Abstract: The support assembly comprises a fixing system which comprises a first connection rod which is connected via a first end to a support component and which is configured to generate a primary force path and a second connection rod which is connected via a first end to the support component and which is configured to generate a secondary force path, the fixing system further comprising a beam which is fixed to a structural component, the second end of the first connection rod and the second end of the second connection rod being connected to the beam, which is arranged so that the directions of the first and second connection rods are oriented in accordance with a plane substantially orthogonal to the plane of the support component.

Abstract: An inlet door for an auxiliary power unit includes a door body with opposed interior and exterior surfaces. The interior surface of the inlet door is curved to diffuse sound waves received by the interior surface.

Abstract: An unmanned aerial vehicle (UAV) is disclosed that includes a retractable payload delivery system. The payload delivery system can lower a payload to the ground using an assembly that secures the payload during descent and releases the payload upon reaching the ground. The assembly can also include a bystander communication module for generating cues for bystander perception. While the assembly securing the payload is being lowered from the UAV, the bystander communication module can generate an avoidance cue indicating that bystanders should avoid interference with the assembly. The assembly also includes sensors that generate data used, at least in part, to determine when the descending assembly is at or near the ground, at which point the assembly releases the payload. The bystander communication module can then cease the avoidance cue and the UAV can retract the assembly.

Abstract: The invention is directed toward a UAV having a plurality of rotors position on axles extending longitudinally from a fuselage. The axles articulate the rotors from a vertical position, where the rotors provide lift, to a horizontal position, where the rotors provide thrust. The UAV is configured such that the voltage provided to each rotor may be varied to adjust rotor speed, and thus thrust, independently, giving the UAV enhanced maneuverability.

Abstract: In one example, a free-flying tethered airship system includes an upper airship adapted to tailor its lift and drag, a lower airship adapted to tailor its lift and drag, and a tether connecting the upper airship to the lower airship such that the upper airship is at least one kilometer above the lower airship. The upper airship is configured to be equiliberally buoyant, while carrying the tether, in a first altitude range. The lower airship is configured to be equiliberally buoyant in a second altitude range, the first altitude range being higher than the second altitude range. A method for stationkeeping of a free-flying tethered airship system is also provided.

Abstract: A VTOL (vertical take-off and landing) aerial flying vehicle comprising an inner frame, a gimbal system and an outer frame, the inner frame comprising a propulsion system and a control system. The propulsion system being able to generate a lift force. The control system being able to control the orientation of the inner frame. The gimbal system connecting the inner frame to the outer frame with at least two rotation axis allowing rotation freedom between the outer frame to rotate independently from the inner frame.

Abstract: A system for electrostatically cleaning surfaces includes an electrostatically chargeable brush, having conductive polymer bristles, moveably disposed adjacent to a solid surface to be cleaned. The system also includes an actuator, configured to linearly move a solid element toward and through sliding contact along the solid surface, the brush being positioned to contact at least one of the solid surface and the solid element prior to the sliding contact, to electrostatically remove dust and the like therefrom.

Abstract: A method of repairing an affected area of a component of a fiber-reinforced polymer composite, especially having elongate or continuous reinforcing fibers in a polymer matrix, is disclosed. The method includes: providing a controlled atmosphere around the affected area of the component; heating the component in the affected area within the controlled atmosphere to cause pyrolysis or depolymerization of the polymer matrix in the affected area and thereby to remove the polymer matrix from the affected area; introducing polymer resin into a space left by the pyrolyzed or depolymerized matrix to refill the affected area.

Abstract: A flat-stock aerial vehicle includes a body having a plurality of flat-stock sheets connected to one another, at least one motor, and at least three aerodynamic propulsors driven by the at least one motor. The aerodynamic propulsors can provide lifting thrust, pitch, yaw, and roll control in both helicopter-like hover flight and airplane-like translational flight.

Abstract: This disclosure describes a configuration of an unmanned aerial vehicle (UAV) landing gear assembly that includes adjustable landing gear extension that may be extended or contracted so that the body of the UAV is contained in a horizontal plane when the UAV is landed, even on sloping surfaces. For example, when a UAV is landing, the slope of the surface may be determined and the landing gear extensions adjusted based on the slope so that the body of the UAV remains approximately horizontal when the UAV lands and is supported by the landing gear extensions.

Abstract: A locking system comprising a handle mounted such that it can rotate about an operating spindle, wherein the handle can move between a locked position and an unlocked position, a hook mounted on the handle and secured in rotation therewith, wherein the hook has a throat in which a latching point of a structure is designed to engage when the handle is in the locked position. The locking system comprises a key associated with the hook and by means of which it is possible to pass from the locked position to the unlocked position of the handle, wherein the key can be removed when the handle is in the locked position and cannot be removed when the handle is in the unlocked position.

Abstract: An airplane, including a wing and a spiroid wing tip coupled to an end of the wing. The wing includes a wing leading edge and a wing trailing edge. The spiroid wing-tip includes an enclosed loop, which includes a beginning section, an ending section, and a middle section. The beginning section includes a leading edge generally continuous with the wing leading edge. The ending section includes a trailing edge swept rearward with respect to the wing trailing edge. The middle section is between the beginning section and the ending section, and includes a portion extending above a chord plane of the wing.

Abstract: A system and method for robust lift generation through flow separation suppression are presented. A fluid flow is ejected over a lifting surface from a fluid ejection orifice, and a flow direction of the fluid flow over the lifting surface is directed using a plurality of vanes configured in the fluid ejection orifice. The flow direction is rotated in a span-wise direction over the lifting surface by swiveling the vanes.

Abstract: Disclosed herein is an improved door system for a satellite deployer for storing, transporting, and deploying space payloads, as well as the method of its use. The satellite deployer's door system as described herein allows for increased efficiency due to the configuration of the mechanical structures used in the satellite deployment process.

Abstract: Current aircraft technology comprises of fixed wing, multi rotor and vectored engine design. The synthesis of fixed wing technology and vectoring engine technology has been implemented but limited to traditional fixed wing design aircraft. The aircraft presented has been designed with an innovation in airframe expectation, improved vectoring engine design system, and landing gear system.

Abstract: An aircraft passenger seat assembly as described herein is formed from two primary and modular components: a structural frame that provides passenger support and dynamic load paths for the seat assembly; and a comfort frame that provides the passenger seating surface and the external upholstery layer for the seat assembly. If the seat assembly is designed for multiple passengers, then a separate comfort frame is used for each passenger seat location. The structural frame can be formed as a molded composite construction, and the comfort frame can also utilize a molded composite support frame. The support frame is used as a mounting shell for a fabric carrier that includes the external upholstery layer. The modular design and use of composite materials results in a significant weight and parts count savings relative to conventional seat designs.

Abstract: Latching or locking deployment hinges are provided that include a latch mechanism, a spring-loaded tensioning device, and a trigger mechanism. The trigger mechanism and the spring-loaded tensioning device are configured to transfer the compressed spring load in the spring-loaded tensioning device to the latch mechanism once the hinge has closed sufficiently far enough to latch together, thus inducing a pre-load through the latch mechanism that eliminates gapping in the hinge interface. The hinges may be sprung or actuated using a powered drive mechanism.

Abstract: The invention relates to a wingtip extension comprising a leading edge and a trailing edge, which wingtip extension is affixable to an outer end of a wing, wherein the leading edge, at least in some sections, is essentially straight, and the straight section of the leading edge comprises a leading-edge sweep angle that exceeds the leading-edge sweep angle of the wing, and the local depth of the wingtip extension gradually decreases between a connecting region for connection to the wing and the outer end of the wingtip extension. By means of a wingtip extension according to the invention, in a delta wing a vortex burst region is positioned just behind the wingtip, as a result of which vortex burst region the cores of wingtip vortices burst and eventually become unstable, so that as a result of this the wake vortices of the aircraft can be reduced. The invention furthermore relates to a wing, comprising wingtip extensions according to the invention, as well as to an aircraft comprising such a wing.

Abstract: Provided is a shell including: a shell body; a steering wing including a drive shaft and that mounted on an external surface of the shell body; an auxiliary wing including a shaft connection portion which is connected to the drive shaft and moving in the lengthwise direction of the drive shaft within the drive shaft to be inserted into and be spread outward from within the steering wing; an auxiliary-wing holding unit including a holding protrusion which is fixedly arranged in a direction of intersecting the shaft connection portion to selectively hold the auxiliary wing in place; and an auxiliary-wing spreading unit installed within the drive shaft, and that provides driving force for spreading the auxiliary wing outward from within the steering wing when the holding protrusion is disengaged with the shaft connection portion.

Abstract: An aerial vehicle system for gathering data may comprise a Waypoint Location, wherein the Waypoint Location comprises an arresting cable; a Ground Control Station, wherein the Ground Control Station comprises a charging cable; and an aerial vehicle, wherein the aerial vehicle comprises an onboard battery, a capturing hook and a sensor payload for generating surveillance data. The aerial vehicle may be configured to autonomously travel between the Waypoint Location and the Ground Control Station. The aerial vehicle may be configured to couple with the arresting cable via the capturing hook. The aerial vehicle may be configured to electronically couple with the charging cable via the capturing hook to facilitate charging the aerial vehicle's onboard battery.