Abstract: Provided herein is a canopy control system comprising a yoke, configured to be pivotably securable to a vehicle and securable to a line system of a canopy in use, such that the yoke pivots with respect to the vehicle in a first direction when the canopy is subjected to a wind force; and a control mechanism configured to apply a control force to the canopy line system to cause the canopy to oppose the wind force, such that yoke pivots with respect to the vehicle in a second direction which is opposite to the first direction.

Abstract: The invention pertains to the development of a unique and small transformable robot that will fit into very small pipes, openings, or packing tubes, thereby enabling complex missions and also which can fly and drive. Other advantages of the system include portability, weight, perch, and stare capabilities. The present invention comprises a compact transformable robot capable of flying and driving designed to furl or fit into small openings, containers, packing tubes, or pipes containing a thrust, a main body, controls, and rotating propellers. The compact transformable robot capable of flying and driving that is designed to furl or fit into small openings, containers, or pipes comprises a ground locomotion, an aerial locomotion, controls, sensors, and a radio.

Abstract: The present invention provides an unmanned aerial vehicle and an unmanned aerial vehicle controlling system. The unmanned aerial vehicle controlling system includes the unmanned aerial vehicle and a controller. The unmanned aerial vehicle has a body, a first localization module and a second localization module. The first localization module and the second localization module are disposed on the body respectively facing a first direction and a second direction. The controller is used for sending a localization signal to the first localization module and a second localization module. The unmanned aerial vehicle controls the direction that the body faces and the distance between the unmanned aerial vehicle and the controller.

Abstract: The present disclosure relates to a total logistics operation system and method using drone, including a delivery information inputter that receives input of delivery information; a delivery model division determiner that extracts, based on the input delivery information, location information of the customer located in an area where drone delivery can be made, speed information of a vehicle and a drone, and location information of the logistics center and the drone station, and that uses the extracted information to determine whether division building of a drone delivery model of using the drone only is possible; and a delivery model builder that, depending on a result of determining whether division of delivery model is possible, builds a delivery model that includes any one of a mixed delivery model for numerous drones and numerous vehicles, the drone delivery model for numerous drones, and a vehicle delivery model for numerous vehicles.

Abstract: A modular aerial vehicle for inspection of enclosed and open space environments. The aerial vehicle is employed for inspection of various environments in remotely controlled and autonomous fashions. The aerial vehicle is capable of carrying different sensory modules depending on the specific application including surface inspection. Aerial vehicle may be connected to a tether cable for electrical power delivery and transmission of control commands. The aerial vehicle may utilize a landing structure which allows landing on any angled metallic or non-metallic surface.

Abstract: In some embodiments, a method for determining a location of an unmanned system (UMS) can include: receiving data from a plurality of data sources, wherein the data sources include a geolocation sensor and at least one of an RF receiver, a RADAR system, a LIDAR system, a SONAR system, an infrared camera, a Simultaneous Location and Mapping Algorithm (SLAM) system, an inertial sensor, or an acoustic sensor; determining a reliability of one or more of the data sources based on the received data; assigning weights to the data sources based at least in part on the determination of the reliability of the one or more data sources; and determining the location of the UMS using the received data and the assigned weights.

Abstract: A method for processing image information in an image to determine a movement for a movable object. The method includes detecting whether the image includes a water surface or a sky based on the image information in the image, And, in response to detecting that the image includes the water surface or the sky, determining a technique from a plurality of techniques for calculating a depth map, generating the depth map using the technique, and determining a movement parameter for the movable object using the depth map.

Abstract: An aircraft having a blended-wing-body configuration includes a centerbody, a pair of wings, at least one pair of engines, a pair of air inlets, and a pair of exhaust outlets. The centerbody has an airfoil-shaped cross section, an aircraft centerline, an aft portion, an upper mold line, a lower mold line, and a pair of centerbody leading edge portions respectively on opposite sides of the aircraft centerline. The wings are integral with the centerbody. The pair of engines are located on opposite sides of the aircraft centerline and are mounted within the centerbody between the upper mold line and the lower mold line. The pair of air inlets are located respectively along the centerbody leading edge portions and are respectively fluidly coupled to the pair of engines. The pair of exhaust outlets our located in the aft portion of the centerbody and our respectively fluidly coupled to the pair of engines.

Abstract: An aircraft includes a fuselage having a nose end and a tail end and a center of gravity. A primary wing is coupled to the fuselage aft of the center of gravity. A secondary wing is coupled to the fuselage forward of the center of gravity. A v-tail is coupled to the fuselage between the primary wing and the tail end of the fuselage, the v-tail comprising first and second angled stabilizers, each of the first and second stabilizers including a first end fixed to the fuselage and a second free end, distal to the fuselage.

Abstract: A method for controlling a spreading apparatus includes obtaining a target degree of opening and a real-time degree of opening of a material outlet of the spreading apparatus, determining whether the real-time degree of opening of the material outlet is abnormal based on a comparison result between the real-time degree of opening and the target degree of opening, and transmitting an alarm signal to a remote control device in response to the real-time degree of opening of the material outlet being abnormal.

Abstract: A vertical landing of an aircraft is performed using the first battery where the aircraft is unoccupied when the vertical landing is performed, the unoccupied aircraft includes the first battery, and the unoccupied aircraft excludes a second, removable battery. In response to detecting that the second, removable battery is detachably coupled to the aircraft, a power source for the aircraft is switched from the first battery to the second, removable battery. After switching the switch power source, a vertical takeoff of the aircraft is performed using the second, removable battery, wherein the aircraft is occupied when the vertical takeoff is performed.

Abstract: A shoring adapter configured for spreading cargo loads, in particular heavy cargo loads, to be loaded on board of a transport aircraft, includes at least one base portion configured to be placed on a standardized aircraft cargo pallet and a cargo adapter portion configured to accommodate the cargo load. In operation, the cargo adapter portion is mounted on top of the at least one base portion. The at least one base portion includes a lower frame assembly, an upper frame assembly and at least one elastic support assembly. The at least one elastic support assembly is arranged between the lower and upper frame assemblies such that, in operation, the upper frame assembly is elastically supported in a vertical direction by the at least one elastic support assembly on the lower frame assembly.

Abstract: A system for retrofitting a wall of an aircraft monument includes a modular power charging unit and mounting hardware. The modular power charging unit includes a housing containing an electrical port component, a cable harness, and a switch. The housing has a plurality of screw holes and a back panel having an opening through which the cable harness extends. The mounting hardware includes a plurality of threaded inserts, each configured to be inserted into one of a plurality of mounting holes formed in the wall, and a plurality of screws, each configured to extend through a screw hole of the housing and into a threaded insert. The housing is configured to be secured to a first side of the wall so that the entirety of the housing projects outward from the first side and only the cable harness extends through a cable-harness hole formed through a thickness of the wall.

Abstract: A time-sensitive, data reduction system is described. According to an aspect of the system, a method is disclosed that comprises: receiving at least a portion of an airline-specific dataset, wherein the airline-specific dataset comprises a plurality of location records, wherein each location record comprises a point of interest (POI) and a unique rank, wherein the POI is defined by unique geographic identifier; determining a current position of the aircraft; and based on the current position and based on the unique rank of each of the plurality of location records, controlling, at a passenger display in the aircraft, a presentation of a map and a plurality of POI indicators associated with a highly-ranked subset of the plurality of location records. According to another aspect of the system, a plurality of servers are used provide relevant location-related content to an aircraft passenger.

Abstract: A component positioning system and method are configured to facilitate positioning of a component (such as a seat assembly) on a seat track within an internal cabin of a vehicle. The component positioning system and method include a component, and a position indicator coupled to a portion of the component. The position indicator emits a proper position indication when the component is in a proper position in relation to the seat track. The position indicator emits a remedial position indication when the component is not in the proper position with respect to the seat track.

Abstract: A travel suite arrangement for an aircraft cabin, such as a business class cabin, including at least one longitudinal aisle dividing sections, with each section including at least one four-suite unit. Each four-suite unit generally includes an angled first seat positioned directly adjacent the longitudinal aisle forward-facing, a second angled seat positioned directly adjacent the longitudinal aisle rearward-facing, a third angled seat positioned apart from the longitudinal aisle, to one side of the first seat and rearward-facing, and a fourth angled seat positioned apart from the longitudinal aisle, to one side of the second seat and forward-facing. Aisle seats are accessed directly from the aisle while outboard seats share access passageways.

Abstract: A modal restraint system for an occupant of a seat of an aircraft having a mechanical failure sensor includes a strap feeder unit and a strap selectively retractable into and extendable from the strap feeder unit. The strap is positionable adjacent to the occupant. The strap feeder unit is adapted to switch between a plurality of modes including an unfixed mode and a fixed mode. The strap is extendable from and retractable into the strap feeder unit in the unfixed mode. The strap is substantially unextendable from the strap feeder unit in the fixed mode. The strap feeder unit is in the unfixed mode by default. The strap feeder unit is operable to switch to the fixed mode in response to a precautionary event including detection of an aircraft mechanical failure by the mechanical failure sensor, thereby reducing freedom of movement of the occupant relative to the seat.

Abstract: A seat positioning system and method for an internal cabin of a vehicle includes a seat track, and a keying assembly that provides expanded openings in relation to the seat track. The expanded openings are arranged in a pattern for proper positioning of a seat assembly. The expanded openings are configured to receive securing studs of the seat assembly.

Abstract: A seat assembly includes a backrest that is configured to recline over a reclination range, and a variable reclination range limiter that is configured to selectively adjust a limit of the reclination range limit. A variable reclination range limiting method for a seat assembly includes allowing a backrest of the seat assembly to recline over a reclination range, and selectively adjusting a limit of the reclination range by a variable reclination range limiter.

Abstract: A seat, in particular an aircraft seat, having a seat support structure having at least one seat surface with a seat surface frame and a backrest with a backrest frame being pivotable relative to the seat surface, a base support element supporting the seat support structure, and a seat adjustment arrangement, which includes at least one coupling unit movable relative to the base support element, the coupling unit is configured to connect the seat surface frame and the backrest frame to one another and which is provided with at least one bearing element, and which includes at least one guide element in which the bearing element is movably guided. The seat adjustment arrangement being adapted to transfer the seat support structure into a sitting position, a comfort position or lying position by displacing the bearing element along the guide element.

Abstract: A seat assembly within an internal cabin of a vehicle includes an electrical interface housing that contains a first portion of a cable that is configured to provide one or both of electrical power or electrical signals to one or more electrical components. A cable reel rotatably coupled to a body of the electrical interface housing. The cable reel is configured to rotate about an axis. The first portion of the cable includes an adjustable coil that is coiled around the cable reel. The cable reel is rotatable in a first direction to deploy the first portion of the cable outwardly from the electrical interface housing and a second direction to retract the first portion of the cable inwardly into the electrical interface housing.

Abstract: An aircraft seat having a voltage supply connection assigned only to the aircraft seat and/or at least one data connection assigned only to the aircraft seat, a voltage supply unit assigned to the aircraft seat and having a voltage input for connection to an on-board voltage network of an aircraft and at least one voltage output, each connected to another of the voltage supply connections. A switching arrangement is assigned only to the aircraft seat and connected between the voltage output and the voltage supply connection and/or between the data connection and a data network. A control unit is assigned only to the aircraft seat and connected to the switching arrangement. An infrared reading device is connected to the control unit and assigned only to the aircraft seat to wirelessly receive infrared signals from an external infrared transmitting device.

Abstract: Described herein is a seat back for an aircraft seat, the seat back comprising a body, wherein the body comprises a support wall for supporting a passenger leaning against the seat back, a first side wall, a second side wall and a cross brace, wherein the cross brace connects the first side wall and the second side wall at a position between a lower end and an upper end of each of the side walls, and wherein the support wall, the first side wall, the second side wall and the cross brace are integrally formed. Also described is a seat comprising the seat back and a row of seats.

Abstract: An externally replaceable friction mechanism for a pivoting assembly such as an armrest assembly, the friction mechanism including a first spacer configured to non-rotationally engage a fixed element and frictionally engage a pivoting element pivotable relative to the fixed element, a first friction ring configured to non-rotationally engage the first spacer, the first friction ring including fingers configured to frictionally engage the pivoting element, and wherein the first friction ring is configured to permit pivoting movement of the pivoting element relative to the fixed element and provide friction against the pivoting movement.

Abstract: A seat adjustment system includes a seat assembly having at least one securing stud that is configured to be retained within a track channel of a seat track, and a seat adjuster coupled to the seat assembly. The seat adjuster is moveable between a secured position in which the securing stud(s) is configured to be retained within the track channel of the seat track, and an adjustment position in which the securing stud(s) is configured to be outside of the seat track.

Abstract: A seat adjustment system and method include a seat assembly having at least one securing stud that is configured to be retained within a track channel of a seat track, and a seat adjuster coupled to the seat assembly. The seat adjuster includes at least one glider. The seat adjuster is moveable between a secured position in which the glider(s) is separated from a top surface of the seat track and the securing stud(s) is retained within the track channel of the seat track, and an adjustment position in which the glider(s) is positioned on a top surface of the seat track and the securing stud(s) is outside of the seat track.

Abstract: A seat indexing system and method for an internal cabin of a vehicle include a seat assembly including one or more indexing indicators, a seat track, and one or more indexing guides on the seat track. The indexing indicator(s) cooperate with the indexing guide(s) to indicate one or more desired positions for the seat assembly in relation to the seat track.

Abstract: A seat indexing system and method for an internal cabin of a vehicle include a seat assembly, and an indexing wheel coupled to the seat assembly. The indexing wheel is configured to be moved between a stowed position, in which the indexing wheel is disengaged from a seat track, and a deployed position, in which the indexing wheel engages the seat track.

Abstract: A life preserver head restraint may be configured to inflate in response to deployment of a parachute assembly. The life preserver head restraint may comprise an inflatable volume and a charge tank fluidly coupled to the inflatable volume. In an inflated state, the life preserver head restraint may restrict head movement during line stretch of the parachute assembly.

Abstract: A hydraulic propulsion system is disclosed which includes an input interface configured to receive mechanical power from a power source, a pressure source comprising one or more fixed or variable displacement pumps coupled to the input interface and adaptable to convert mechanical power to hydraulic power and controlling outlet pressure of the pressure source (system pressure), one or more variable displacement motors coupled to the pressure source via a corresponding high-pressure line configured to be mechanically coupled to one or more aerodynamic rotors of an aircraft and comprising a closed loop speed control arrangement in response to a commanded rotor speed, and a controller configured to control the speed of one or more variable displacement motors by providing a control signal for controlling the system pressure.

Abstract: An aircraft power plant has: a hybrid propulsion system having an electric motor, an output shaft drivingly connectable to a thrust generator, a combustion engine, a compressor, and a transmission having a first transmission drive path and a second transmission drive path selectively engageable to the first transmission drive path, the electric motor and the compressor in driving engagement with the first transmission drive path, the combustion engine and the output shaft in driving engagement with the second transmission drive path.

Abstract: A multi-engine aircraft that includes two or more powerplants, each including an electric motor, and an electric power system controlling electrical distribution and operatively connected to the electric motors. The electric power system includes primary battery packs operatively connected to the electric motor of a respective one of the two or more powerplants, a reserve battery pack, and a switch interconnecting the reserve battery pack and the electric motors. The reserve battery pack is shared by the electric motors by the switch and configured such that the reserve battery pack provides electric power to a selected one of the electric motors.

Abstract: Arms and an associated unmanned aerial vehicle (UAV) are disclosed, which include a connecting component, a frame and arms. Each arm includes a longitudinal tube having an inverted teardrop shape-cross section with a hollow interior. The upper end of the longitudinal tube is a first curved surface. The lower end of the longitudinal tube is a second curved surface. The arc length of the first curved surface is greater than the arc length of the second curved surface. The connecting component connects the arm to the frame, and comprises an installing component and a mounting component. The installing component and the mounting component are mounted on two respective ends of the arm. The frame of UAV and the driving assembly are connected through the arm. Compared to circular shape, the raindrop/half lemniscate shape is more streamlined than those having a circular cross-sectional shape, resulting in substantially improved air fluidities.

Abstract: An assembly for an aircraft, which includes a pylon with a bearing face and a contact face, an engine mount with a bearing face and a contact face bearing against the contact face of the pylon, at least two bolts comprising a threaded stem with a head and a nut bearing against the bearing face of the engine mount, for each head, a bearing washer with a first bearing face and a second bearing face, where the second bearing face of the bearing washer bears against the bearing face of the pylon, and where the head bears against the first bearing face of the bearing washer, a shoe, and, for each bearing washer, a clamp that is secured to the shoe and comprises a first branch and a second branch between which the bearing washer is clamped and is free to rotate.

Abstract: An aircraft rear engine attachment connecting a primary structure of a pylon and an engine of an aircraft. The rear engine attachment includes first and second rods, each of them including at least two parts, a first part including at least one support orifice, accommodating a support link bar, configured to connect the rod directly or indirectly to the primary structure, at least one second part including at least one engine orifice, accommodating an engine link bar, configured to connect the rod directly or indirectly to the engine, and also detachable link elements for connecting the first and second parts oriented parallel to the direction of the rod.

Abstract: An aircraft power plant has a hybrid propulsion system having an electric motor, a combustion engine, an output shaft drivingly connectable to a thrust generator, a compressor, and a transmission having a first transmission drive path and a second transmission drive path, the combustion engine and the output shaft in driving engagement with the first transmission drive path, the electric motor selectively drivingly engageable to the compressor via either the first drive path or via the second drive path.

Abstract: An aircraft power plant has a hybrid propulsion system having an electric motor, an output shaft drivingly connectable to a thrust generator, a combustion engine, a compressor, and a planetary gear train having an Auxiliary Power Unit (APU) mode in which the electric motor is in driving engagement with the compressor via the planetary gear train while the combustion engine is disengaged from the output shaft, and a propulsion mode in which the combustion engine and the electric motor are in driving engagement with the output shaft via the planetary gear train.

Abstract: Tunable multi-layer thermoplastic polymer sealants and tunable two-layer conductive thermoplastic polymer sealants, and substrates and assemblies comprising the tunable multi-layer sealants; and edge seals and fillet seals produced comprising such sealants; and substrates, components and objects comprising the tunable edge seals and fillet seals, and methods for making and applying such edge seals and fillet seals are disclosed.

Abstract: A pressure-operated check valve assembly for a fuel tank inerting system includes a valve body having a fluid flow path between an inlet and an outlet, a plurality of poppets arranged in series in the fluid flow path, and an actuator in the valve body that is movable in response to fluid pressure in the valve body to actuate open the poppets or enable the poppets to close. Each poppet may be movable in the flow path independent of the other poppets to thereby provide independent and redundant functionality. The poppets may be normally biased toward closed, and activation of the actuator in response to fluid pressure being greater than a predefined threshold level may cause the actuator to overcome the biasing force of the poppets to urge the poppets to open. A flow restrictor downstream of the poppets may facilitate buildup of upstream pressure to enable low cracking pressure.

Abstract: An aircraft fuel tank inerting system may include at least one fuel tank, at least one surge tank, an inert air assembly, at least one fluid valve connected to the at least one fuel tank, the at least one surge tank, and the inert air assembly, and/or an electronic control unit. The electronic control unit may control the at least one fluid valve to provide inert air from the inert air assembly to the at least one fuel tank and/or to the at least one surge tank. The electronic control unit may control the at least one fluid valve to provide inert air from the inert air assembly to the fuel tank during a climb phase of a flight and control the at least one fluid valve to provide inert air from the inert air assembly to the at least one surge tank during a descent phase of the flight.

Abstract: An auxiliary power unit (APU) control system for an aircraft is disclosed and includes an APU, an air inlet having an effective area, an air inlet door moveable to vary the effective area of the air inlet, an actuator configured to move the air inlet door into a set position, one or more processors, and a memory coupled to the one or more processors. The memory stores data comprising a database and program code that, when executed by the one or more processors, causes the APU control system to receive one or more ambient signals indicative of an air density value. The system also determines the effective area of the air inlet based on the air density value. The system is further caused to instruct the actuator to move the air inlet door into the set position.

Abstract: An apparatus and system are provided for use as a flight deck workstation for an aircraft pilot. The apparatus comprises a touch screen display located on the flight deck workstation that shows aircraft data to the aircraft pilot. User sensors are integrated into the touch screen display that allow user input and provide feedback to the aircraft pilot when using the touch screen display.

Abstract: A system for landing gear prognostic and health management may comprise a stroke measurement component and a pin configured to translate relative to the stroke measurement component. The pin may include a plurality of graduations. The pin may be configured such that a graduation corresponding to a stroke length of the landing gear may be visible through a viewing window of the stroke measurement component.

Abstract: A camera module for surveillance of a passenger cabin of an aircraft, including a covering device for securing in a longitudinal cutout of a service channel including a carrier part having a circular securing cutout and including a mounting structure at least partly surrounding the securing cutout. A camera device includes a camera housing having a mounting portion with a spherically curved outer surface, and includes a camera unit having a lens accommodated in a front cutout of the camera housing, an optical sensor for generating image data, the optical sensor being in an interior of the camera housing, and a data interface for transferring the image data, wherein the camera housing is mounted by the mounting portion in the mounting structure to be rotatable or pivotable about at least two axes, and a locking device for locking the camera housing relative to the mounting structure.

Abstract: A UAV includes a body, an arm connected to the body, and a gimbal assembly. The gimbal assembly includes a gimbal, a load carried by the gimbal, and a damping device connecting the gimbal to the body. The damping device includes a connection shaft configured to pass through the body, and a first shock-absorbing structure and a second shock-absorbing structure disposed at two ends of the connection shaft, respectively. The first shock-absorbing structure is connected to the body or the arm. The second shock-absorbing structure is connected to the body. One of the first shock-absorbing structure and the second shock-absorbing structure is connected to the gimbal.

Abstract: A landing strobe is provided that comprises a vane extending from the landing strobe, and an actuator coupled to the vane. The actuator can be configured to move the vane from a first position to a second position upon impact of the landing strobe. The landing strobe can also comprise an optical emitter configured to emit an adjustable radiation pattern extending radially around a central axis that is substantially vertical when the van is moved to the second position. A landing strobe system is also provided and comprises a landing strobe configured to be released from an aircraft arranged over a landing zone. The vane is configured to extend at an upward angle outward from the landing strobe when released from the aircraft. The vane is further configured to extend at a downward angle outward from the landing strobe when the landing strobe contacts the landing zone.

Abstract: A landing strobe is provided having an optical emitter configured to emit an optical signal. An input device can be coupled to the optical emitter for setting the optical signal to a signature strobe output unique to the landing strobe. A landing zone designation system is also provided having a landing strobe configured to emit a signature strobe output unique to the landing strobe. An aircraft spaced from the landing strobe can include a detector for optically receiving the signature strobe output to determine the landing zone is proper to land the aircraft if the signature strobe output matches an expected signature strobe output.

Abstract: A base station configured for charging an autonomous drone may comprise a first conductive groove and a second conductive groove. The first conductive groove and the second conductive groove may be configured to interface with a first conductive strip and a second conductive strip disposed on a landing gear of the autonomous drone. The base station may be configured to charge a battery of the autonomous drone in response to the first conductive groove interfacing with the first conductive strip and the second conductive groove interfacing with the second conductive strip.

Abstract: A drone is described. The drone includes a propulsion system, a base station transceiver, a tether connector, and a power system. The power system has a battery and a chopper circuit. The chopper circuit bleeds excess charge from the battery. The power system is configured to power the propulsion system, and to power the base station transceiver through the chopper circuit. The power system is also configured to receive electrical power, through the tether connector, to charge the battery while the drone is in the air.

Abstract: An engine thrust rating process and system for controlling engine thrust during flight of an aircraft and/or to support an airplane development program (including design, validation testing, and production of airplane systems, airplane dispatch and operation tools). The thrust rating process uses thrust ratios derived from thrust expressed in power rather than engine rotor speed (N1). In one or more examples, the thrust rating architecture is based on “Max Rated Thrust” tables and the power setting parameter “PSP” being calculated at the end of the process instead of at the beginning of the process (unlike conventional procedures), thereby enabling the system software development early as needed to support the airplane development phase. This concept also yields improvements such as simplified control logic, optimized engine performance and engine life.