Abstract: A system and method for lift augmentation of an aircraft having a wing with a leading edge and a trailing edge extending along a wingspan, a plurality of thrust-producing devices connected to the bottom of said wing, at least one flap connected to an inboard portion of said wing proximate the trailing edge, and an aircraft roll control device connected to said wing, wherein the improvement comprises a plurality of slipstreams associated with a plurality of thrust producing devices and a flap adaptable to deflect from a chord of the inboard portion of the wing.

Abstract: An aircraft landing gear is disclosed having a landing gear leg attachable at a first end to an aircraft, and an axle beam, both the landing gear leg and the axle beam being rotatably mounted. The axle beam is rotatable between a first position, in which a first end of the axle beam is a first (shorter) distance from the first end of the landing gear leg, and a second position, in which said first end of the axle beam is a second (longer) distance from the first end of the landing gear leg. A biasing member is configured to be able to bias the axle beam towards the second position. An aircraft, a blended wing body aircraft, and a method of operating an aircraft are also disclosed.

Abstract: An aircraft includes a fuselage, a wing disposed above the fuselage, a pylon connecting the wing to the fuselage, and a plurality of internal combustion engines housed in the fuselage. The pylon vertically traverses the fuselage and is fixed to an upper portion and a lower portion of the fuselage. Among the plurality of internal combustion engines, a first internal combustion engine and a second internal combustion engine are disposed bilaterally symmetrically about the pylon and are fixed to the pylon.

Abstract: A system and method for an aircraft evacuation system with hydrogen inflation is disclosed. The system includes an aircraft having an integrated hydrogen-electric engine. A fuel cell stack for powering an aircraft motor of the integrated hydrogen-electric engine. A hydrogen fuel source in fluid communication with the fuel cell stack, the hydrogen fuel source containing hydrogen. An inflatable slide and a pump operably coupled with the hydrogen fuel source and the inflatable slide to selectively pump the hydrogen to the inflatable slide for inflating the inflatable slide.

Abstract: A paramotor assembly, a unibody frame for such a paramotor assembly, and a method of making a paramotor assembly are provided. The paramotor assembly includes a monolithic, non-metallic molded body, a hoop extending at least partially around the molded body, and spars coupling the hoop and the molded body. Each of the spars includes an inner end coupled to the molded body and an outer end coupled to the hoop. The inner ends of the spars are spaced from one another and held in position relative to one another by the molded body. The method includes molding the monolithic molded body from the non-metallic material, attaching inner ends of the spars to the molded body at spaced apart inner locations, and attaching outer ends of the spars to the hoop at spaced apart outer locations.

Abstract: A docking system for docking an aerial vehicle, including an interface configured to secure the docking system to a stationary element located above the ground, a housing, mechanically coupled to the interface, a docking magnetic member located in the housing, the docking magnetic member is configured to attract an aerial magnetic member of the aerial vehicle, a docking element mechanically coupled to the housing, where the docking element defines a minimal distance between the docking magnetic member and the aerial vehicle when the aerial vehicle docks in the docking system, and a maneuver mechanism for adjusting a distance between the docking element and the docking magnetic member.

Abstract: This aeronautical equipment for an aircraft, comprising a part configured to be positioned at the level of a skin of the aircraft and means for reheating this part comprising a closed-circuit thermodynamic loop in which a phase-change heat transfer fluid circulates, is wherein it includes means for monitoring the fluid pressure in the loop in order to detect and report a malfunction of the equipment.

Abstract: A hydrogen storage system comprises a hydrogen tank and a system for controlling hydrogen evaporation in the hydrogen tank. This control system comprises a hydrogen discharge pipe connected to the hydrogen tank, on the one hand, and to a controllable valve, on the other hand, as well as a processing unit configured to control the valve as a function of the pressure in the tank. The hydrogen storage system further comprises a fuel cell permanently connected to the hydrogen tank and the processing unit being electrically powered by the fuel cell.

Abstract: An anti-icing system may comprise a deicing boot of an elastomeric material comprising a plurality of tubes, wherein the deicing boot comprises a first set of tubes and a second set of tubes, wherein each of the first set of tubes and the second set of tubes have a corresponding end, and wherein the corresponding end is coupled to a continuous dual wrap end closure.

Abstract: A spacecraft includes a semi-rigid solar array and a main body structure, the main body structure configured as a convex polyhedron and including an aft and a forward face disposed opposite to the aft face and at least four side faces disposed between and approximately orthogonal to the aft face and the forward face. The solar array includes a number of panels linked together with flexible couplings. In an undeployed configuration, panels of the solar array cover at least two adjacent side faces, the flexible couplings providing an articulable joint approximately aligned with a line along which the two adjacent side faces are joined and connecting a first panel of the solar array and a second panel of the solar array, the first panel being proximal to a first side face and the second panel being proximal to a second side face.

Abstract: A tiltrotor aircraft is designed to accommodate rotors of different diameters, as well as corresponding wings and fuselages with different span and length, while maintaining very high parts commonality, especially with respect to drive train and power source. This enables design and operation of a fleet of such aircraft with significantly different rotor diameters, which are nevertheless optimized for different missions. In preferred embodiments the rotors are configured to have high stiffness and low weight to reduce aero-structural dynamic issues across the fleet. Also in preferred embodiments drive systems are designed for a full range of speed, torque, and power associated with all intended rotors. Turboshaft engine speeds are restricted to a narrow RPM range, so that a single gearset can be replaced to achieve the desired rotor RPM. Also in preferred embodiments, aircraft in a fleet can differ in folded length, empty weight, payload length by up 50%.

Abstract: A system and method for preventing back-drive in a braking system for a rotary actuator. The braking system comprises a housing and split cam design. A driving cam located within the housing is associated with an upstream side of the braking system. The driving cam is configured to rotate when a torque is applied to the upstream side. The braking system has a wedging cam and a plurality of cylindrical rollers. The wedging cam located within the housing and is associated with a downstream side of the braking system. The wedging cam is configured to react and prevent back-drive motion when torque is applied to the downstream side. The plurality of cylindrical rollers is positioned between the wedging cam and the housing. The plurality of cylindrical rollers is configured to wedge between a surface of the wedging cam and the housing when the torque is applied to the downstream side.

Abstract: A guided projectile includes a body and a deployable wing in which the deployable wing is coupled to and enclosed by the body. A linear distance from the leading edge to the trailing edge of the wing defines a chord line that, in the stowed position, forms an angle with a plane containing the chord line and extending parallel to a longitudinal dimension of the wing in a deployed position.

Abstract: A landing gear door system, including a landing gear bay including an opening and accommodating a landing gear in a retracted position, a landing gear door for opening and closing the opening, an actuator for operating the landing gear door between an open and a closed position, a lock located in the landing gear bay and latching the landing gear door in the closed position, a stop fitting located in the landing gear bay and configured to be in connection with the landing gear door at least in its latched position. The landing gear door system further includes an additional actuator configured to apply a force to the landing gear door in its closed position and to elastically deform the landing gear door towards the landing gear door bay.

Abstract: The method for transporting a payload to a target location, comprises the following steps of providing a hybrid airship comprises a buoyancy enclosure, a gondola carried by the buoyancy enclosure and a payload carrier, and at least one propeller; flying the hybrid airship carrying the payload to a target location, flying the hybrid airship carrying the payload comprising generating a lift force with the at least one propeller. Flying the hybrid airship carrying the payload comprises tilting the longitudinal axis of the buoyancy enclosure to a positive pitch to generate an aerodynamic lift force when the hybrid airship carrying the payload moves longitudinally.

Abstract: A refueling system has a vehicle having a fuel tank connected to a deployable fuel hose, an end effector having controlled flight, the fuel hose connected at an end away from the first vehicle, through the end effector to a fuel connector under the end effector, a second vehicle having a fuel tank coupled through a pumping apparatus to a fueling port on an acquisition apparatus adapted to acquire the end effector and connect the fueling port and the fuel connector of the end effector, and control circuitry enabling controlled flight of the end effector, wherein the end effector is controlled to be acquired by the acquisition apparatus to couple the fuel connector with the fueling port and fuel is provided from the fuel tank of one of the vehicles to the fuel tank of the other of the vehicles through the pumping apparatus.

Abstract: The system and method of spin stabilizing a guided munition where a motor provides necessary de-spinning torque. The despun PGK portion of a guided projectile is already at high rate of spin relative to the projectile body and the motor is operated to maintain that rate.

Abstract: An aircraft propulsion system capable of improving the restartability of an engine is provided. An aircraft propulsion system includes: a plurality of engines (60-1 and 60-2); an electric generator connected to engine shafts (63-1 and 63-2); a plurality of electric motors; a plurality of rotors; and a controller (100) which controls an operation state of the plurality of engines (60-1 and 60-2). The controller (100) causes a part of the plurality of engines (60-1 and 60-2) to operate while stopping the remaining engine when a flight state is in a first state. The plurality of engines (60-1 and 60-2) include circulators (65-1 and 65-2). A plurality of communication pipes (68 and 69) which communicate the circulator (65-1) in the first engine (60-1) among the plurality of engines (60-1 and 60-2) with the circulator (65-2) in the second engine (60-2) are provided.

Abstract: A system for deploying an inflatable structure may include a balloon defining an envelope having a first stiffness, a valve assembly including a control valve, and a reactor defining a chamber having a second stiffness, the valve assembly disposed in fluid communication between the chamber and the envelope, the control valve selectively actuatable to control fluid communication between the chamber and the envelope, the second stiffness of the chamber greater than the first stiffness of the envelope, and the reactor foldable onto itself along the chamber and elastically deformable to unfold in response to an increase in pressure in the chamber.

Abstract: A compound helicopter includes a fuselage, a fixed wing, a rotary wing, and a barrier member. The fixed wing is fixed to the fuselage. The rotary wing is rotatably coupled to the fuselage. The barrier member is attached to a part, of the fuselage, that is above the fixed wing and is between the rotary wing and the fixed wing. The barrier member is configured to generate no lift upon forward flight.