Abstract: A falling-resistant and anti-drifting unmanned aerial vehicle has a main body and at least one rotor wing thereon. Both sides of the main body have a wing with an airbag filled with gas lighter than air. Bulges protruding downwards are arranged at the bottoms of the airbag. The two airbags are at the same height symmetrically arranged based on the main body. The airbag can function as an undercarriage when the aircraft lands down, and as a buffer when crash landing and then reduce damage to the main body. If the aircraft falls in water, the aircraft can float on the water to avoid damage caused by sinking. As bulges protruding downwards are arranged at the bottoms of the airbags, in spraying operation, side wing can be relatively well baffled by the bulges in case of side wing blowing in the flying process, resulting in less droplets draft.

Abstract: A system enabling safe manned and unmanned operations at extremely high altitudes (above 70,000 feet). The system utilizes a balloon launch system and parachute and/or parafoil recovery.

Abstract: An aircraft comprises several elements. A throttle body is adapted to regulate a rate of air flow. An electronic control unit, in turn, is in signal communication with one or more sensors, and comprises a data processor in signal communication with a memory. A first fuel delivery system is operative to direct a first fuel from a first fuel tank to the plurality of cylinders at a rate determined at least in part by a condition of the throttle body. A second fuel delivery system is operative to direct a second fuel from a second fuel tank to the plurality of cylinders at a rate determined at least in part by the electronic control unit in response to signals from the one or more sensors. One or more fuel selection controls allow a pilot of the aircraft to select between powering the aircraft with the first fuel delivery system and the second fuel delivery system.

Abstract: A morphing skin for an air vehicle structure, the skin being formed by a composite material which includes: a multiplicity of fibers, a matrix incorporating the fibers, and a thermo-sensitive material, such as a thermo-plastic. The thermo-sensitive material can be reversibly transitionable in response to a change in temperature, between (i) an ambient temperature mode in which the thermo-sensitive material is capable of transferring loads in the composite material, and (ii) a heated mode in which the ability of the thermo-sensitive material to transfer the loads is reduced. This can allow the stiffness of the skin to be temporarily reduced to enable the skin to be morphed into a different shape.

Abstract: A landing gear assembly is also provided. The landing gear assembly may include a thin-skin support member defining a cavity and a cylindrical cavity. A cylinder may extend from the cylindrical cavity with an axle extending from the cylinder. A torsion link may be coupled to the axle and a torsion interface of the thin-skin support member.

Abstract: An oscillating pump system includes a pump operable to circulate a fluid. The pump has a first port stage including an inlet port and an outlet port and a second port stage including a first oscillating port and a second oscillating port. An oscillator disk is disposed between the first port stage and the second port stage. The oscillator disk is rotatable relative to the inlet port, the outlet port, the first oscillating port and the second oscillating port. During rotation, the oscillator disk alternatingly routes the fluid to the inlet port from the first and second oscillating ports and alternatingly routes the fluid from the outlet port to the first and second oscillating ports, thereby generating oscillating fluid flow.

Abstract: A flexurally controlled system comprises an elongated structure, a tendon attached to the elongated structure, and an actuator operable to apply a tensile load to the tendon. The actuator is operable to apply the tensile load to the tendon when at least one of the first side of the elongated structure is under a first tensile stress or the second side of the elongated structure is under a first compressive stress. The actuator is also operable to apply no load to the tendon when the first side and the second side of the elongated structure are not under stress. The tendon is non-coaxial with a central axis of the elongated structure and is aligned with at least one region of the elongated structure.

Abstract: A habitation module with a gravity chamber that provides an artificial gravity environment. In one embodiment, the gravity chamber is annular and includes an outer cylindrical wall, an inner cylindrical structure, and opposing side walls that connect the outer cylindrical wall and the inner cylindrical structure. The gravity chamber attaches to a cylindrical core member of the habitation module with support bearings. The support bearing includes an inner race attached to the cylindrical core member, and an outer race attached to the gravity chamber. A drive mechanism drives the outer race of the support bearing to rotate the gravity chamber about an axis to simulate a gravitational force within the gravity chamber.

Abstract: A load-bearing fairing element for a flap adjustment mechanism of an aircraft comprises a shell-shaped fairing housing with an at least partly U-shaped profile with an open side, a closed side, and a direction of main extension, at least one first cover panel that along the direction of main extension covers part of the open side, and a load-bearing bridge element. The bridge element is arranged in the fairing housing and with a base area conforms so as to be flush against an internal surface of the fairing housing and extends towards the open side. The bridge element comprises an essentially planar cover area that covers the base area on the open side in order to produce a closed profile contour that is circumferential on the direction of main extension. The bridge element comprises means for holding a shaft feed-in of a central flap drive and means for holding an adjustment mechanism that is couplable to the shaft feed-in.

Abstract: A battery containment pod including a body formed of a lightweight material. The body has an aerodynamic exterior shape and an interior cavity formed in the lightweight material, the size and shape of the interior cavity designed to accommodate one or more battery packs. A smooth exterior coating covers the exterior shape of the body, and an attachment structure formed in or on the body allows the body to be coupled to a flight vehicle. Other implementations are disclosed and claimed.

Abstract: A LiDAR sensor can include a laser, a directional sensor, a window, an electromagnetic pulse receiving sensor, and a processor. The laser can be configured to emit a narrow electromagnetic pulse. Further, the directional sensor can be configured to measure the direction of the narrow electromagnetic pulse emitted by the laser. The narrow emitted electromagnetic pulse can pass through the window. The pulse can then be reflected by at least the window and an object external from the LiDAR sensor, creating at least two reflected pulses. The electromagnetic pulse receiving sensor can be configured to measure the two reflected pulses resulting from the narrow pulse emitted by the laser. The processor can be configured to receive information from the sensors, indicating a position of the object relative to the LiDAR sensor. Further, the processor can be configured to measure the intensity of the pulse being reflected by the window.

Abstract: The present invention relates to a joint between a laminar composite cover (12) and a second cover (15) (which may or may not be also formed from a composite material). The invention also relates to a method of manufacturing such a joint and a method of manufacturing a composite cover suitable for use in such a joint. The laminar composite cover (12) comprises a stack of layers, substantially all of the layers being shaped to form a joggle, each joggle comprising a first portion, a second portion where the layer extends substantially parallel with the first portion, and a ramp (33) between the first and second portions where the layer extends at an angle to the first and second portions, the number of layers being substantially the same on both sides of the ramp. The second cover (15) partially overlaps with the composite cover, and a clamp or fastener (31) holds the covers together where they overlap.

Abstract: A light beam is detected/localized by multisector detector—quad-cell, or 5+ sectors handling plural beams. Preferences: Beams focus to diffraction limit on the detector, which reveals origin direction by null-balance—shifting spots to a central sector junction, and measuring shifts to reach there. One or more MEMS reflectors, and control system with programmed processor(s), sequence the spot toward center: following a normal to an intersector boundary; then along the boundary. One afocal optic amplifies MEMS deflections; another sends beams to imaging optics. After it's known which sector received a spot, and the beam shifts, source direction is reported. The system can respond toward that (or a related) direction. It can illuminate objects, generating beams reflectively. Optics define an FOR in which to search; other optics define an FOV (narrower), for imaging spots onto the detector. The FOR:FOV angular ratio is on order of ten—roughly 180:20°, or 120:10°.

Abstract: In an embodiment of the disclosure, there is provided an apparatus to provide a panel stiffening element. The apparatus has an outer braided thermoplastic tube and an inner braided thermoplastic tube disposed within the outer braided thermoplastic tube. The apparatus further has a separation ply layer co-consolidated between the outer braided thermoplastic tube and the inner braided thermoplastic tube. The separation ply layer provides reinforcement and impact damage resistance to the inner braided thermoplastic tube in order to avoid a loss in structural loading capability.

Abstract: An apparatus may comprise a housing, a first member, and a second member. The housing may have a first end, a second end, a first side, a second side, an opening located in the first end, and a passage extending from the opening. The first member may extend from the first side. The first member may have a first channel in communication with the passage and the channel has a first center axis. The second member may extend from the first side. The second member may have a second channel in communication with the passage and the second channel has a second center axis substantially aligned with the center axis of the channel in the first member.

Abstract: Launch vehicle systems and methods for landing and recovering a booster stage and/or other portions thereof on a platform at sea or on another body of water are disclosed. In one embodiment, a reusable space launch vehicle is launched from a coastal launch site in a trajectory over water. After booster engine cutoff and upper stage separation, the booster stage reenters the earth's atmosphere in a tail-first orientation. The booster engines are then restarted and the booster stage performs a vertical powered landing on the deck of a pre-positioned sea-going platform. In one embodiment, bidirectional aerodynamic control surfaces control the trajectory of the booster stage as it glides through the earth's atmosphere toward the sea-going platform. The sea-going platform can broadcast its real-time position to the booster stage so that the booster stage can compensate for errors in the position of the sea-going platform due to current drift and/or other factors.