Abstract: A quick disconnect apparatus including a first end configured to interface with a legacy fill and drain valve (FDV) of a satellite to be serviced, a second end configured to interface with a refueling tool, and a middle portion including at least one redundant seal to prevent unwanted fuel transfer during connection of the FDV and refueling tool.

Abstract: A propulsion system for an aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a forward flight orientation. The propulsion system includes an turboshaft engine, a lift fan system, a forced air bypass system and an exhaust system. The engine has a turboshaft mode and a turbofan mode. The lift fan system includes at least one ducted fan. In the VTOL orientation of the aircraft, the engine is in the turboshaft mode coupled to the lift fan system such that the engine provides rotational energy to the at least one ducted fan generating the thrust-borne lift. In the forward flight orientation of the aircraft, the engine is in the turbofan mode coupled to the forced air bypass system such that the bypass air combines with the engine exhaust in the exhaust system to provide forward thrust generating the wing-borne lift.

Abstract: A flap system driving a leading-edge flap between retracted and extended positions comprises a leading-edge flap having first and second flap joints, first and second scissor links, a first connecting link, and an actuator. The actuator couples with either the first scissor link or first connecting link. The first scissor link is rotatable supported on a first fixed point by a first support joint. An end of the first scissor link opposite the first support joint couples with the first flap joint. The first connecting link is rotatably supported on a second fixed point by a second support joint. An end of the first connecting link opposite the second support joint rotatably couples with an end of the second scissor link. An opposite end of the second scissor link couples with the second flap joint. The first and second scissor links are rotatably coupled to form a scissor arrangement.

Abstract: A rotation-stabilized beamed-energy receiver, and associated systems and methods, including an aircraft carrying a rotating electromagnetic energy receiver that, when rotated, is supported by centripetal force in a selected shape and/or orientation. Accordingly, the receiver can be made from very thin and/or otherwise lightweight/flexible materials, while performing an energy-receiving function.

Abstract: An aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a forward flight orientation. The aircraft has a blended wing body and includes an engine, a binary lift fan system, a forced air bypass system and an exhaust system. The engine has a turboshaft mode and a turbofan mode. The lift fan system includes a plurality of ducted fans in a tandem lateral orientation. In the VTOL orientation of the aircraft, the engine is in the turboshaft mode coupled to the lift fan system such that the engine provides rotational energy to the ducted fans generating the thrust-borne lift. In the forward flight orientation of the aircraft, the engine is in the turbofan mode coupled to the forced air bypass system such that the bypass air combines with the engine exhaust in the exhaust system to provide forward thrust generating the wing-borne lift.

Abstract: A system for landing and locomoting on a surface of a structure comprises an unmanned aerial vehicle having a plurality of independently controllable thrusters and an undercarriage including a frame with wheels at corners. The undercarriage further includes a plurality of bars pivotally coupled at respective first ends to the frame and coupled at respective second ends to the unmanned aerial vehicle; wherein the unmanned aerial vehicle is operative to differentially activate the plurality of thrusters so as to tilt with respect to the frame of the undercarriage and to cause a net resultant force on the undercarriage to locomote on the surface of the structure.

Abstract: This solar panel includes a structure in contact with an ambient environment and at least two photovoltaic cells each defining a lateral contact face and including a base element, a grid of electric conductors and a protective element made from transparent material, the grid including at least one conductive wire extending along the lateral contact face. The two cells are arranged on the structure such that at least part of each of the lateral contact faces is arranged regarding the other part while forming a panel surface and such that the shortest path passing through the ambient environment between the opposite parts of the lateral faces of the two cells is equal to at least about 20 mm.

Abstract: An intelligent restraint system architecture for aircraft cargo is provided. The intelligent restraint system architecture includes restraints arrayed along a cargo deck and local restraint control panels (RCPs). Each restraint is configured to normally assume a retracted condition at which cargo movement proximate to the restraint is permitted and to selectively assume an erected condition at which cargo movement proximate to the restraint is inhibited by the restraint. The local RCPs are respectively coupled to proximal restraints. Each local RCP is receptive of a signal indicative of a cargo movement status and is configured to automatically control each of the proximal restraints to selectively assume the erected condition or to re-assume the retracted condition in accordance with the signal being received and content thereof.

Abstract: An aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a forward flight orientation. The aircraft has a blended wing body and includes an engine, a unitary lift fan system, a forced air bypass system and an exhaust system. The engine has a turboshaft mode and a turbofan mode. The lift fan system includes a ducted fan. In the VTOL orientation of the aircraft, the engine is in the turboshaft mode coupled to the lift fan system such that the engine provides rotational energy to the ducted fan generating the thrust-borne lift. In the forward flight orientation of the aircraft, the engine is in the turbofan mode coupled to the forced air bypass system such that the bypass air combines with the engine exhaust in the exhaust system to provide forward thrust generating the wing-borne lift.

Abstract: An unmanned aerial vehicle includes a housing assembly having a receiving space, a power assembly received in the receiving space, and a controlling assembly received in the receiving space and configured to control the power assembly. The housing assembly is provided with a flow passage penetrating an inside of the housing assembly, and the power assembly partially forms the flow passage. In the UAV, since the power assembly is mounted in the housing assembly, the propeller of the power assembly will not hurt person during the flight, thereby improving the safety performance while flying near the ground.

Abstract: A lighter-than-air airship has an exoskeleton constructed of spokes and hubs to create a set of connected hexagrams comprised of isosceles triangles wherein the spokes flex and vary in length to produce the slope of said airship's surface. In one embodiment, the exoskeleton connects to a nose cone that includes a cockpit cabin for controlling the airship's operation from a single location that can be physically separated from the exoskeleton in response to catastrophic events and for autonomous and/or remotely piloted operation. An improved means is also provided for landing and unloading cargo, and through use of unmanned aerial vehicles in another embodiment, the airship is configured for remote pickup, transport, delivery and return of payloads such as packages. In yet another embodiment, the airship provides a communications platform for beam form transmission and satellite signal relay, including in combination with the foregoing disclosed attributes.

Abstract: A cinched parachute is disclosed. In various embodiments, a cinched parachute as disclosed herein includes a canopy comprising one or more sections of canopy material, and a device integrated with the canopy that controls dimensions of the canopy material. For example, in some embodiments the device may be used to control the size of an opening atop the parachute.

Abstract: A window assembly for use in a vehicle including a window frame including a first end and a second end opposite the first end, and an opaque shade movable relative to the window frame, wherein the opaque shade includes a first tab formed at a bottom end of the opaque shade. A transparent shade is movable relative to the window frame, wherein the transparent shade includes a second tab formed at a bottom end of the transparent shade. The first tab and the second tab are configured for selective integration with each other to enable dependent movement of the opaque shade and the transparent shade with each other, and to enable independent movement of the opaque shade and the transparent shade relative to each other.

Abstract: An aircraft landing gear 2 is disclosed having a first arm 6a configured to have one or more wheels 8a mounted at one end, the first arm 6a being configured for mounting to a pivot 10a. The landing gear 2 includes a second arm 6b configured to have one or more wheels 8b mounted at one end, the second arm 6b being configured for mounting to a pivot 10b. The landing gear 2 further includes a first link 18a pivotally coupled to the first arm 6a, a second link 18b pivotally coupled to the second arm 6b; and a main link 20 pivotally coupled to each of the first and second links 18a, 18b and to a shock absorber 22 arranged to provide a biasing force via (i) the main linkage 20 and the first link 18a which opposes rotation of the first arm 6a about the pivot 10a and (ii) the main linkage 20 and the second link 18b which opposes rotation of the second arm 6b about the pivot 10b.

Abstract: A movable flight control surface for aircraft, the movable surface comprising: a skin mounted to pivot on a hinge shaft having at least one end that projects from the skin; at least one electric motor that is mounted inside the skin and that has an outlet shaft coupled to the hinge shaft so as to cause the skin to pivot on the shaft; and a power circuit and a control circuit for powering and controlling the motor, the circuits being housed inside the skin and being connected to connectors leading to the outside of the skin.

Abstract: A torque box rib includes an upper rib cap configured to be coupled to an upper skin of a wing, a lower rib cap configured to be coupled to a lower skin of the wing, a forward post configured to be coupled to a forward spar of the wing, an aft post configured to be coupled to an aft spar of the wing, and a rib web configured to be coupled to the upper rib cap, the lower rib cap, the forward post, and the aft post.

Abstract: A trap system is presented for deployment of a reserve parachute. The trap system includes a trap line with a first end coupled to a main parachute and a trap attached to a surface of the container. The trap includes an outer perimeter to removably hold the trap line and an interior to removably hold the reserve bridle. A kit is also presented for converting a parachute container into an improved parachute container to deploy a reserve parachute. The kit includes an attachment to be secured to a surface of the parachute container. The attachment includes a trap line with a first end configured to be coupled to the first end of the RSL lanyard, and a trap secured to a region of the attachment, with an outer perimeter to removably hold a second end of the trap line and an interior to removably hold the reserve bridle.

Abstract: The present disclosure relates to the aerospace application field, and provides a method for flying a large balloon. In the method, a constraint apparatus is disposed on a balloon capsule to replace a roller, and the constraint apparatus is released progressively in a release process of the balloon capsule, so that the balloon capsule is released progressively and slowly before rising above a pod. This greatly reduces the impact in a flying process, makes it easier to control a flying status of the balloon capsule, and also makes related operations of onsite staffs simpler and controllable.

Abstract: An exemplary spring-loaded link for an aircraft including a spring interposed between a first and a second rod, the spring, when compressed, urging the first rod and the second rod away from each other.

Abstract: A lifting device including: a movable discontinuity (1) located in a surface of the lifting device, the movable discontinuity (1) being movable between: an active position in which the movable discontinuity (1) acts as vortex generator, and a passive position in which the movable discontinuity (1) is integrated into the surface of the lifting surface, a conduit (2) located in the spanwise direction of the lifting surface and in communication with the movable discontinuity (1), the lifting surface including openings (3) in its surface spanwise distant from each other in communication with the conduit (2), the movable discontinuity (1) and the conduit (2) being configured such that when an airflow goes through the conduit (2), this airflow activates the movable discontinuity (1) to act as a vortex generator of the lifting surface.