Abstract: Aircraft landing gear forward trunnion support assemblies and related methods are described herein. An example aircraft wing disclosed herein includes a rear spar having a rear side and a front side opposite the rear side and a forward trunnion support assembly. The forward trunnion support assembly includes first and second vertical support fittings coupled to the rear side of the rear spar, and a trunnion housing with a bearing. The trunnion housing is coupled between the first and second vertical support fittings. The trunnion housing also includes first and second shoulders formed on a top side of the trunnion housing, each of the first and second shoulders having a respective open trough formed on a respective top surface thereof, thereby defining first and second cradles. A fuse pin is received within the troughs and has first and second ends extending through the first and second vertical support fittings respectively.

Abstract: A vertical take-off and landing (VTOL) aircraft provides transportation to users of a network system. The network system may include multiple aircraft or other types of vehicles to provide multi-model transportation. An aircraft may include a fuselage, a truss coupled to the fuselage, and multiple distributed electric propellers coupled to the truss. The distributed electric propellers may be positioned on at least two different planes. The fuselage may include a cabin having one or more seats for the passengers arranged in a configuration that has a compact footprint, provides legroom, provides visibility to surroundings of the aircraft, or facilitates convenient ingress or egress of passengers. The aircraft may open a port cabin door and starboard cabin door for simultaneous ingress or egress of passengers.

Abstract: An aerial vehicle includes an airframe, a canopy capable of adjusting a speed of falling during falling, a brake cord having one end connected to the canopy, a wind-up apparatus provided in the airframe and being capable of winding up the other end of the brake cord, a sensor unit that detects a distance to an external object, and a controller that controls an operation of the wind-up apparatus based on a result of detection by the sensor unit. The wind-up apparatus includes a gas generator as a drive source. The controller has the wind-up apparatus operate to wind up the other end of the brake cord by activating the gas generator when the distance detected by the sensor unit is equal to or smaller than a prescribed value.

Abstract: Systems and methods for compactly mounted cyclic flight control for a rotorcraft. One embodiment is an apparatus that includes a stick base assembly coupled with a cyclic stick and configured to rotate with respect to a mounting frame to control a pitch and a roll of the rotorcraft. A cyclic housing is pivotably coupled with the mounting frame for rotation about a pitch axis to control pitch, and coupled with a pitch actuator having a pitch force sensor to measure its resistance to rotation. The cyclic housing supports the stick base assembly for independent rotation of the stick base assembly about a roll axis to control roll, and the stick base assembly couples with a roll actuator having a roll force sensor to measure its resistance to rotation.

Abstract: A selectively deployable heated propulsor system which may be integrated into vehicles, airplanes, or any other machinery configured for flight. The system includes a structural feature that includes a mounted propulsor including a rotor and a motor mechanically coupled to the rotor allowing the rotor to rotate when in an activated mode. The mounted propulsor includes a chamber configured to support a first configuration where the propulsor and the rotor are stowed and heated in an enclosed environment, and a second configuration where the rotor is deployed.

Abstract: A control system (200) using fixed point computation avoids overflow conditions by limiting the internal quantities ensuring that contributing calculations from various parts of the control loop never add up to an overflow. Various parts of a control loop e.g. proportional terms can be prioritised over other parts, e.g. integral and differential terms and ensuring that the overall total resulting when the separate terms are summed together never exceeds the maximum or minimum imposed limits. Variable limit calculator circuits (211,219) revise the limits according to the output of the higher priority control path(s). The revised limits cascade down through each contributor, eventually allowing the lowest priority control path the smallest authority. The control system may be applied to control of a drive motor (111) for an aircraft inceptor (103).

Abstract: A runback system for receiving fluid from a deicing system may comprise a body and a first channel and a second channel defined by the body. A first end of the first channel may be spaced apart from a first end of the second channel. A second end of the first channel and a second end of the second channel may meet and form an outlet at an end of the body.

Abstract: In an example, a seating system includes a seat comprising a chamber, a wall structure adjacent to the seat and defining a compartment, a door insert configured to move within the compartment between a starting position and a retracted position, wherein in the starting position, the door is adjacent to the seat and blocks access to the compartment, and in the retracted position, the door is retracted into the wall structure and provides access to the compartment, a closed channel extending from the chamber and operably connected to the door, and a piston operably coupled to the seat and positioned within the chamber, wherein when a load is applied to the seat, the piston is compressed, moving the door from the starting position to the retracted position, and when the load is removed, the piston is decompressed, causing the door to move from the retracted position to the starting position.

Abstract: Various measures (for example methods, UAVs, controllers and computer programs) are provided in relation to controlling a UAV. The UAV is caused to provide energy to and receive energy from a given vehicle. The received energy is used to provide power to at least one component of the UAV.

Abstract: Fluid systems are described herein. An example fluid system includes a main body and a heating member attached to the main body. The main body has a leading edge, a trailing edge, an injection opening, a suction opening, a channel, a first passageway, a second passageway, a first opening, a second opening, and a third opening. The channel extends from the injection opening to the suction opening. The first passageway extends from the first opening to the second opening. The first opening is in communication with the channel and the second opening is in communication with the second passageway. The second passageway is in communication with the first passageway and extends to the third opening, which is in communication with a first environment exterior to the second passageway. The heating member is sized and configured to heat fluid traveling through the second passageway.

Abstract: An airborne device for surveillance of an enclosed area, comprising a platform having illuminating imaging devices, and an attached lighter than air balloon. A vertically aligned rotor provides additional lift, a rotor directed along the length of the platform provides forward and backward motion, and additional rotors aligned sideways steer and rotate the device. The rotors are driven by electric motors powered by an on-board battery. A vertically directed distance sensor measures and controls the hovering distance of the device from the roof. A reel of optical fiber is installed at the rear end of the platform, and the optical fiber unwinds from the reel and deploys behind the device as it moves forward. This optical fiber carries image data back to a monitor. The length of fiber deployed, combined with directional and accelerometer readings can be used to determine the absolute position of the device.

Abstract: A flight assembly and glider possessing bilateral, flexible, and collapsible wings and associated method of flight are provided. The flight assembly may include a central frame that may encapsulate a human operator. A wing frame may include at least a pair of wings that couple to the central frame, wherein each wing may include one or more pivotal connections. To control the extension and retraction of the pair of wings, a control lever network may be incorporated within the central frame and the wing frame. The control lever network may include wing sail deployment, flight deceleration and parachute wing conversion features.

Abstract: A method for operating an electric fan of an aircraft propulsion system includes driving a plurality of fan blades of the electric fan with an electric machine to generate thrust for the aircraft; and driving the electric machine with the plurality of fan blades of the electric fan to generate electrical power subsequent to driving the plurality of fan blades of the electric fan with the electric machine to generate thrust for the aircraft.

Abstract: The present invention discloses improvements to mechanical and electro-mechanical force simulators for aircraft pilot controllers, and particularly foot-actuated controllers. In particular, the invention replaces conventional foot-actuated, pilot controller systems—namely, those that employ multiple, discrete, motion control subsystems to control the various force simulation and trim functions used in modern aircraft to assist pilot control of a given axis of flight—with a single motion control system. The invention accomplishes this in part by eliminating the force-feel spring used in conventional, federated, foot-actuated, motor-coupled pilot controllers.

Abstract: A fluid foil has a main fixed portion and a tip portion movably mounted at a tip end of the main fixed portion. The main fixed portion has an upper surface and a lower surface, and the tip portion has an upper surface and a lower surface. The fluid foil is operable in: a) a first configuration in which the upper surface of the tip portion is angled downwardly with respect to the upper surface of the main fixed portion; and b) a second configuration in which the tip portion is rotated upwardly with respect to the first configuration such that the upper surface of the tip portion and the upper surface of the main fixed portion are substantially continuous surfaces. The movement of the tip portion with respect to the main fixed portion is exclusively passively actuated by movement of the foil with respect to a surrounding fluid.

Abstract: Systems and methods include providing an aircraft with a fuselage, a tail boom or empennage extending from the fuselage, a main rotor, a tail rotor, and at least one counter torque device. The counter torque device provides counter torque to the fuselage to prevent rotation of fuselage when the main rotor is operated, particularly in right sideward flight (RSF) for conventional helicopters with a counter-clockwise rotating (when viewed from above the helicopter) main rotor.

Abstract: Launch and/or recovery for unmanned aircraft and/or other payloads, including via parachute-assist, and associated systems and methods are disclosed. A representative method for lofting a payload includes directing a lifting device upward, releasing a parachute from the lifting device, with the parachute carrying a pulley and having a flexible line passing around the pulley. The flexible line is connected between a tension device (e.g., a winch) and the payload. The method further includes activating the tension device to reel in the flexible line and accelerate the payload upwardly.

Abstract: Embodiments of the present invention relate to a launch vehicle fairing recovery system and method using inflatable bags and fairing repositioning mechanisms. Embodiments of the present invention also relate to providing a system or mechanism to flip the fairing into the proper floating position. In some embodiments, the fairing has an inner surface and an outer surface, where the outer surface is exposed to the atmosphere when the fairing is interconnected to a spacecraft, and one or more inflatable bags interconnected to the outer surface of the fairing, where when the fairing is interconnected to the spacecraft the one or more inflatable bags is empty, and after the fairing separates from the spacecraft the one or more airbags are filled with pressurized gas and/or hydraulic liquids.

Abstract: A universal aerial platform (11, 41) supports lift elements (13, 14), thrusters (15), landing gear (21, 22) and a fuel supply (16) and has a coupling mechanism (17) external to the aerial platform for coupling to a terrain vehicle (20) so as to convert any suitably adapted terrain vehicle to a flying vehicle (10, 40). The terrain vehicle forms the cockpit of the flying vehicle. The terrain vehicle (20) includes flight controls that are automatically coupled to the airplane structure either wirelessly or by wires when the terrain vehicle is coupled thereto.

Abstract: A vehicle includes a fuselage having a longitudinal axis and a propulsion system that is coupled to the fuselage. The vehicle also includes a pair of articulated appendages that is coupled to the fuselage. Each one of the articulated appendages includes a plurality of airfoil segments and is moveable between a ground configuration, in which each one of the pair of articulated appendages supports the vehicle during takeoff or landing of the vehicle, and a flight configuration, in which each one of the pair of articulated appendages produces lift during flight of the vehicle.