Abstract: Aspects relate to systems and methods for folding wings on an aircraft. An exemplary system includes a blended wing body, where the blended wing body includes a main body and at least a wing, a hinge located on the at least a wing and configured to allow folding of the at least a wing, an actuation system configured to fold the at least a wing, and a controller configured to control the at least an actuation system.

Abstract: Provided is an abnormality detection device for a rotary wing unit. The rotary wing unit includes a plurality of rotary wings that is coaxially disposed. The abnormality detection device includes a controller configured to acquire at least one of a correlation at the time of normal operation between operation parameters related to the rotary wings and a correlation at the time of abnormal operation between the operation parameters and detect abnormality of the rotary wing unit, based on a correlation at the time of actual operation between the operation parameters and at least one of the correlation at the time of normal operation and the correlation at the time of abnormal operation.

Abstract: Aircraft stringers having carbon fiber reinforced plastic (CFRP) material reinforced flanges are disclosed. An example stringer to be coupled to a skin of an aircraft comprises a flange. The flange includes a first portion of a first stiffening segment. The flange further includes a first portion of a second stiffening segment coupled to the first portion of the first stiffening segment. The flange further includes a CFRP reinforcement segment coupled to the first portion of the first stiffening segment and to the first portion of the second stiffening segment. The CFRP reinforcement segment strengthens the first portion of the first stiffening segment and the first portion of the second stiffening segment.

Abstract: A system and method for installing, deploying, and recovering a plurality of spacecraft that provides an ease of use and structural stability, and facilitates a standardization of spacecraft design. In embodiments of this invention, threaded rods are arranged orthogonal to a surface of a baseplate, and each spacecraft includes a coupling mechanism that selectively engages or disengages each threaded rod. Each spacecraft is added to the stack by engaging its coupling mechanism and rotating the threaded rods while the preceding spacecraft on the stack disengage their coupling mechanisms, thereby enabling the spacecraft to travel along the threaded rods toward the baseplate. When all of the spacecraft are added to the stack, the stack is preloaded by rotating the treaded rods into a terminator component at the top of the stack while the coupling mechanisms in all of the spacecraft are disengaged. Spacecraft are deployed by reversing the process.

Abstract: The present disclosure is directed to a blended wing body aircraft including a blended wing body, wherein the blended wing body is characterized by having no clear dividing line between wings and a main body along a leading edge of the aircraft; a cabin located within the main body and a transitional portion of the blended wing body; and a plurality of transparent panels in a ceiling of the cabin configured to transmit light from outside the blended wing body aircraft to inside the cabin.

Abstract: A wing for an aircraft includes a main wing, slat, and connection assembly movably connecting the slat to the main wing, wherein the slat is movable between a retracted position and an extended position. The connection assembly includes a guide rail and an elongate slat track extending along a track longitudinal axis between front and rear ends, the front end of the slat track fixedly mounted to the slat. A first roller unit is mounted to the rear end of the slat track engaging the guide rail. A roller bearing includes a second roller unit mounted to the main wing and engaging an engagement surface of the slat track. The slat track includes a slot extending through the slat track along the track longitudinal axis. The second roller unit includes a first roller element and a second roller element mounted on one common shaft for common rotation, and the common shaft proceeds through the slot.

Abstract: This disclosure describes an aerial vehicle, such as an unmanned aerial vehicle (“UAV”), which includes a plurality of maneuverability propulsion mechanisms that enable the aerial vehicle to move in any of the six degrees of freedom (surge, sway, heave, pitch, yaw, and roll). The aerial vehicle may also include a lifting propulsion mechanism that operates to generate a force sufficient to maintain the aerial vehicle at an altitude.

Abstract: A harmless low-consumption on-orbit continuous launch system includes a satellite platform, a launch apparatus and a plurality of CubeSats. The satellite platform carries the launch apparatus and dozens or hundreds of CubeSats, and is launched from a ground into an orbit for on-orbit operation. The launch apparatus is configured to store the plurality of CubeSats and provide power for on-orbit launching of each of the CubeSats. A solid working medium in the launch apparatus is activated by heating to undergo a phase change, and the activated solid working medium expands instantly and is converted into a high-pressure gaseous working medium. The high-pressure gaseous working medium does work to eject the CubeSats, such that the CubeSats obtain a speed increment. The CubeSats enter a transfer orbit towards different target spacecraft through the speed increment applied by the launch apparatus to perform a plurality of different on-orbit serving missions.

Abstract: An aerial vehicle adapted for vertical takeoff and landing using a set of wing mounted thrust producing elements for takeoff and landing. An aerial vehicle which is adapted to vertical takeoff with the 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 different configurations of its wing mounted rotors and propellers to reduce drag in all flight modes. The aerial vehicle uses deployment mechanisms to deploy rotor assemblies up and away from their stowed configuration locations.

Abstract: A satellite rescue system (SRS) (1) for rescue and recertification of dormant satellites, said SRS having a thruster end (13) with a primary propulsion nozzle (11) and maneuvering thrusters (12) and a satellite connection end (8) with a body (15) between both ends. The satellite connection end of the SRS has an interface ring (14) with clinch clamps (4) that securely attach to a ring (3) on the rescued satellite. An umbilical connector (7) on the satellite connecting end of the SRS provides power and data to the rescued satellite.

Abstract: The present invention relates to a downwash blocking apparatus of air mobility configured such that multi-stage guide shells configured for blocking downwash and guiding the downwash to a discharge portion of a vertiport are mounted to a rotor guide of a flying vehicle for air urban mobility to be movable upwards and downwards, whereby it is possible to prevent the downwash from affecting passengers at the time of boarding and deboarding, and therefore it is possible to solve passenger inconvenience at the time of boarding and deboarding.

Abstract: A personal service unit (PSU) includes a housing, a dial, and a flow control ring. The dial is rotatable about the housing. The housing includes a longitudinal axis therethrough and a first end and a second end opposite the first end. The dial includes a helical first portion along an interior wall of the dial. The flow control ring includes a helical second portion along an exterior wall of the flow control ring. The helical second portion rotatably mates with the helical first portion and rotation of the dial in a first direction moves the flow control ring in a first direction along the longitudinal axis to cause a first adjustment in airflow past the flow control ring and rotation of the flow control ring in an opposite direction moves the flow control ring in an opposite direction to cause a second adjustment in airflow past the flow control ring.

Abstract: A system and method for protecting a rotorcraft from entering a vortex ring state, the method including monitoring a vertical speed of a rotorcraft, comparing the vertical speed to a vertical speed safety threshold, and performing vortex ring state (VRS) avoidance in response to the vertical speed exceeding the vertical speed safety threshold. The performing the VRS avoidance includes determining a power margin available from one or more engines of the rotorcraft, limiting the vertical speed of the rotorcraft in response to the power margin exceeding a threshold, and increasing a forward airspeed of the rotorcraft in response to the power margin not exceeding the threshold.

Abstract: A trolley lift for connecting a lower aircraft deck to an upper aircraft deck. The trolley lift comprises a platform configured to accommodate at least one trolley, wherein the platform delimits a lift compartment at the bottom, and a cover which delimits the lift compartment at the top. In particular, on a side facing away from the lift compartment, the cover at least partly forms a floor of the upper aircraft deck. Furthermore, an aircraft area having a trolley lift and an aircraft having a trolley lift and/or an aircraft area are described.

Abstract: An aircraft tail skid energy absorption indicator including a crushable indicator cartridge disposed within the an outer shock absorber canister of the aircraft tail skid, and an indicator rod coupled to the crushable indicator cartridge so as to move with a portion of the crushable indicator cartridge as a unit, where the indicator rod extends through an aperture in a wall of the outer shock absorber canister, where the indicator rod includes at least one graduation that indicates an amount of remaining energy absorption of the aircraft tail skid energy absorption indicator.

Abstract: A method of providing active flow control for an aircraft includes cooling a liquid coolant in a heat exchanger by circulating a cooling airflow through the heat exchanger, and providing fluid communication between the cooling airflow and a boundary layer flow of at least one flight control surface of the aircraft. The cooling airflow affects the boundary layer flow of the flight control surface(s) to provide active flow control. A method of cooling an engine core of an engine assembly includes circulating a cooling fluid through the engine core, and cooling the cooling fluid with a cooling airflow used to provide active flow control to a flight control surface of the aircraft. An active flow control system for an aircraft is also discussed.

Abstract: An aircraft can include a first wing and a second wing. The first wing can extend laterally from an aircraft body to a first tip, and the second wing can extend laterally from the aircraft body to a second tip. The aircraft can include a first end effector and a second end effector, each including a fore winglet and an aft winglet. The fore and aft winglets of the first end effector can be pivotably connected to the first tip. The fore and aft winglets of the second end effector can be pivotably connected to the second tip. The fore and aft winglets of the first and second end effectors can be independently operable. The first and second end effectors can be independently operable. A processor can be operatively connected to control movement of the fore and aft winglets of the first and second end effectors.

Abstract: In an example, an overhead payload module is described. The overhead payload module comprises a ceiling assembly, an aisle floor assembly, a first payload assembly attached to the ceiling assembly and the aisle floor assembly to form a first side of the overhead payload module, and a second payload assembly attached to the ceiling assembly and the aisle floor assembly to form a second side of the overhead payload module. The first payload assembly comprises a first payload module and a first overhead stowbin module structurally integrated with the first payload module and having a first stowage area configured to receive stowbins. The second payload assembly is positioned opposite the first payload assembly to form an aisle therebetween and comprises a second payload module and a second overhead stowbin module structurally integrated with the second payload module and having a second stowage area configured to receive stowbins.

Abstract: Aircraft propulsion systems and aircraft having such propulsion systems are described. The aircraft propulsion systems include a fan, a motor operably connected to the fan by a drive shaft, and an aircraft power generation system operably coupled to the motor to drive rotation of the fan through the drive shaft, wherein the aircraft power generation system comprises a fuel cell configured to generate at least 1 MW of electrical power.

Abstract: A blended wing body aircraft wherein at least each profile section corresponding to the normalized half-span values from 0 to 0.2 has a thickness ratio having a nominal value within the range set forth in Table 1. Also, a blended wing body aircraft wherein at least each profile section corresponding to the normalized half-span values from 0.15 to 0.3 has a normalized chord having a nominal value within the range set forth in Table 1, and wherein a ratio between a maximum thickness of the center body and the chord length along the centerline has a nominal value of at least 16%. Also, a blended wing body aircraft wherein a region of the aircraft defined by normalized half-span values from 0.1 to 0.2 has a normalized chord having a dimensionless rate of change from ?3.5 to ?5.1, and a thickness ratio having a rate of change from ?0.27 to ?0.72.