Abstract: The present invention relates to a vertical take-off and landing module (200) for a fixed-wing aircraft (110), which includes at least one vertically-acting propulsion unit (240), actuator means (245) and support means (230), so as to be adapted to be operatively connected to said aircraft (110). The actuator means (245) can move the propulsion unit (240) from the inside of the module (200) towards the outside, and vice versa, so that the propulsion unit (240) is adapted to generate a substantially vertical propulsive force during the aircraft take-off and landing phases.

Abstract: A safety device capable of rapidly inflating a float, having sufficient buoyancy at the time of landing on water, and being lighter than a conventional safety device, and a flight vehicle including the safety device. A safety device includes a parachute, a bottomed cylindrical container that accommodates the parachute, and an ejection device that is provided in the container and ejects the parachute to the outside of the container. The parachute includes an umbrella body, a plurality of lines, a center cord, and a bag-shaped member. The bag-shaped member including an intake port connected to a ventilation port is provided outside a top portion of the umbrella body. The intake port of the bag-shaped member is provided with a check valve including a hinge portion and a plate member.

Abstract: An auxiliary storage box is detachable and storable in a storage box provided in a vehicle interior. The auxiliary storage box includes: an auxiliary box body; and an auxiliary box attachment. The auxiliary box body is storable inside the storage box. The auxiliary box attachment is detachably attached to the auxiliary box body and capable of supporting an auxiliary item used in combination with the auxiliary box body outside the auxiliary box body.

Abstract: An aircraft structure having a fuselage, an engine and an air inlet for receiving air for the engine. The air inlet has a cowl which surrounds an inlet opening. The air inlet has a compression surface and a transition shoulder. The air inlet additionally has a flow guide surface, which is arranged as a local elevation in a region of the transition shoulder and extends into the inlet opening. This flow guide surface designed as a local elevation contributes to improving the displacement of the boundary layer of a fluid flowing along the aircraft structure at the air inlet.

Abstract: Retrofittable satellite systems for an in-orbit host satellite comprising an enhancement module for adding a capability to the in-orbit host satellite, modifying the function of the in-orbit host satellite, and/or extending the function of the in-orbit host satellite. The in-orbit, retrofittable satellite system comprises a transfer vehicle for transferring the enhancement module from a first to a second location and a service vehicle for receiving the enhancement module from the transfer vehicle and installing the enhancement module on the in-orbit host satellite.

Abstract: An aircraft includes actuators coupled to a lift device. The aircraft also includes a lift device control interface disposed on a flight deck of the aircraft. The lift device control interface is configured to receive a pilot input. The aircraft further includes a flight control system configured to generate a command corresponding to a target lift device position. The flight control system is also configured to send the command to the lift device control interface to cause the lift device control interface to indicate the target lift device position. The flight control system is further configured to send a control signal to the actuators to set the lift device to the target lift device position.

Abstract: Hybrid propulsion systems that utilize liquid natural gas solid oxide fuel cells in a manner practical for use in aircraft that avoid the use of heavy batteries, provide transient response times suitable for use in aircraft, and/or simplify reactant pre-conditioning systems using a compressor and turbine pair operatively coupled to the solid oxide fuel cell. Such hybrid propulsion systems for an aircraft may include a liquid natural gas solid oxide fuel cell, a motor driven by electric power from the solid oxide fuel cell, a gearbox operatively coupled to the motor, and a turbofan engine configured to generate thrust for the aircraft. The turbofan engine may be configured to provide electric power and shaft power and may include a duct fan that is operatively coupled to the motor via the gearbox, with the duct fan being driven by mechanical power from the gearbox and by the motor.

Abstract: An aircraft, including a wing having an exterior with an exterior surface, a first power supply structure disposed in the wing, an electric motor electrically connected to the first power supply structure, a first heat exchanger disposed in the wing, where the first heat exchanger is disposed adjacent to, and in thermal contact with, at least a portion of the exterior of the wing, where the first heat exchanger is configured to transfer heat to the exterior surface, and a first coolant pump in fluid communication with the first heat exchanger and the first power supply structure.

Abstract: A vehicle front structure includes: an upper beam to which a headlight is fixed; a bracket installed side by side with the upper beam and formed to extend outward in a vehicle width direction from one end thereof fixed to a bulkhead of a vehicle, curve rearward at a point halfway to an outer end in the vehicle width direction of the vehicle, and extend rearward to the other end thereof fixed to a lower member of the vehicle; and an airbag sensor provided on the bracket.

Abstract: A seat mounting system having a seat rail and a seat fitting, wherein the seat rail has an upper flange with a plurality of heads thereon. The seat fitting comprises a main body having a void configured to receive the upper flange and at least some of the plurality of heads.

Abstract: A pickup bed storage system for storing and organizing objects in a bed of a pickup truck includes a mat that is positionable on the bed and extends between a front end and a rear end of the bed. A pair of rails is coupled to the mat. A container movably coupled to the pair of rails is slidable between the front end and the rear end of the bed. The container has a front wall, a back wall, and a peripheral wall that is coupled to and extends between the front wall and the back wall to define an interior space. The peripheral wall is expandable to adjust a volume of the interior space. A pulley mechanism is coupled to the container and the pair of rails to slide the container along the pair of rails.

Abstract: Provided is a neck supporting device including a housing capable of being attached to or detached from a seat, a main body capable of being withdrawn from the inside of the housing, the main body including two support portions disposed at two opposite sides of one surface of the main body, respectively, and configured to protrude toward a neck of an occupant, and a strap coupled to the two opposite support portions of the main body while having tension and having a neck support portion positioned between the two opposite support portions and configured to support the neck of the occupant.

Abstract: A cavity system for use on a vehicle is provided. The cavity system comprises a cavity having at least one of a front edge and a rear edge arranged orthogonally to the actual or intended direction of travel of the vehicle, and longitudinal edges. The front and/or rear and longitudinal edges define an opening. The cavity system also comprises at least one shock stabiliser protruding from a surface adjacent each longitudinal edge of the cavity into the ambient flow outside of the cavity. An aircraft comprising the cavity system is also provided.

Abstract: An aircraft wing (3) comprising an aerofoil structure (5) is disclosed. The aerofoil structure (5) comprises a load-carrying member (10) having stiffness properties selected such that the load-carrying member (10) twists in a predefined manner in response to bending of the load-carrying member (10). The aerofoil structure (5) further comprises an actuator (15A, 15B) which is fixedly mounted to the load-carrying member (10) and which is operable to bend the load-carrying member (10) to thereby cause the load-carrying member (10) to twist. An aircraft comprising the aircraft wing and a method of adjusting the twist in an aircraft wing are also disclosed.

Abstract: An unmanned aerial vehicle includes an airframe and a plurality of rotor assemblies operatively connected to the airframe and configured to propel the unmanned aerial vehicle. The air frame includes a plurality of tubes and a plurality of hardpoints. Each of the plurality of hardpoints may include a tubular protrusion for receiving one of the plurality of tubes. The unmanned aerial vehicle may further include structural adhesive bonding the tubular protrusion of each of the plurality of hardpoints to a corresponding one of the plurality of tubes.

Abstract: Systems, apparatuses, and methods provide for a door handle mechanism including a vent panel, a handle lever, and a four bar mechanism. The handle lever has a lift-to-open configuration. The four bar mechanism is coupled to the handle lever and the vent panel. The four bar mechanism is to time sequence operations to close an aircraft passenger door, latch the aircraft passenger door, lock the aircraft passenger door, and close the vent panel in response to the handle lever being toggled between a closed position and an open position.

Abstract: A seat armrest is provided. The seat armrest includes a support unit, having a fixed seat and a support rod extending upward from the fixed seat; wherein the support rod has an accommodation space, and the support pole is provided with a positioning slot section composed of a vertical displacement slot and a plurality of horizontal displacement slots communicated with each other; a casing unit, sleeved around the support rod and having an installation groove communicated with the accommodation space; and an adjusting rod, having a positioning protrusion and being pivot disposed on the installation groove of the casing unit.

Abstract: A payload delivery device is an apparatus designed to facilitate the delivery of emergency items to a target location via aerial vehicles. The apparatus includes a base strap, a plurality of holder straps, and a plurality of cargo straps. The base strap serves as the central structure of the apparatus that supports the plurality of holder straps and the plurality of cargo straps. The plurality of holder straps includes several straps designed to retain a parachute and the devices necessary to facilitate the deployment of the parachute. The plurality of holder straps is also designed to facilitate the operation of the parachute while securing the parachute to the base strap. The plurality of cargo straps include several straps that secure the payload to the apparatus. The plurality of cargo straps can also be arranged to accommodate the shape and size of the payload to be delivered using the apparatus.

Abstract: A wing for an aircraft, comprising a main wing and a high lift assembly which includes a body, and an assembly connecting the body to the main wing, so the body is movable between a retracted position and an extended position. The assembly comprises a track extending along a longitudinal axis between first and second ends, with an intermediate portion therebetween. A roller bearing ensures that the track moves along the longitudinal axis. The roller bearing comprises bearing units, each mounted to the main wing and having a bearing surface for engaging the elongate track. The units include a first and second end units and an intermediate unit wherein, relative to the longitudinal axis, the intermediate unit is positioned between the first end unit and the second end unit. The elongate track comprises a recessed portion which, in the retracted position, aligns the intermediate unit.

Abstract: The method of obtaining both, lifting force and thrust, required for horizontal flight of the vertical take-off and landing flying machine while maintaining horizontal flight stability of the machine which is realized due to suction atmospheric air to the inner cavity formed between coaxial mounted, multi-blade turbines (2, 18), the top and the bottom, which are counter-rotating relatively to each other, and remove the air outside under the machine; the conical turbines are mounted with the direction of wider, circular bases facing in front of them and which are mounted on the double-sided fixed bearings (4, 16) alongside the contour edge of the external ring (12), which is mounted using the distance spacers (13) form the inner side to the central housing (6) which is formed with the conical shape and which is the base where the both turbines (2, 18) are mounted using linear drives from the side of their smaller bases.