Abstract: A flight control apparatus for fixed-wing aircraft includes a first port wing and first starboard wing, a first port swash plate coupled between a first port rotor and first port electric motor, the first port electric motor coupled to the first port wing, and a first starboard swash plate coupled between a first starboard rotor and first starboard electric motor, the first starboard electric motor coupled to the first starboard wing.

Abstract: Method and apparatus for providing a modular unit through a confined entryway. The modular unit includes portions that are foldable between a transit configuration and a deployed configuration. In the transit configuration, the modular unit can fit through the confined entryway. In the deployed configuration, the modular unit may not fit through the door, but can have larger dimensions. Once past the confined entryway, the foldable portions can be quickly moved to the deployed configuration and fixed in place with a small number of pins or other fasteners. In some instances, multiple modular units may be attached together to form a larger unit. The modular units can include foldable portions, and the modular units can be connected together with a relatively small number of fasteners.

Abstract: The invention relates to a propulsion system concept that is a propulsion system that is integrated in the hull of an aerial vehicle (1), which propulsion concept comprises at least one differential velocity fan (4), which is arranged on a shaft driven by one or more power units (2). The propulsion concept is intended to provide short takeoff and landing distances, high flight speed (high subsonic to transsonic) and to be able to provide low IR signature, low radar signature, a small cross section and low air resistance. The propulsion concept is called HPVO (High Performance Optimized Versatile propulsion). The invention is useful both for air vehicles of the type for conventional takeoff and landing, “CTOL” (Conventional Take Off and Landing), “Chair” and for vertical takeoff and landing, “V (t) OL” (Vertical (Take) Off and Landing’) and the flying wing (blended-body). The concept is applicable to both large and small aircraft, manned as well as unmanned aerial vehicles.

Abstract: An unmanned aerial vehicle (UAV) is disclosed that includes a retractable payload delivery system. The payload delivery system can lower a payload to the ground using an assembly that secures the payload during descent and releases the payload upon reaching the ground. The assembly can also include a bystander communication module for generating cues for bystander perception. While the assembly securing the payload is being lowered from the UAV, the bystander communication module can generate an avoidance cue indicating that bystanders should avoid interference with the assembly. The assembly also includes sensors that generate data used, at least in part, to determine when the descending assembly is at or near the ground, at which point the assembly releases the payload. The bystander communication module can then cease the avoidance cue and the UAV can retract the assembly.

Abstract: A double-deck airplane that facilitates passenger embarking/disembarking and cargo loading/unloading operations in order to maximize the number of flight missions carried out in a given time. The floors of its upper and lower decks are planar surfaces extending continuously inside the fuselage in at least the inner space of the fuselage intended for the payload; the lower deck is located at a height from the ground that allows carrying out passenger embarking/disembarking via equipment incorporated in the airplane without any external airport ground equipment; passenger and/or cargo compartments are distributed on the upper and/or lower decks; and the lifting structure is disposed in the airplane in a manner that none of its components crosses the upper and lower decks.

Abstract: A thrust recovery outflow valve includes a valve frame for mounting on an aircraft exterior skin and a bi-fold valve door that is mounted within the valve frame. The bi-fold valve door includes an aft door section, a forward door section, and a ram air flap. The aft door section is rotatable between an aft door closed position and an aft door full-open position and has a ram air opening formed therein. The forward door section is rotatable between a forward door closed position and a forward door full-open position. The ram air flap is rotationally mounted on the aft door section and is rotatable between a flap closed position, which prevents air flow through the ram air opening, and a flap open position, which allows air flow through the ram air opening.

Abstract: A deployment system for deploying a store from an aircraft includes a lock member that selectively engages the store to the deployment system, an ejector that selectively ejects the store from the deployment system, and a deployment system controller communicatively coupled to the lock member and to the ejector, the system controller communicatively coupled to the aircraft to receive commands from the aircraft, wherein upon receipt of a master arm command from the aircraft the system controller maintains the lock member in an engaged state relative to the store, and wherein upon receipt of a fire command from the aircraft the system controller disengages the lock member from the store and activates the ejector to eject the store from the deployment system.

Abstract: A rotary drive assembly is provided. The assembly includes a tip hinge box, a body hinge box pivotably coupled to the tip hinge box, a rotary actuator positioned within the body hinge box, and a linkage mechanism coupled between the rotary actuator and the tip hinge box, the linkage mechanism including a first linkage fixedly coupled to the rotary actuator, and a second linkage coupled between the first linkage and the tip hinge box, wherein rotation of the rotary actuator causes the tip hinge box to rotate relative to the body hinge box.

Abstract: The present invention provides lightweight fluid-jet thrust pack which provides three rotational axes and reduced restriction of fluid flow to the output nozzles. A first rotational axis is provided by a first rotatable coupling that is concentric with a coupler for a hose supplying pressurized fluid. The top of the first coupling has a splitter which directs incoming fluid into two splayed stub supply pipes. A preformed, reinforced rubber hose connects each stub supply pipe to one of a pair of coaxial rotatable couplings at opposite ends of a tiltable cross arm assembly that is pivotally secured to tower support bracket that is secured to the first rotatable coupling. An outward rotatable portion of each of the coaxial rotatable couplings is equipped with one boot-mounting platform and a downward-projecting jet nozzle that is in communication with the stub receiver pipe of the same rotatable coupling.

Abstract: An inlet for an aircraft nacelle may comprise a nanoreinforced polyimide composite lip skin. The nanomaterials may increase thermal conductivity and decrease microcracking in the lip skin. A lip skin for an inlet with an electric heater may comprise a surface layer, an outer composite skin, an electric heater, an inner composite skin, and a thermal barrier coating. A lip skin for an inlet with a pneumatic deicing system may comprise a surface layer, a composite skin, and a thermal barrier coating.

Abstract: An aircraft body comprises a support structure. A gas turbine engine comprises a gas generator having at least one compressor rotor, at least one gas generator turbine rotor, and a combustion section. A fan drive turbine is positioned downstream of at least one gas generator turbine rotor, and is configured to drive a shaft. The shaft engages gears to drive a plurality of fan rotors. The gas turbine engine is embedded into the support structure such that there is an inlet leading through the support structure to the fan rotors to deliver air to the fan rotors. A gas turbine engine is also disclosed.

Abstract: A fiber-reinforced composite structure includes a cut edge; an elastomeric cap covering the cut edge; and an adhesive sealant bonding the elastomeric cap to the cut edge. The fiber-reinforced composite structure is joined to a component and the elastomeric cap includes a generally Z or L-shaped cap with a web bonded to the cut edge of the fiber-reinforced structure and a flange bonded to the component and extending away from the fiber-reinforced structure.

Abstract: A motionless skew detection system for an aircraft is disclosed, and includes a flight control surface of an aircraft wing, two drive mechanisms for operating the flight control surface, a first load sensor and a second load sensor for each of the two drive mechanisms, and a control module. Each of the two drive mechanisms are located on opposing sides of the flight control surface and each of the two drive mechanisms include at least a first linkage including a first outer surface and a second linkage including a second outer surface. The first load sensor is disposed along the first outer surface of the first linkage and the second load sensor is disposed along the second outer surface of the second linkage. The control module is in signal communication with the first load sensor and the second load sensor of each drive mechanism.

Abstract: This disclosure provides egress and ingress for unmanned aerial vehicles (UAVs) from a fulfillment center (FC) to perform deliveries of products and return to the FC from such deliveries while providing minimal exposure of an interior of the FC. The UAV may be used to deliver the cargo from the FC to a destination, and then return to the FC to retrieve other cargo for another transport to another destination. In some embodiments, departing UAVs may be launched from the FC through a launch bay and returning UAVs may land upon a conveyance system to await being transported back into the FC. A flight coordinator may also provide assignments to the UAV based upon a current state of the UAV and other nearby UAVs and also based on a current order backlog of the FC and/or other considerations.

Abstract: Space craft comprising a body, at least one pair of supporting arms, a first device mounted on a first supporting arm and a second device mounted on a second supporting arm. The first arm is rotatably mounted on the body of the craft about an axis of rotation. The second arm is fixed to the body, and in which craft of the first device and the second device at least one is offset from the axis of rotation of the first arm. The pair of supporting arms further comprises a hollow module for the rotatable mounting of the first arm on the body. The mounting module comprising an opening through which the axis of rotation and the second supporting arm pass.

Abstract: A Marman clamp is disclosed. The Marman clamp includes a release mechanism with either pins or tubes formed with a shape memory alloy. The release mechanism opens and closes the clamp depending on the temperature of the pins or tubes. The temperature of the pins or tubes may be based on whether a space vehicle including the clamp is in a direct line of sight of radiation from the sun. Alternatively, a heat source may control the temperature of the pins or tubes. The Marman clamp may also open and close as a result of an independent force applied to the release mechanism.

Abstract: A VTOL (vertical take-off and landing) aerial flying vehicle comprising an inner frame, a gimbal system and an outer frame, the inner frame comprising a propulsion system and a control system. The propulsion system being able to generate a lift force. The VTOL may also include a decoupling mechanism having either a linear or non-linear beam coupled to a ring. The beam may optionally include sliders at ends thereof that provide an additional rotation freedom to the inner frame.

Abstract: An engine system has a gas generator, a bi-fi wall surrounding at least a portion of the gas generator, a casing surrounding a fan, and the casing having first and second thrust reverser doors which in a deployed position abut each other and the bi-fi wall.

Abstract: Systems and methods provide for a guided lift system utilized for maneuvering payloads. According to aspects of the disclosure, a guided lift system may include a lift unit attached to a payload, at least two control tethers attached to the lift unit, and at least two control units fixed in positions and capable of adjusting the lengths of the control tethers. Coordinated length adjustments of the control tethers pulls the lift unit and payload in a desired direction to a desired delivery location.

Abstract: An aircraft landing gear comprising an axle (3) intended to receive a wheel (4) comprising a rim (6) mounted to rotate on the axle (3) by means of at least one rolling bearing (8). The rolling bearing (8) comprises an inner ring (11) mounted around the axle (3) and an outer ring (12) rotationally secured to the rim (6) of the wheel (4). The landing gear further comprising a measurement device (21) intended to perform measurements of at least one operating parameter of the landing gear. The measurement device (21) is incorporated in the rolling bearing (8) by being secured to one of the inner or outer rings of the rolling bearing (8).