Abstract: An aircraft propulsion system is disclosed that includes at least one hybrid-electric powerplant for delivering power to an air mover for propelling the aircraft, wherein the at least one hybrid-electric powerplant includes a heat engine and an electric motor arranged in a parallel drive configuration or an in-line drive configuration.

Abstract: Technologies for providing emergency egress routes for a blended wing body aircraft are described herein. In some examples, the emergency egress routes are through a side cabin bulkhead and aft one or more cargo holds. In some examples, the blended wing body aircraft has wings that are high geometry wings. In these examples, the emergency egress routes do not penetrate an aft spar, reducing weight and increasing the integrity of the aircraft.

Abstract: A method (50) for orbit control of a satellite (10) in Earth orbit and for desaturation of an angular momentum storage device of the satellite, the satellite (10) including an articulated arm (21) suitable for moving a propulsion unit (31) within a motion volume included in a half-space delimited by an orbital plane when the satellite is in a mission attitude, the method (50) including a single-arm control mode using only the propulsion unit (31) carried by the articulated arm (21), the single-arm control mode using a maneuvering plan including only thrust maneuvers to be executed when the satellite (10) is located within an angular range of at most 180° centered on a target node in the orbit of the satellite (10), including two thrust maneuvers to be performed respectively upstream and downstream of the target node.

Abstract: A door that is adapted to separating two environments with different pressures and to an aircraft with such a door. The door may include a door leaf, a door frame having a door stop and a roller, and an actuating system having a latch element and an inward-moving drive system. The inward-moving drive system may include a puller shaft and a puller that is non-rotatably attached to the puller shaft. The puller may include a guide rail that moves along the roller during a rotation of the puller such that the puller moves the door leaf in direction of the first environment thereby disengaging the latch element from the door stop.

Abstract: An example method for launching a high-altitude balloon includes securing a launch collar around a balloon envelope to form a choke point separating an upper portion of the balloon envelope from a lower portion of the balloon envelope. The balloon envelope is structurally secured to a launch platform via a tether that is coupled to the launch collar. The launch collar is configured such that release of the launch collar from the choke point releases the balloon envelope from the launch platform.

Abstract: An operations platform includes a structure configured to house and transport drones and a storage facility configured to store the drones within the structure. The operations platform includes a lift or conveyor configured to move the plurality of drones to/from a launching area. In some implementations, the operations platform may also include at least one robotic element configured to move the drones to and from the storage facility.

Abstract: A low stall or minimum control speed aircraft comprising a fuselage that has vertically flat sides; wings with high a lift airfoil profile of constant chord section set at zero degree planform sweep, twin booms having inner vertically flat surfaces, twin vertical stabilizers, a flying horizontal stabilizer; preferably twin engines having propellers and wherein each engine preferably has a thrust-line that is inclined nose-up to a maximum of +8 degrees, and is parallel to the wing chord underneath wing mounts and landing gear doors that provide surfaces for channeling propeller wash in a rearward direction; all working in concert so that the airplane has an extremely low stall speed and minimum control speed. The engines may be diesel, hydrogen fuel cell, electric fuel cell, diesel-electric, gas turbine or combinations thereof. The propellers may be counter-rotating.

Abstract: A payload coupling apparatus is provided including a housing, wherein the housing is adapted for attachment to a first end of a tether, a slot extending downwardly from an outer surface of the housing towards a center of the housing thereby forming a lower lip on the housing beneath the slot, and wherein the slot is adapted to receive a handle of a payload.

Abstract: A method for providing thermal balance of spacecraft electronics is provided. The spacecraft includes two or more electronic units wherein each electronic unit is capable of performing the same spacecraft operational task. The method for balancing the temperature of spacecraft electronics further includes providing each of the two or more electronic units with a temperature sensor for determining the temperature of that electronics unit. The electronic units and their respective temperature sensors are connected to a controller. In the event that the controller determines that the temperature of an activated first electronics unit has reached or exceeded a predetermined threshold, and the controller has determined that the temperature of a second deactivated electronics unit is below a predetermined threshold, the controller automatically deactivates the first electronics unit and activates the second electronics unit to perform the task previously being performed by the first electronics unit.

Abstract: Assemblies and methods for facilitating the assembly of aircraft wings to a fuselage are disclosed. In some embodiments, a wing unit includes features that are configured to define one of more parts of a pressure vessel that is partially defined by the fuselage portion. In some embodiments, the aircraft assemblies disclosed herein comprise one or more first structural interfaces that permit positional adjustment between the wing unit and the fuselage portion so that one or more second structural interfaces may be finished only after such positional adjustment. In some embodiments, the aircraft assemblies disclosed herein comprise one or more structural interfaces that are disposed outside of the wing unit in order to eliminate or reduce the need for assembly personnel to access the interior of the wing unit to carry out the structural assembly of the wing unit to the fuselage portion.

Abstract: A fixed-wing VTOL hybrid UAV is disclosed comprising: a central frame 104; a pair of quick lockable fixed-wings 102 comprising right wing 102-2 and left wing 102-1 that lock with each other over the central frame; and four electrically operated rotors 108 in downward facing configuration attached to fixed-wings with help of rotor-blade arms 110. Arms 110 are pivotally fixed to wings 102 so that arms 110 are movable between a working position in which arms 110 are oriented parallel to central frame 104, and a storage position in which arms 110 are aligned with wings 102. Central frame 104 is a thin rod and works as fuselage. Drivers and control modules are fitted in wings 102. UAV includes rudders attached to arms at 45 degrees for maneuvering UAV for yaw and a secondary roll response. UAV includes two landing gears 106 attached to each end of central frame.

Abstract: The present invention discloses an integrated airport design. The runways are designed in an elevated curved shape. The middles of landing runways and take-off runways are designed as an overhead parking apron, and the terminal building is below the runways. Therefore, the usable area of the whole airport is increased. The length of each elevated curved runway is lengthened comparing to the traditional straight runway within the same area. In addition, the downhill take-off runway can enhance take-off operation and reduce the fuel consumption. Thus, the existing land resources can be used to the maximum extent.

Abstract: A flight guidance panel for an aircraft includes a subpanel display, a joystick, rotary encoders, a deflection sensor, and a processor. The subpanel display indicates autopilot modes and flight value goals and has a top-level state and a subpanel control state. The joystick is for user interaction with the subpanel display. The rotary encoder is coupled with the joystick to receive rotation inputs from a user of the joystick. The deflection sensor is coupled with the joystick to detect a deflection input from the user of the joystick. The processor is programmed to: change a state of the subpanel display to the subpanel control state corresponding to a selected subpanel in response to receiving the deflection input while the subpanel display is in the top-level state; and change the flight value goals in response to receiving the rotation inputs while the subpanel display is in the subpanel control state.

Abstract: The invention described and claimed in this application is a throttle assembly for a paramotor with an integrated locking mechanism which can be engaged to lock the throttle input in any position to maintain level flight. The throttle locking mechanism can be quickly disengaged as needed by squeezing the throttle control lever. The throttle locking mechanism is also able to be tuned when in the locked position as to attain the ideal engine input for level flight. The throttle locking mechanism can be preset and quickly returned to a designated power setting.

Abstract: An antenna system is configured for use in Low Earth Orbit (LEO) around Earth. The system has a plurality of antenna satellites coupled together to form a phased array. Each of the plurality of antenna satellites have an antenna body with an antenna and a solar cell. A processing device determines an orientation of the plurality of antenna satellites and position the phased array in the orientation based on an analysis of the solar cell of the antenna bodies facing the sun, the antenna of the antenna bodies facing the Earth, and maintaining a torque equilibrium of the phased array.

Abstract: An assembly of a pylon and of a wing of an aircraft, the pylon including a primary structure with a rear face and an upper spar. The assembly includes a rear fastening system including a pair of vertical shackles articulated between the rear face of the primary structure and a first shoe fastened to the wing, wherein the shackles are fastened to the primary structure by a clevis-type connection, and a pair of transverse shackles articulated between the rear face of the primary structure and a second shoe fastened to the wing, wherein the shackles are fastened to the primary structure by a clevis-type connection. With such an assembly, the bulk of the rear fastening system is reduced.

Abstract: A slat track roller assembly is provided so as to mount a slat track operatively associated with a wing leading edge slat for movements between retracted and deployed conditions relative to a leading edge of an aircraft wing. The slat track roller assembly may include at least forward and aft pairs of roller mechanisms connected to a respective one of opposed wing ribs of the wing leading edge in operatively rolling contact with a respective opposed lateral edge of the slat track. At least one of the roller mechanisms is positionally adjustable relative to the respectively opposed lateral edge of the slat track so as to compensate for mechanical tolerances that may be present.

Abstract: Technologies for providing noise shielding are described herein. In some examples, noise shields are installed proximate to one or more of the main engines of the aircraft. The noise shields can be extended during terminal operations and retracted during flight operations.

Abstract: A deployable device includes a tape-spring capable of passing from a wound configuration about a first axis Z to a deployed configuration along a second axis X substantially perpendicular to the first axis Z, the tape-spring having two characteristic dimensions, a first characteristic dimension being the width of the tape-spring along the first axis Z, a second characteristic dimension being the thickness of the tape-spring along a third axis Y substantially perpendicular to the first axis Z and to the second axis X. At least one of the two characteristic dimensions has a non-constant value along the second axis X.

Abstract: A wall covering panel for a nose of an aircraft. The panel comprises a rigid carrying framework preferably having an alveolar structure obtained by 3-D printing, a décor carried by the carrying framework and an acoustically and thermally insulating padding fixed to the carrying framework, and also attachments for fixing the carrying framework to the primary structure of the aircraft. Preferably, the panel also integrates systems, such as electrical route portions or ventilation route portions that traverse the panel from one side to the other or lead to an outlet equipment item also integrated in the panel. Only the carrying structure of the panel, which carries the décor, the insulating padding and any route portions and equipment items, is fixed to the primary structure of the aircraft. The number of attachments is low; the kitting-out and the finishing of the nose of the aircraft are greatly simplified.