Abstract: Aspects of this disclosure relate to externally accessible auxiliary power unit (APU) pump assembly, comprising: a pump configured to pressurize an accumulator that is used to start an APU of an aircraft; a pressure gauge for the accumulator; and a support frame configured to be mounted within an outer wall of the aircraft, wherein the support frame defines an externally accessible compartment and secures the pump and the pressure gauge within the externally accessible compartment.

Abstract: An aerial vehicle adapted for vertical takeoff and landing using mounted thrust producing elements. An aerial vehicle which is adapted to vertical takeoff with the forward rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle uses one or more thrust producing elements on both of the right and the left sides. The aerial vehicle may have one or more front thrust producing elements and one or more rear thrust producing elements on both of the right and the left sides of a main vehicle body.

Abstract: A helicopter includes annular rotors surrounding a fuselage. Rotor blades extend radially outwardly from each annular rotor. One or more motors is provided. Each motor rotates a roller, which drives each annular rotor by traction. In an embodiment with two rotors, one rotor rotates in one direction and the other rotor rotates in the opposite direction. A swash device with a grooved outer cylindrical surface engages the free end of a crank arm of each rotor blade to provide collective and cyclic pitch control. Actuators, which may be electromechanical or hydraulic, control positioning and movement of the swash device. Batteries, an electric generator and/or a hydrogen fuel cell may supply electric power.

Abstract: An aircraft (100) with a rotary wing (40) is equipped with a propulsion system (10). The aircraft (100) includes a rotating mast (50) that rotates the rotor wing (40). The propulsion system (10) includes a pole (20) mechanically connected to the rotating mast (50) of the aircraft (100), where at least one end of the pole (20) is equipped with a motor (30) configured to rotate the pole (20) around the axis of the rotating mast (50) in such a way that the rotation of the pole (20) can be used to rotate the rotating wing (40). At each end of the pole (20) is placed a motor group (30), where each motor group (30) includes a pair of counter-rotating propellers (32,32), said pair of counter-rotating propellers (32,32?) being arranged in such a way as to generate a rotational torque to rotate the pole (20).

Abstract: A method for producing a satellite to facilitate the inclusion of one or more reflector antennas on a surface of the satellite is disclosed. A reusable generic configuration is determined in advance separately from the satellite mission. The generic configuration generally features the following parameters for each reflector: diameter, focal distance, offset distance of the reflector in the deployed position, position of the deployment device, position of the radiofrequency source. The generic configuration is determined such that an antenna points by default towards the centre of the earth when its reflector is in a deployed position. A specific configuration step then consists of defining a limited number of specific parameters depending on the satellite mission. The specific configuration is rendered possible in particular by controlling the deployment device, i.e., by changing the direction in which the antenna points, once the reflector has been deployed.

Abstract: Described is an aircraft suite having an aircraft seat for use by a passenger, the aircraft suite also having a controller, for controlling a number of output states of the aircraft suite, the controller having a logic condition receiver for receiving a logic condition input, and distance measurement equipment for measuring a distance between a first location within the suite and a second location within the suite, and providing a distance input to a distance receiver of the controller, wherein, in use, the controller controls at least one of the output states of the aircraft suite based upon both the logic condition input and the distance input. The invention also provides a method of controlling an environment within an aircraft suite.

Abstract: Methods and systems for implementing a Jupiter aerospace mission can enable delivery of a science payload to a Jupiter orbit on a direct Earth-to-Jupiter trajectory. Solar power and use of avionics also allow a fast assembly, integration, and test process compared to past outer Solar System missions. The spacecraft can include an aerodynamic forebody, a shell, and a thermal protection system. The spacecraft can manage the radiation environment, generate solar power, and return data to Earth with a robust radio-frequency (RF) amplification and antenna gain.

Abstract: Provided is a configuration construction and attitude control method for a pyramid deorbit sail. By taking into consideration environmental perturbation like atmospheric resistance perturbation and non-spherical earth perturbation, a dynamics model featuring three-dimensional orbit-and-attitude coupling based on position vectors and quaternion descriptions, the deorbit sail is taken as a rigid body, a spacecraft body is taken as a mass point, airflow obstruction is considered in the windward area, thereby improving the precision of the dynamics model; based on this model, the law of influence of the configuration parameters in the deorbit sail, such as a cone angle and a strut length, on the attitude stability and deorbiting efficiency of the spacecraft in different cases is analyzed, the configuration parameters of the pyramid deorbit sail system are analyzed and optimized according to the derived law, so as to obtain a pyramid deorbit sail achieving high attitude stability and high deorbiting efficiency.

Abstract: An outer space-based reusable manufacturing and assembly system including at least one joint that comprises at least one receiver component, at least one strut that engages the at least one receiver component on the at least one joint and a joining element that provides for engaging and disengaging the at least one joint with at least the at least one strut so that either the at least one joint and the at least one strut are usable for another mission. Two other systems are also disclosed.

Abstract: A spacecraft chassis includes a chassis body defined by first and second opposing sides bound by a perimeter, wherein at least one heat-generating component is configured to be secured directly to the chassis body, and at least one heat dissipating feature configured to radiate heat generated from the at least one heat-generating component into outer space.

Abstract: A mobility vehicle hub configured to function as a terminal for an air mobility vehicle, a ground mobility vehicle, or a water mobility vehicle, includes a plurality of layers through a combination of: a water layer connected to the surface of water and having an entrance for a water mobility vehicle; a port layer having a take-off and landing pad for an air mobility vehicle; or a ground layer configured to be connected to a ground and having an entrance for a ground mobility vehicle, wherein an elevation passage is provided between the layers, the elevation passage has an internal space extending in an up-down direction of the mobility vehicle hub, the internal space is connected to each of the water, port and ground layers, and the air mobility vehicle, the ground mobility vehicle, or the water mobility vehicle is lifted or lowered through the internal space.

Abstract: An aircraft emergency parachute deployment system (AEPDS) is disclosed. The AEPDS includes a parachute assembly coupled with an aircraft, a ballistic rocket assembly coupled to a top portion of the parachute assembly by a lanyard, an actuator for initiating launch of the ballistic rocket; and a control module configured to receive aircraft orientation measurements and controlling launch of the rocket when the spatial orientation the aircraft is within a pre-selected range of values.

Abstract: An auxiliary power unit enclosure of an aircraft includes a space frame configured to carry a load and defining an auxiliary power unit compartment. The space frame includes a plurality of frame elements coupled together at a plurality of nodes. The auxiliary power unit enclosure also includes a fairing coupled to and surrounding the space frame.

Abstract: In an aspect this disclosure is directed at a propulsor assembly powered by a dual motor system. The aircraft may comprise a propulsors. The electric aircraft may also include a driveshaft that is mechanically coupled to the propulsor, wherein a driveshaft is configured to provide mechanical power to the propulsor. The aircraft includes a plurality of electric motors. The electric motors may be configured to impart rotational energy to the driveshaft. Wherein each electric motor includes a stator and a rotor. Each electric motor is selectively engaged to the driveshaft by a freewheel clutch.

Abstract: The invention relates to a wing arrangement (10) for a projectile (1). The wing arrangement (10) comprising: a wing shaft (20) extending longitudinally between a proximal end (21) and a distal end (22) along a wing shaft axis (R), the proximal end (21) being configured to be inserted into a wing shaft aperture (6) in a circumferential wall (2) of the projectile (1), the wing shaft (20) being rotatable around the wing shaft axis (R); a wing blade (30) connected to the distal end (22) of the wing shaft (20); a deployment arrangement (40) configured to control a rotational movement of the wing shaft (20) around the wing shaft axis (R), whereby the wing blade (30) is deployed from a folded state to a deployed state.

Abstract: A transparency includes a plurality of sheets. Each sheet of the plurality of sheets can include a first major surface, an opposite second major surface, and a peripheral surface between the first major surface and the second major surface. The transparency can further include: an inter-sheet layer positioned between the first major surface of one of the sheets of the plurality of sheets and the second major surface of an adjacent sheet of the plurality of sheets; and a wireless sensor positioned in the inter-sheet layer. The wireless sensor includes a sensory portion configured to measure information representative of a condition of a portion of the transparency and a wireless transmitter configured to wirelessly transmit the received information to a wireless receiver.

Abstract: A universal external port is proposed to add new functionality to or replace existing functionality of an already deployed spacecraft (e.g., a satellite in orbit). The universal external port is mounted on an external surface of the spacecraft and configured to connect to different types of external modules that have different functions, without removing components from the spacecraft other than one or more components of the universal external port. A communication interface onboard the spacecraft is configured to wirelessly receive a software patch from an entity remote from the spacecraft (e.g., from a ground terminal or other spacecraft) to program the spacecraft to change operation of the spacecraft to utilize the external module when the external module is connected to the universal external port.

Abstract: An anti-torque system (10) for a helicopter (1) is described that comprises: an electric power supply unit (15); at least one first rotor (17), operatively connected to an electric power supply unit (15) and operable by the electric power supply unit (15) so as to rotate with a first variable angular speed; and at least one second rotor (25) operatively connected to electric power supply unit (15) and operable by the electric power supply unit (15) so as to rotate with a second variable angular speed.

Abstract: A foot pedal, which swings a waste flap from a closed position to an opened position, is disposed near a section on a floor of an aircraft lavatory unit directly below a waste compartment. A foot pedal support mechanism is configured such that the foot pedal at the upper limit position is inclined and supported with a foot pedal rear end located directly below the waste compartment being located above a foot pedal front end away from the waste compartment and that the foot pedal rear end swings in a vertical direction by using the foot pedal front end as a fulcrum.

Abstract: Disclosed embodiments include a blown flying wing tailsitter aircraft leveraging distributed electric propulsion to enable a combination of exceptional aerodynamic performance and high bandwidth control in both vertical (hovering) and horizontal flight. A pilot in one disclosed embodiment may be in the prone position during cruise and standing during vertical flight phase to enable greater aerodynamic efficiency with minimal engineering complexity and a small landing footprint. Batteries may be disposed in a high-volume wing sealed off from the piloted compartment to increase the safety of the pilot while distributing the inertial load of batteries and motors across the wingspan, thus enabling a lighter and simpler structure. Propellers may be above head-level for operational safety when the aircraft is standing on the ground.