Abstract: An aircraft launch apparatus including a bottom attachment assembly configured to receive a fixed wing aircraft, the bottom attachment assembly including a saddle movable between an open position and a locked position, the saddle including one or more front engagers and one or more rear engagers configured to engage the fixed-wing aircraft, the one or more front engagers are each configured to engage a top and a bottom of a respective wing of the fixed-wing aircraft; a plurality of landing legs connected to the bottom attachment assembly; and a top attachment assembly connected to the bottom attachment assembly and configured to receive a flexible member.

Abstract: A method of delivering heavy payload using an autonomous UAV able to deliver supply by way of airdrop with more precision and at a lower cost. The UAV is equipped with two movable wing systems that rotate from a stowed position to a deployed position upon jettison of the UAV from a mothership. The UAV can be controlled remotely or it can operate autonomously and the movable wings can include ailerons to effectuate flight control of the UAV. The UAV can be reusable or can be an expendable UAV.

Abstract: There is provided an expandable strut assembly for a wing of an aircraft, having a strut with a strut cross section with an airfoil shape, and the strut having an outboard end coupled to the wing, an inboard end coupled to a fuselage, and an elongate body, and having at least one shape transition assembly connected to the strut. Each shape transition assembly is configured to transition the strut between a contracted position and an expanded position, and is configured to transition the strut cross section between a contracted airfoil shape and an expanded airfoil shape. Each shape transition assembly has a shape transition mechanism attached to an interior of the strut. The shape transition mechanism includes fixed length structural members, and a drive mechanism of variable length structural member(s), includes an actuation mechanism connected to the shape transition mechanism, and an activation mechanism coupled to the actuation mechanism.

Abstract: Technology for orbit raising of multiple spacecraft launched with a single launch vehicle. Two or more spacecraft are configured in a stacked launch configuration in which a lower spacecraft is mechanically coupled with a payload adapter of a launch vehicle with one or more upper spacecraft above the lower spacecraft. Propellant that is stored in the lower spacecraft during launch is transferred to an upper spacecraft in the stack after launch. The propellent may be used by the upper spacecraft for an orbit raising maneuver that raises the orbit of at least the upper spacecraft from a first orbit to a second orbit. Storing the propellant in the lower spacecraft lowers the center of mass of the stack during launch. Lowering the center of mass reduces the structural bending moment of the stack during launch, which allows a greater total launch mass.

Abstract: Rescue parachute deployment systems (RPDSs) and related techniques are provided to improve the safety and operational flexibility of unmanned aerial vehicles (UAVs). An RPDS includes a canopy assembly, a rotor guard disposed at least partially about the canopy assembly and configured to protect the canopy assembly from rotor strike damage as the canopy assembly is launched through a rotor plane of the UAV, and an ejector assembly configured to deploy the rotor guard into and the canopy assembly through a rotor plane of the UAV. The RPDS may also include a logic device coupled to and/or integrated with the ejector assembly and/or the UAV that is configured to determine a rescue parachute launch condition is active and to control the ejector assembly to deploy the canopy assembly through the rotor plane of the UAV.

Abstract: A rotary wing vehicle includes a body structure having an elongated tubular backbone or core, and a counter-rotating coaxial rotor system having rotors with each rotor having a separate motor to drive the rotors about a common rotor axis of rotation. The rotor system is used to move the rotary wing vehicle in directional flight.

Abstract: A launcher device includes a hopper having an open end disposed beneath a stack of UAVs. A retainer retains the UAVs in the hopper and releases one of the UAVs at the hopper's open end. A movable carriage disposed beneath the retainer receives the released UAV. The carriage is operable to be moved along a first direction from beneath the retainer to a terminus and subsequently operable to be moved along a second direction from the terminus to beneath the retainer. When moved in the first direction when the released UAV is on the carriage, the carriage moves the released UAV in the first direction to the terminus. A ramp aligned with the carriage guides the carriage along the ramp as the carriage is moved along the first and second directions.

Abstract: There is provided an extendable compression chain system for extending a structure. The system includes a track assembly, a curved guide assembly, an extendable compression chain assembly, an actuation mechanism, and a mechanical power apparatus. The extendable compression chain assembly is configured to travel along the track assembly and to follow the curved portion of the track assembly, to move from a retracted position to an extended position, to extend the structure coupled to the extendable compression chain assembly. The extendable compression chain assembly includes a compression chain structure having a first end, a second end, and modules. The modules are movable between a rigid position and a collapsed position, as the compression chain structure follows the curved portion of the track assembly, and wraps around the curved guide assembly. The extendable compression chain assembly includes an actuation end fitting and a structure interface end fitting.

Abstract: An aerial vehicle safety apparatus includes a safety mechanism, a drive mechanism, an ejection mechanism, and a control mechanism. The safety mechanism is used for securing safety of at least one of an aerial vehicle and an object outside the aerial vehicle. The drive mechanism includes at least one drive unit serving as a drive source of the safety mechanism. The ejection mechanism ejects the drive mechanism together with the safety mechanism. The control mechanism controls operations of the drive mechanism for the drive mechanism to drive the safety mechanism after the ejection mechanism starts ejection of the safety mechanism.

Abstract: An aircraft (41) including a fuselage (14) having a skin (15) and extending along a longitudinal axis (39) from a front end to a rear end (17) of the aircraft, and an engine (30) including an air intake (31) forming an opening in the skin (15) and an exhaust (32) forming another opening in the skin (15). The engine is in a rear fuselage section, in which the exhaust (32) is situated ahead of the air intake (31) along the longitudinal direction (39).

Abstract: An amphibious aircraft has a tricycle landing gear that is fixed. Each member of the landing gear is protected in the forward direction by a hydrodynamic protector, or vane, or shoe, such as may tend to create lift when brought into engagement with water, as during landing. The landing gear protector vanes may be mounted to move with extension and retraction of the landing gear. The landing gear wheels protrude to extend partially downwardly proud of the sole of the shoe. The shoes may include sacrificial wear members for ground engagement.

Abstract: Resilient unmanned aerial vehicle landing platforms are disclosed herein. An example device includes a base plate having protuberances that are arranged into rows of concentric rings, each of the protuberances being a conical member that extends orthogonally from the base plate, wherein each of the protuberances is resilient and are adapted to arrest and protect the drone during landing.

Abstract: A wing structure for a vehicle includes a plurality of multi-connecting-rod structures, the multi-connecting-rod structures are arranged along the main body of the vehicle, each of the multi-connecting-rod structure being arranged in a direction extending from a main body of the vehicle to a wingtip, each of the multi-connecting-rod structures comprising a plurality of connecting rods, and the connecting rods that are adjacent to each other being connected by a motor, a plurality of groups of ribs are sleeved onto each of the multi-connecting-rod structures, and each group of the ribs comprises a plurality of rib units, wherein in the same group of the ribs, adjacent rib units are connected by a ball hinge. The present technical solution can perform adjustment on a complex flow field or environment, the motion speed and the motion efficiency are significantly improved, and high maneuvering actions can be achieved.

Abstract: Hybrid-electric aircraft and a series hybrid powertrain configured to power the aircraft for a medium-haul flight. The series hybrid power train includes a plurality of energy storage units, at least one range extending generator, and a plurality of electric propulsors, each coupled to a distribution bus. The electric propulsors can produce a maximum thrust of at least 15 MW. During a cruise regime, the hybrid-electric aircraft can have an airspeed of at least 0.7 Mach at an altitude of less than 32000 feet, and the plurality of electric propulsors can have a fan pressure ratio of between 1.15 and 1.19. The hybrid-electric aircraft can have a degree of hybridization of at least 25% for the medium-haul flight and carbon dioxide equivalent (CO2e) well-to-wake greenhouse gas (GHG) emissions less than 0.25 lbs/Available Seat Mile (ASM).

Abstract: A shock load attenuation device is provided. The shock load attenuation device includes a crushable material; a first compartment in the crushable material surrounding a first line; and a second compartment in the crushable material surrounding a second line. In response to the first line being acted upon by a first force and the second line being acted upon by a second force, a first loop in the first line is configured to slide along the second line and a first loop in the second line is configured to slide along the first line, crushing the crushable material.

Abstract: A system and method for carrying an aeronautical or launch vehicle to altitude for release to flight may involve a multiplicity of mounting elements affixed to a carrier aircraft in distributed fashion along a mounting axis. Each mounting element may include a cradle and a retention strap. Each retention strap may be suspendedly attached to a respective cradle, and actuatable from a retention configuration to a release configuration. The retention configuration allows the retention straps to clampingly secure the vehicle to the respective cradles. The actuation of the retention straps from the retention configuration to the release configuration may disable the clamping securement and thereby release the vehicle to drop away from the cradles. For one or more of the retention straps, the actuation may be by way of detonating at least one corresponding pyrotechnic fastener.

Abstract: An aircraft landing platform for a passenger carrying aircraft has a landing module that is moveable between a landing position and a gate position, the landing module has a turntable that orients a door of aircraft to facilitate disembarkment of the passenger(s).

Abstract: A system is provided for an aircraft. This aircraft system includes a propulsion system, and the propulsion system includes a first thermal engine, a second thermal engine and a first electric machine. The propulsion system is configured to operate the first thermal engine and the second thermal engine, without operating the first electric machine, during a first mode of operation to provide aircraft thrust. The propulsion system is configured to operate the first electric machine and the second thermal engine, without operating the first thermal engine, during a second mode of operation to provide the aircraft thrust.

Abstract: An unmanned flying device including a body; a first blade and at least a second blade; a coupling assembly for coupling the first blade and the at least second blade to the body, wherein the coupling assembly urges the collapsing of the first blade and the at least second blade towards the body; and wherein both the first blade and the at least second blade are rotatable about the body, and wherein the first blade and the at least second blade are deployable away from the body via rotation of the first and the at least second blades about the body.

Abstract: An anchor for an aircraft. The anchor comprises a jack comprising a housing and a head that is able to move in translation in relation to the housing along an elevation axis, the head having three degrees of rotational freedom respectively about a longitudinal axis as well as a transverse axis and the elevation axis, the anchor comprising a member for taking up forces surrounding the jack and provided with a fastening suitable for being secured to the aircraft.