Abstract: Described herein is a blended wing body aircraft. In some embodiments, a blended wing body aircraft may include a set of passenger loading doors on a first lateral side of the aircraft, and a set of passenger unloading doors on the second lateral side of the aircraft. In some embodiments, this configuration may allow for more efficient loading and unloading of blended wing body aircraft.

Abstract: A compact aircraft control surface track mechanism is disclosed. A disclosed example aerodynamic body includes a support structure, a control surface movable relative to the support structure, the control surface including at least two rollers spaced apart along at least a spanwise direction of the aerodynamic body, and at least two tracks associated with the support structure, wherein a first track is to guide a first roller along a first movement pathway, and wherein a second track is to guide a second roller along a second movement pathway shaped differently than the first movement pathway.

Abstract: A method and a device for assisting the piloting of a propeller rotorcraft having a rotary wing and at least one propeller. The piloting assistance device comprises a computer configured to display the following on a display: (i) a first scale representing a power consumed by the at least one propeller and carrying a minimum power mark and a maximum power mark, (ii) a second scale graduated in forward speed of the propeller rotorcraft, (iii) an index comprising a power section representing a current power consumed by the at least one propeller, the index comprising a speed section indicating a current forward speed on the second scale.

Abstract: A self-leveling recovery platform for a landing operation of an unmanned aerial vehicle and a method for an unmanned aerial vehicle on a self-leveling recovery platform are described. The platform includes landing includes a base, a landing pad, first to sixth motors, first to sixth arms, an accelerometer, a gyroscope/inertial measurement unit, and a controller. The base is for fixedly mounting to a moving body. The landing pad has a landing surface on which an aerial vehicle can land. The first to sixth motors are attached to the base. The first to sixth arms control the first to sixth motors to the platform. The accelerometer and gyroscope/inertial measurement unit sense motion of the platform and output sensing signals. The controller is responsive to the sensing signals to control each of the motors to adjust the arms such that the landing surface is maintained in a substantially stable plane relative to a predetermined surface.

Abstract: Systems and methods are configured for power distribution in a hybrid fixed-wing VTOL drone aircraft. A drone aircraft includes two modes of operation. In a first mode of operation, the internal combustion engine is shut off while an electric motor-based VTOL system provides lift and thrust. In a second mode of operation, an internal combustion engine provides thrust while a set of fixed wings provide lift. In the second mode of operation, mechanical power from the internal combustion engine provides for power generation to charge an electrical battery to power the electric motor-based VTOL system.

Abstract: Series hybrid propulsion unit including a gas turbine driving a mechanical shaft of an electric generator having n output phases and supplying an AC busbar, and a system for monitoring the speed of the gas turbine, the AC busbar supplying a plurality of AC distribution channels each composed of an electric rectifier and a battery sharing the power required to supply a DC bus, the DC bus in turn supplying a plurality of propulsion sub-channels composed of electric inverters supplying, under the monitoring of a control module, motors driving thrusters, further including a battery charger for charging the battery from the DC bus, a power management module delivering a power reference for the electric generator, and a hybridization rate management module monitoring the voltage of the DC bus, the battery being directly connected on the DC bus via a passive component and the electric rectifier being a passive converter.

Abstract: A gimbal sleeve for connecting to a camera gimbal may float between a floor surface and a ceiling surface of an aerial vehicle chassis such that the gimbal sleeve has freedom of motion in yaw, pitch, and roll directions relative to the vehicle chassis. The gimbal sleeve may comprise a pair of connection points to the lower dampers on a floor surface of the vehicle chassis. The gimbal sleeve may furthermore comprise a ball joint coupled to a back surface of the vehicle chassis. The connection points include spring forces that enable the gimbal sleeve to return to an equilibrium position in response to external vibrations and reduce the magnitude of vibrations transferred from the aerial vehicle to the gimbal and camera systems.

Abstract: The disclosure describes an automated aerial vehicle (AAV) and system for automatically detecting a contact or an imminent contact between a propeller of the AAV and an object (e.g., human, pet, or other animal). When a contact or an imminent contact is detected, a safety profile may be executed to reduce or avoid any potential harm to the object and/or the AAV. For example, if a contact with a propeller of the AAV by an object is detected, the rotation of the propeller may be stopped to avoid harming the object. Likewise, an object detection component may be used to detect an object that is nearing a propeller, stop the rotation of the propeller, and/or navigate the AAV away from the detected object.

Abstract: An electric propulsion architecture for a multi-rotor vertical take-off and landing aircraft includes four electric generators; and four pairs of rotors. For each rotor, a first electric motor is configured to operate in an active mode, and a second electric motor is configured to be in a standby mode and being able to operate in an active mode in a breakdown situation. A propeller is coupled to the electric motors, wherein, for each pair of rotors, one of the electric generators powers the first electric motors, and another of the electric generators powers the second electric motors. The rotors form counter-rotors and for each counter-rotor, the electric motors are each powered by one of the four electric generators so that the four electric generators power the electric motors of the rotors of each counter-rotor.

Abstract: A passenger vertical take-off and landing aircraft includes a flying wing comprising a passenger compartment, a first set of rotors positioned at least partially forward of a leading edge of the flying wing, and a second set of rotors positioned at least partially rearward of a trailing edge of the flying wing. The first set of rotors may include at least four rotors and the second set of rotors may comprise at least two rotors. The first set of rotors, the second set of rotors, both, or neither may be tiltable between lift configurations for providing lift for vertical take-off and landing of the aircraft and propulsion configurations for providing forward thrust to the aircraft.

Abstract: A satellite constellation forming system forms a satellite constellation (20) having a plurality of orbital planes (21) in each of which a plurality of satellites fly at the same orbital altitude. A satellite constellation forming unit forms the satellite constellation (20) in which orbital altitudes of the orbital planes (21) are mutually different. Furthermore, in the satellite constellation (20), relative altitude differences between adjacent orbital planes in the plurality of orbital planes are sequentially arranged to be sinusoidal. The satellite constellation forming unit sequentially changes an orbital altitude (23) of each orbital plane of the plurality of orbital planes while maintaining a sinusoidal arrangement of the relative altitude differences between adjacent orbital planes in the plurality of orbital planes.

Abstract: A leading-edge component for an aircraft includes at least a part of a flow body having a front skin and a rib. The front skin comprises a top section, a bottom section and a leading edge arranged therebetween. The rib extends from the bottom section to the top section. The rib comprises a flange that at least partially surrounds the rib. The flange is attached to an inner side of the front skin. The at least one peripheral surface extends from the contact surface inwardly into the flow body and away from the inner side of the front skin or encloses a weakened connection region with the contact surface for bending inwardly into the flow body upon an impact onto the front skin on or adjacent to the at least one peripheral surface.

Abstract: A load carrying assembly for carrying a load with a rotary wing aircraft. The load carrying assembly includes a cargo cable and a load engaging system. The cargo cable may have a first end that is attachable to a hoist or a cargo hook arrangement. The load engaging system may include a first attachment that is attached to the second end of the cargo cable, a second attachment that is adapted for receiving a load, a connecting apparatus that connects the first attachment with the second attachment, and at least two first and second thrust producing devices that are attached to the connecting apparatus and produce thrust in a direction that is orthogonal to the cargo cable extension.

Abstract: An airframe-mounted package launching system including a package launching device mounted in an interior portion of an airframe structure proximate an external airframe opening, the package launching device including a launch bed configured to support a package during a launching process, and a launch assembly configured to impart a launching force to the supported package on the launch bed during the launching process.

Abstract: A rotor for a hover-capable aircraft includes an attenuating device to attenuate the transmission of vibrations from a mast to the aircraft. The attenuating device includes a first mass free to oscillate parallel to a hub rotation axis with respect to a casing of the attenuating device and elastically connected to the casing. The attenuating device further includes a second mass free to oscillate parallel to the hub rotation axis, connection means adapted to make the first and second masses integrally movable along the hub rotation axis when the angular speed of the mast assumes a first value, and actuator means activatable to decouple the first and second masses when the angular speed of the mast assumes a second value, different from the first value.

Abstract: The present invention relates to a multi-modal vehicle operable in a first mode as a fixed wing aircraft and reconfigurable to be operable in a second mode as a ground vehicle. The vehicle comprises first and second ends configured to operate in a first direction, with the first end leading the second end, in the first mode and in a second direction, with the second end leading the first end, in normal operation in the second mode.

Abstract: The invention discloses an aircraft generating a larger thrust and lift by fluid continuity. First open channels used to extend fluid paths are formed in front parts and/or middle parts of windward sides of wings of the aircraft and extend from sides, close to the fuselage, of the wings to sides, away from the fuselage, of the wings, and the first open channels are concave channels or convex channels, so that a pressure difference in a direction identical with a moving direction is generated from back to front due to different flow speeds of fluid flowing over the windward sides of the wings in a lengthwise direction and a widthwise direction to reduce fluid resistance, and a larger pressure difference and lift are generated due to different flow speeds on the windward sides and leeward sides of the wings.

Abstract: A wheel speed measuring device for an aircraft braking system uses dual technology packaged in a single transducer that incorporates the robust and reliable variable reluctance technology along with a secondary package for measuring position and velocity bi-directionally for low speed and taxi operations. The transducer of the present invention is preferably incorporated into the envelope of the axle to allow both retrofit on existing aircraft and to maintain existing axle design and configuration.

Abstract: A system for providing spacecraft-based services, preferably including one or more spacecraft and one or more ground control elements, wherein the spacecraft can include one or more payloads associated with one or more organizations. A method for providing spacecraft-based services, preferably including receiving service requests, determining request assignments, and/or controlling spacecraft.

Abstract: A leading-edge arrangement for an aircraft is proposed, comprising a plurality of movable flow bodies, a supply duct, an air transfer duct, and at least one perforated tube. The movable flow bodies are arranged in a consecutive arrangement to form a row with a first end and a second end. The supply duct reaches into an interior of one of the flow bodies at the first end. The air transfer duct connects to the supply duct and extends at least through the interior of the respective flow body in the direction towards the second end. The at least one perforated tube is arranged inside at least one of the flow bodies that directly follows on. The at least one perforated tube is in fluid communication with the transfer duct. The transfer duct is configured to transfer air from the supply duct into the at least one perforated tube.