertical take-off or landing, e.g. using rockets
B64U 50/19 - Propulsion using electrically powered motors
B64U 101/30 - UAVs specially adapted for particular uses or applications for imaging, photography or videography
A system having a damper with six or more indentations on alternating sides of the damper, where 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.
H02K 5/24 - CasingsEnclosuresSupports specially adapted for suppression or reduction of noise or vibrations
F16F 1/376 - Springs made of plastics, e.g. rubberSprings made of material having high internal friction characterised by having a particular shape having projections, studs, serrations or the like on at least one surface
F16F 1/38 - Springs made of plastics, e.g. rubberSprings made of material having high internal friction with a sleeve of elastic material between a rigid outer sleeve and a rigid inner sleeve or pin
F16F 15/08 - Suppression of vibrations of non-rotating, e.g. reciprocating, systemsSuppression of vibrations of rotating systems by use of members not moving with the rotating system using elastic means with rubber springs
F16M 13/02 - Other supports for positioning apparatus or articlesMeans for steadying hand-held apparatus or articles for supporting on, or attaching to, an object, e.g. tree, gate, window-frame, cycle
44.
SURVEY MIGRATION SYSTEM FOR VERTICAL TAKE-OFF AND LANDING (VTOL) UNMANNED AERIAL VEHICLES (UAVS)
A method of migrating unmanned aerial vehicle (UAV) 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 from the UAV pod a plurality of times to perform the first plurality of flight missions; 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 from the second UAV pod a plurality of times to perform the second plurality of flight missions; 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.
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
B64D 1/02 - Dropping, ejecting, or releasing articles
Systems, devices, and methods for determining, by a processor, an unmanned aerial system (UAS) position relative to at least one flight boundary; 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.
Systems, devices, and methods including a launch control box; a multi-pack launcher (MPL) box; and a cable connecting the launch control box and the MPL box, where the cable comprises: an outer jacket, a shielded braid, a first wire, a second wire, a third wire, and a fourth wire, where the first wire and the second wire are shielded by the shielded braid, where the third wire and the fourth wire are outside of the shielded braid, and where the third wire and the fourth wire act as an antenna.
Systems, devices, and methods including one or more rib mounting flanges, where each rib mounting flange comprises: a spar opening configured to receive a main spar of a wing panel; one or more holes for receiving cross-bracing cables; and one or more holes for receiving cross-bracing cables; and one or more holes for connecting the rib mounting flange to an adjacent rib mounting flange.
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 video camera to capture still images and video frames 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 a still image output including image data packets. A multiplexer is coupled to the video output and the still image output. The multiplexer produces a data transmission including the video packets and the 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.
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
H04N 21/2743 - Video hosting of uploaded data from client
H04N 21/414 - Specialised client platforms, e.g. receiver in car or embedded in a mobile appliance
H04N 21/434 - Disassembling of a multiplex stream, e.g. demultiplexing audio and video streams or extraction of additional data from a video streamRemultiplexing of multiplex streamsExtraction or processing of SIDisassembling of packetised elementary stream
An unmanned aerial vehicle (UAV) storage and launch system, including: a UAV pod having an interior; and a telescoping UAV landing surface disposed in the interior of the UAV pod; where the telescoping UAV landing surface may translate up toward a top opening of the UAV pod, translate down into an interior of the UAV pod, or rotate relative to the UAV pod.
B64F 1/22 - Ground or aircraft-carrier-deck installations for handling aircraft
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 39/02 - Aircraft not otherwise provided for characterised by special use
B64F 1/00 - Ground or aircraft-carrier-deck installations
B64F 1/02 - Ground or aircraft-carrier-deck installations for arresting aircraft, e.g. nets or cables
B64F 1/04 - Ground or aircraft-carrier-deck installations for launching aircraft
B64F 1/222 - Ground or aircraft-carrier-deck installations for handling aircraft for storing aircraft, e.g. in hangars
A method and system including: defining a geographic area; receiving a plurality of images; determining a plurality of image points; partitioning the geographic area into a plurality of image regions based on the plurality of image points; and stitching the plurality of images into a combined image based on the plurality of image regions.
A method and system including: an aerial vehicle including: a first camera 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 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 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.
Systems, devices, and methods including an unmanned aerial vehicle (UAV); one or more inner wing panels of the UAV; one or more outer wing panels of the UAV; at least one inboard propeller attached to at least one engine disposed on the one or more inner wing panels; at least one tip propeller attached to at least one engine disposed on the one or more outer wing panels; at least one microcontroller 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.
An unmanned aerial vehicle (UAV) launch tube that comprises at least one inner layer of prepreg substrate disposed about a right parallelepiped aperture, at least one outer layer of prepreg substrate disposed about the right parallelepiped aperture, and one or more structural panels disposed between the at least one inner layer of prepreg substrate and the at least one outer layer of prepreg substrate. An unmanned aerial vehicle (UAV) launch tube that comprises a tethered sabot configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot is hollow having an open end oriented toward a high pressure volume and a tether attached within a hollow of the sabot and attached to the inner wall retaining the high pressure volume or attach to the inner base wall. A system comprising a communication node and a launcher comprising an unmanned aerial vehicle (UAV) in a pre-launch state configured to receive and respond to command inputs from the communication node.
A hydrogen fueled powerplant including an internal combustion engine that drives a motor-generator, and has a two-stage turbocharger, for an aircraft. A control system controls the operation of the motor-generator to maintain the engine at a speed selected based on controlling the engine equivalence ratio. The control system controls an afterburner, an intercooler and an aftercooler to maximize powerplant efficiency. The afterburner also adds power to the turbochargers during high-altitude restarts. The turbochargers also include motor-generators that extract excess power from the exhaust.
F01N 3/20 - Exhaust or silencing apparatus having means for purifying, rendering innocuous, or otherwise treating exhaust for rendering innocuous by thermal or catalytic conversion of noxious components of exhaust characterised by methods of operationControl specially adapted for catalytic conversion
F01N 9/00 - Electrical control of exhaust gas treating apparatus
F02D 19/02 - Controlling engines characterised by their use of non-liquid fuels, pluralities of fuels, or non-fuel substances added to the combustible mixtures peculiar to engines working with gaseous fuels
F02D 29/06 - Controlling engines, such controlling being peculiar to the devices driven thereby, the devices being other than parts or accessories essential to engine operation, e.g. controlling of engines by signals external thereto peculiar to engines driving electric generators
F02D 41/00 - Electrical control of supply of combustible mixture or its constituents
F02M 21/02 - Apparatus for supplying engines with non-liquid fuels, e.g. gaseous fuels stored in liquid form for gaseous fuels
F02D 41/06 - Introducing corrections for particular operating conditions for engine starting or warming up
F02D 41/08 - Introducing corrections for particular operating conditions for idling
An aircraft apparatus is disclosed that has a fuselage boom having proximal and distal ends, a wing coupled to a proximal end of the fuselage boom and at least one transparent stabilizer coupled to a distal end of the fuselage boom.
Systems, devices, and methods for a vertical take-off and landing (VTOL) aerial vehicle having a first GPS antenna and a second GPS antenna, where the second GPS antenna is disposed distal from the first GPS antenna; and an aerial vehicle flight controller, 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.
Systems, devices, and methods for an extruded wing protection and control surface comprising: a channel proximate a leading edge of the control surface, a knuckle disposed about the channel, a leading void, a trailing void, and a separator dividing the leading void and the trailing void; and a plurality of notches disposed in the extruded control surface proximate the leading edge of the control surface.
B64C 9/16 - Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing
B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
B64C 39/02 - Aircraft not otherwise provided for characterised by special use
B64C 13/38 - Transmitting means with power amplification
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
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
B64C 3/36 - Structures adapted to reduce effects of aerodynamic or other external heating
B64F 5/00 - Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided forHandling, transporting, testing or inspecting aircraft components, not otherwise provided for
58.
System for detachably coupling an unmanned aerial vehicle within a launch tube
An unmanned aerial vehicle launch tube that has a tube, a sabot disposed in an interior of said tube, said sabot having a first clasp tab, and a clasp detachably coupled to said first clasp tab and contacting an inner circumferential wall of said tube so that said clasp is rotationally constrained by the inner circumferential wall and said first clasp tab.
A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements.
B64C 9/08 - Adjustable control surfaces or members, e.g. rudders bodily displaceable
B64C 9/18 - Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing by single flaps
B64C 9/36 - Adjustable control surfaces or members, e.g. rudders collapsing or retracting against or within other surfaces or other members the members being fuselages or nacelles
B64C 11/00 - Propellers, e.g. of ducted typeFeatures common to propellers and rotors for rotorcraft
B64C 13/18 - Initiating means actuated automatically, e.g. responsive to gust detectors using automatic pilot
B64C 13/34 - Transmitting means without power amplification or where power amplification is irrelevant mechanical using toothed gearing
B64C 39/02 - Aircraft not otherwise provided for characterised by special use
B64U 40/10 - On-board mechanical arrangements for adjusting control surfaces or rotorsOn-board mechanical arrangements for in-flight adjustment of the base configuration for adjusting control surfaces or rotors
B64C 9/00 - Adjustable control surfaces or members, e.g. rudders
A ganged servo flight control system for an unmanned aerial vehicle is provided. The flight control system may include a swashplate having first, second, and third connection portions; a first control assembly connected to the first connection portion of the swashplate; a second control assembly connected to the second connection portion of the swashplate; and a third control assembly connected to the third connection portion of the swashplate. The first control assembly may include two or more servo-actuators connected to operate in cooperation with each other.
B64C 27/605 - Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical including swash plate, spider or cam mechanisms
B64C 13/50 - Transmitting means with power amplification using electrical energy
B64C 27/625 - Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical including rotating masses or servo rotors
B64C 39/02 - Aircraft not otherwise provided for characterised by special use
B64U 20/70 - Constructional aspects of the UAV body
B64U 40/10 - On-board mechanical arrangements for adjusting control surfaces or rotorsOn-board mechanical arrangements for in-flight adjustment of the base configuration for adjusting control surfaces or rotors
61.
System for protecting a rotatable shaft of a motor from excessive bending moments
A motor assembly that includes a motor having a motor casing, a rotatable shaft extending from said motor casing to a shaft length and a hub coupled to said rotatable shaft, the hub having a circumferential skid surface disposed immediately proximal to the motor casing and having a channel configured to seat a propeller, when a propeller is present, wherein a bending moment applied to the shaft through the hub results in the circumferential skid surface contacting said motor casing.
H02K 7/00 - Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
H02K 7/14 - Structural association with mechanical loads, e.g. with hand-held machine tools or fans
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.
Described is a method of delivery for cargo or goods from an aerial vehicle (mothership) to a designated ground delivery location via the use of a direct air shipping package. For example, an aerial vehicle may be an airplane or helicopter that remains at altitude with a package stowed for deployment. As the mothership travels in the vicinity of the designated location the package flight control computer (flight controller) calculates a preferred travel trajectory based upon the aerodynamic properties of the package and location relative to the designated delivery location such as a small delivery pad located on a patio of a home. When the mothership transits through a calculated release point the package disengages the mothership. As the package descends it may increase accuracy relative to the designated delivery location by altering aerodynamic properties to maintain the preferred travel trajectory and decreasing landing zone size requirements and increasing precision of delivery. To reduce the impact force at landing the designated delivery location and/or the package may contain a net, airbag, parachute or similar device to provide a suitably soft landing suitable for commercial home delivery.
B64U 101/69 - UAVs specially adapted for particular uses or applications for transporting passengersUAVs specially adapted for particular uses or applications for transporting goods other than weapons the UAVs provided with means for airdropping goods, e.g. deploying a parachute during descent
G01C 21/20 - Instruments for performing navigational calculations
64.
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.
Systems, devices, and methods that may include: determining one or more take-off variables for a vertical take-off and landing (VTOL) aerial vehicle; increasing an altitude of the VTOL aerial vehicle to a first altitude, where increasing the altitude comprises substantially vertical flight of the VTOL aerial vehicle; performing a first pre-rotation check of the VTOL aerial vehicle; adjusting a pitch of the VTOL aerial vehicle to a first pitch angle via motor control; 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; and adjusting the pitch of the VTOL aerial vehicle to a third pitch angle via the one or more effectors, where the third pitch angle is substantially perpendicular to a vertical plane.
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
G05D 1/08 - Control of attitude, i.e. control of roll, pitch, or yaw
G05D 1/02 - Control of position or course in two dimensions
Systems, devices, and methods for identifying a target aerial vehicle, deploying an interceptor aerial vehicle comprising at least one effector, maneuvering the interceptor aerial vehicle to a position to engage a target aerial vehicle, deploying the at least one effector to intercept the target aerial vehicle, and confirming that the target aerial vehicle has been intercepted.
In one possible implementation, a motor is provided including a rotor and a stator. Front cooling fins are thermally coupled to a front of the stator, and rear cooling fins are thermally coupled to a rear portion of the stator. The winding is between the front and rear cooling fins.
H02K 3/14 - Windings characterised by the conductor shape, form or construction, e.g. with bar conductors arranged in slots with transposed conductors, e.g. twisted conductors
H02K 3/47 - Air-gap windings, i.e. iron-free windings
H02K 7/14 - Structural association with mechanical loads, e.g. with hand-held machine tools or fans
H02K 16/02 - Machines with one stator and two rotors
H02K 9/14 - Arrangements for cooling or ventilating wherein gaseous cooling medium circulates between the machine casing and a surrounding mantle
H02K 9/22 - Arrangements for cooling or ventilating by solid heat conducting material embedded in, or arranged in contact with, the stator or rotor, e.g. heat bridges
H02K 9/06 - Arrangements for cooling or ventilating by ambient air flowing through the machine having means for generating a flow of cooling medium with fans or impellers driven by the machine shaft
H02K 9/02 - Arrangements for cooling or ventilating by ambient air flowing through the machine
H02K 3/30 - Windings characterised by the insulating material
H02K 3/32 - Windings characterised by the shape, form or construction of the insulation
Systems, devices, and methods for determining a predicted impact point of a selected weapon and associated round based on stored ballistic information, provided elevation data, provided azimuth data, and provided position data.
A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements.
B64C 9/08 - Adjustable control surfaces or members, e.g. rudders bodily displaceable
B64C 9/18 - Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing by single flaps
B64C 9/36 - Adjustable control surfaces or members, e.g. rudders collapsing or retracting against or within other surfaces or other members the members being fuselages or nacelles
B64C 11/00 - Propellers, e.g. of ducted typeFeatures common to propellers and rotors for rotorcraft
B64C 13/18 - Initiating means actuated automatically, e.g. responsive to gust detectors using automatic pilot
B64C 39/02 - Aircraft not otherwise provided for characterised by special use
B64U 40/10 - On-board mechanical arrangements for adjusting control surfaces or rotorsOn-board mechanical arrangements for in-flight adjustment of the base configuration for adjusting control surfaces or rotors
B64C 9/00 - Adjustable control surfaces or members, e.g. rudders
A system comprising an unmanned aerial vehicle (UAV) configured to transition from a terminal homing mode to a target search mode, responsive to an uplink signal and/or an autonomous determination of scene change.
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.
Systems, devices, and methods including: a latching mechanism comprising: a first latch configured to attach to a door of an unmanned aerial vehicle (UAV); a second latch configured to attach to a portion of the UAV distal from the first latch; a string connected between the first and second latch, where the string secures the door shut; at least two radio modules in communication with a ground control station; and at least two burn wires in contact with a portion of the string between the first latch and the second latch; where current from a backup battery passes to at least one burn wire when the burn signal is received, where the burn wire causes the connection between the first latch and the second latch to be broken and the door of the UAV is separated from the UAV, and where the parachute is deployed when the door of the UAV is separated from a rest of the UAV.
Systems, devices, and methods for determining, by a processor, an unmanned aerial system (UAS) position relative to at least one flight boundary; 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.
Systems, devices, and methods including one or more rib mounting flanges, where each rib mounting flange comprises: a spar opening configured to receive a main spar of a wing panel; one or more holes for receiving cross-bracing cables; and one or more holes for receiving cross-bracing cables; and one or more holes for connecting the rib mounting flange to an adjacent rib mounting flange.
Systems, devices, and methods including a leading edge tubular member; an upper tubular member; a lower tubular member; one or more upper rib members connected between the leading edge tubular member and the upper tubular member; one or more lower rib members connected between the leading edge tubular member and the lower tubular member; a rigid sandwich shell disposed between the upper tubular member and the leading edge tubular member; and a sandwich shear web disposed between the upper tubular member and the lower tubular member; where the rigid sandwich shell and the sandwich shear web form a D-shape.
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 video camera to capture still images and video frames 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 a still image output including image data packets. A multiplexer is coupled to the video output and the still image output. The multiplexer produces a data transmission including the video packets and the 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.
H04N 23/661 - Transmitting camera control signals through networks, e.g. control via the Internet
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
H04N 21/434 - Disassembling of a multiplex stream, e.g. demultiplexing audio and video streams or extraction of additional data from a video streamRemultiplexing of multiplex streamsExtraction or processing of SIDisassembling of packetised elementary stream
79.
Systems and methods for starting a sensorless motor
Systems, devices, and methods for: an unmanned aerial vehicle (UAV); at least one sensorless motor of the UAV, the 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 if at least one of: the determined rotation rate is not a desired rotation rate and the determined rotation direction is not a desired rotation direction; and provide an output to start the at least one propeller if the at least one propeller is stopped at the desired rotation rate and the desired rotation direction.
G01P 3/48 - Devices characterised by the use of electric or magnetic means for measuring angular speed by measuring frequency of generated current or voltage
B64C 39/02 - Aircraft not otherwise provided for characterised by special use
An unmanned aerial vehicle (UAV) launch tube that comprises at least one inner layer of prepreg substrate disposed about a right parallelepiped aperture, at least one outer layer of prepreg substrate disposed about the right parallelepiped aperture, and one or more structural panels disposed between the at least one inner layer of prepreg substrate and the at least one outer layer of prepreg substrate. An unmanned aerial vehicle (UAV) launch tube that comprises a tethered sabot configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot is hollow having an open end oriented toward a high pressure volume and a tether attached within a hollow of the sabot and attached to the inner wall retaining the high pressure volume or attach to the inner base wall. A system comprising a communication node and a launcher comprising an unmanned aerial vehicle (UAV) in a pre-launch state configured to receive and respond to command inputs from the communication node.
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 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 for a ground support system for an unmanned aerial vehicle (UAV) including: at least one handling fixture, where each handling fixture is configured to support at least one wing panel of the UAV; and at least one dolly, where each dolly is configured to receive at least one landing pod 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 further allows for transportation of the UAV over uneven terrain.
Systems, devices, and methods including at least one flight control computer (FCC) associated with at least one UAV, 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 covering at least a portion of the UAV.
Systems, devices, and methods for an aircraft having a fuselage; a wing extending from both sides of the fuselage; a first pair of motors disposed at a first end of the wing; and a second pair of motors disposed at a second end of the wing; where each motor is angled to provide a component of thrust by a propeller attached thereto that for a desired aircraft movement applies a resulting torque additive to the resulting torque created by rotating the propellers.
B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
B64D 27/06 - Aircraft characterised by the type or position of power plants of piston type within, or attached to, wings
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 39/02 - Aircraft not otherwise provided for characterised by special use
A method of unmanned aerial vehicle (UAV) flight includes providing horizontal thrust in-line with the direction of forward flight of the UAV using at least one electric motor, providing primary vertical lift for the UAV during the forward flight using a fixed and non-rotating wing, repositioning the at least one electric motor to provide vertical thrust during transition of the UAV to vertical flight for descent, landing the UAV on a surface using a vertical approach after the motor repositioning, and deploying an anchor to secure the UAV to a surface.
A system having a damper with six or more indentations on alternating sides of the damper, where 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.
H02K 5/24 - CasingsEnclosuresSupports specially adapted for suppression or reduction of noise or vibrations
F16F 1/376 - Springs made of plastics, e.g. rubberSprings made of material having high internal friction characterised by having a particular shape having projections, studs, serrations or the like on at least one surface
F16F 1/38 - Springs made of plastics, e.g. rubberSprings made of material having high internal friction with a sleeve of elastic material between a rigid outer sleeve and a rigid inner sleeve or pin
F16F 15/08 - Suppression of vibrations of non-rotating, e.g. reciprocating, systemsSuppression of vibrations of rotating systems by use of members not moving with the rotating system using elastic means with rubber springs
F16M 13/02 - Other supports for positioning apparatus or articlesMeans for steadying hand-held apparatus or articles for supporting on, or attaching to, an object, e.g. tree, gate, window-frame, cycle
88.
Method Of Flight Plan Optimization Of A High Altitude Long Endurance Aircraft
Systems, devices, and methods including: at least one unmanned aerial vehicle (UAV); at least one flight control computer (FCC) associated with each UAV, where the FCC controls movement of each UAV; at least one computing device associated with a ground control station; where the at least one FCC maintains a first flight pattern 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 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 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 including at least one computing device associated with a ground control station, 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 for a fleet of three or more unmanned aerial vehicles (UAVs), where each UAV of the fleet of UAVs comprise a respective flight control computer (FCC); at least one computing device at a ground control station, where each computing device is in communication with each FCC, and where each computing device is associated with at least one operator; where the fleet of UAVs above the threshold altitude 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.
Embodiments include one or more high altitude, long endurance (HALE) unmanned aircraft capable of persistent station-keeping having one or more electromagnetic (IR/Visual/RF) sensor elements or suites for purposes of survey and/or signal gathering. Embodiments include one or more high altitude, long endurance (HALE) unmanned aircraft capable of persistent station-keeping having a directable laser. Embodiments include a group of four or more high altitude, long endurance (HALE) unmanned aircraft configured as GPS repeaters.
B64C 39/02 - Aircraft not otherwise provided for characterised by special use
G01S 19/11 - Cooperating elementsInteraction or communication between different cooperating elements or between cooperating elements and receivers providing dedicated supplementary positioning signals wherein the cooperating elements are pseudolites or satellite radio beacon positioning system signal repeaters
A method of migrating unmanned aerial vehicle (UAV) 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 from the UAV pod a plurality of times to perform the first plurality of flight missions; 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 from the second UAV pod a plurality of times to perform the second plurality of flight missions; 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.
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
A payload delivery device configured to deliver an aircraft deployed payload along a flight path to a predetermined landing destination includes a support member configured to be removably attached to the payload, a flight control and navigation system module configured to control orientation of the plurality of control surfaces while the payload is travelling along the flight path to the predetermined landing destination, a control surface assembly module including a plurality of control surfaces, a rotor assembly including a plurality of rotor blades having a central axis of rotation, and a collective control assembly module including at least one collective servomotor configured to control a plurality of control linkages connected to the plurality of rotor blades.
A method of assembling a delivery payload assembly configured to be deployed from an aircraft and travel along a flight path to a predetermined landing destination includes attaching a tail-kit assembly to a first end of a payload, the tail-kit assembly including a rotor blade assembly including a plurality of rotor blades having a central axis of rotation, and a flight control and navigation system configured to control a collective pitch angle of each of the plurality of rotor blades of the rotor blade assembly, configured to control an axial thrust force of the rotor blade assembly, the axial thrust force being at an angle with respect to the central axis of rotation of the rotor blade assembly, and configured to navigate the delivery payload assembly along the flight path to the predetermined landing destination. The method further includes removing the tail-kit assembly from the payload after the payload is delivered to the predetermined landing destination.
Systems, devices, and methods including an unmanned aerial vehicle (UAV); one or more inner wing panels of the UAV; one or more outer wing panels of the UAV; at least one inboard propeller attached to at least one engine disposed on the one or more inner wing panels; at least one tip propeller attached to at least one engine disposed on the one or more outer wing panels; at least one microcontroller 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.
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.
Systems, devices, and methods for determining a predicted impact point of a selected weapon and associated round based on stored ballistic information, provided elevation data, provided azimuth data, and provided position data.
Systems, devices, and methods including: a latching mechanism comprising: a first latch configured to attach to a door of an unmanned aerial vehicle (UAV); a second latch configured to attach to a portion of the UAV distal from the first latch; a string connected between the first and second latch, where the string secures the door shut; at least two radio modules in communication with a ground control station; and at least two burn wires in contact with a portion of the string between the first latch and the second latch; where current from a backup battery passes to at least one burn wire when the burn signal is received, where the burn wire causes the connection between the first latch and the second latch to be broken and the door of the UAV is separated from the UAV, and where the parachute is deployed when the door of the UAV is separated from a rest of the UAV.
Systems, devices, and methods for a ground support system for an unmanned aerial vehicle (UAV) including: at least one handling fixture, where each handling fixture is configured to support at least one wing panel of the UAV; and at least one dolly, where each dolly is configured to receive at least one landing pod 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 further allows for transportation of the UAV over uneven terrain.
An electric motor controller system for modulating requested motor torque via oscillating the instantaneous torque, including a bi-stable torque controller; a proportional-integral (PI) velocity controller a proportional-integral-differential (PID) position controller; and sinusoidal zero-velocity table mapping.
H02P 7/06 - Arrangements for regulating or controlling the speed or torque of electric DC motors for regulating or controlling an individual DC dynamo-electric motor by varying field or armature current
B60L 15/20 - Methods, circuits or devices for controlling the propulsion of electrically-propelled vehicles, e.g. their traction-motor speed, to achieve a desired performanceAdaptation of control equipment on electrically-propelled vehicles for remote actuation from a stationary place, from alternative parts of the vehicle or from alternative vehicles of the same vehicle train for control of the vehicle or its driving motor to achieve a desired performance, e.g. speed, torque, programmed variation of speed
H02P 6/10 - Arrangements for controlling torque ripple, e.g. providing reduced torque ripple
