Abstract: A nitrogen gas system for an aircraft is provided and operable in warm-up and normal modes. The system includes an air separation module (ASM), a line to transport nitrogen enriched air (NEA) from the ASM to a fuel distribution system and a diverter valve disposed on the line and configured to divert the NEA away from the fuel distribution system during warm-up operations.

Abstract: The present invention provides methods and apparatus for unmanned aerial vehicles (UAVs) with improved reliability. According to one aspect of the invention, interference experienced by onboard sensors from onboard electrical components is reduced. According to another aspect of the invention, user-configuration or assembly of electrical components is minimized to reduce user errors.

Abstract: A payload cut-down mechanism having a pathway member having a first end and a second end attached to a balloon envelope, a line extending within the pathway member having first and second ends extending from the pathway member, where the first end of the line is releasably secured to a first actuated release mechanism attached to a payload, and a second end of the line releasably secured to a second actuated release mechanism attached to the payload, and wherein at least one of the first and second actuated release mechanisms are operable, upon receiving a signal, to release the first or second end of the line from one of the actuated release mechanisms and cause the payload to separate from the payload.

Abstract: A high-lift device suppresses the occurrence of aerodynamic noise while minimizing an increase in airframe weight. The device includes a slat main body disposed to be able to extend from and retract into a main wing, and a concave part formed on the slat main body at a location facing the main wing and able to accommodate at least a part of a leading edge of the main wing. The device also includes an airflow control part disposed at an area in the concave part facing an upper surface of the main wing, that is accommodated between the main wing and the concave part when the slat main body is retracted into the main wing, and that suppresses turbulence colliding against the area in the concave part facing the upper surface of the main wing when the slat main body is extended from the main wing.

Abstract: A collapsible wing, methods of producing the collapsible wing, and an unmanned aircraft system that includes the collapsible wing are provided.

Abstract: A low-heat-transfer coupling or assembly is configured to mechanically couple together a pair of mating parts, one of which may be in a heat-producing environment. By roughening at least part of the surface of one of the parts, the contact area between the mating parts can be reduced, while still maintaining the structural integrity of the connection. The roughening can be a knurling process of all or part of the mating surface on one of the parts. This can produce a series of recesses on the surface that are in contact with the other part. The recesses can be small enough, interspersed with non-etched areas of the contact surface, that structural integrity of the coupling between the parts is still maintained. The coupling may be between a leading edge of an aircraft control surface, such as a missile fin, and a body of the control surface.

Abstract: Improved supersonic laminar flow wing structure, on a supersonic aircraft, having strake extending forwardly of the wing inboard extent, and reversed fillet at strake junction with the wing leading edge.

Abstract: An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust vectoring module and a second thrust vectoring module, and an electronics module. The electronics module provides commands to the two thrust vectoring modules. The two thrust vectoring modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as thrust vectoring modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds.

Abstract: A method and apparatus for generating avoidance data. Strips are generated for a path of a space object. The strips are positioned relative to the path of the space object. The strips have parameters that obscure an identification of the path of the space object to form the avoidance data.

Abstract: The present invention is realized by apparatus and methods for placing a large utility scale photovoltaic array in the low stratosphere of earth's atmosphere at an altitude of about 20 km, above clouds, moisture, dust, and wind. This is accomplished using a large light-weight, rigid, buoyant structure to support the large photovoltaic array. Long, strong and light tethers connect the buoyant structure to the ground and hold it in position against wind forces. The electricity output from the photovoltaic array is then coupled to high voltage transmission lines which connect from the platform to the earth's surface. The electricity is then transmitted through the high voltage transmission lines to the earth's surface where it is connected to the electrical supply grid and provides lower cost, more reliable electricity.

Abstract: An impact protection apparatus is provided, comprising a gas container configured to hold a compressed gas and an inflatable member configured to be inflated by the gas and function as an airbag of a movable object, such as an aerial vehicle. A valve controls flow of gas from the container to the inflatable member in response to a signal from a valve controller. The valve and valve controller are powered by an independent power source than one or more other systems of the movable object. A safety mechanism may also be provided that, unless deactivated, prevents inflation of the inflatable member.

Abstract: An electric fail-safe is operable to move a first ramp between distinct positions. The first ramp is associated with the second ramp. There are balls intermediate the first and second ramps. When the electric fail-safe brake is in an actuated condition, the second ramp forces stationary brake disks to engage rotating brake disks which rotate with a shaft to cause braking of the shaft. There is a keeper associated with the second ramp which abuts a stop surface to limit the amount of torque applied to the rotary and stationary disks after a predetermined amount of braking force has occurred. A brake with a test switch is also disclosed.

Abstract: Described herein is a vertical take-off and landing aircraft comprising: an upper enclosure comprising a first upper arm and a second upper arm; a lower enclosure comprising a first lower arm and a second lower arm; wherein the first upper arm and the first lower arm comprise a first upper buckle and a first lower buckle, respectively; wherein the second upper arm and the second lower arm comprise a second upper buckle and a second lower buckle, respectively; wherein the first upper buckle engages the first lower buckle and the second upper buckle engages the second lower buckle, thereby securing the upper enclosure to the lower enclosure.

Abstract: A landing gear for an aircraft has a set of axially spaced wheels rotatable about a common axis drive by a transverse flux drive. In another feature, a transverse flux drive includes a first rotor and a second rotor. One of the first and second rotors is positioned radially inwardly of the other. A single stator is positioned radially intermediate the first and second rotors. In another feature, a landing gear combination for use on an aircraft has a nose wheel assembly including at least one nose wheel to be associated with a nose cone on an aircraft. A main landing gear assembly is also associated with the aircraft. A transverse flux motor provides on-ground propulsion and/or braking to the aircraft.

Abstract: The present disclosure relates to a wall component for an aircraft for forming an outer wall comprising at least one first wall element, at least one second wall element and at least one connecting device for connecting the first wall element to the second wall element. On wall regions that are to be directed towards each other, the first and the second wall element comprise connecting regions. Furthermore, a joint element is provided, which comprises a joint region with a joint region surface that is to be arranged towards the outside of the aircraft, wherein the joint region is designed to be received with a matching fit into a recess formed by the connecting regions of the wall elements, and wherein the joint region surface, when the joint element is inserted, is flush with the outer surfaces of the wall elements.

Abstract: An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust-vectoring (“T/V”) module and a second T/V module, and an electronics module. The electronics module provides commands to the two T/V modules. The two T/V modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as T/V modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds.

Abstract: A method of releasing cargo suspended from at least one cargo hook release pendant in a suspension system coupled to a cargo hook release system includes receiving a voltage release signal at a cargo hook control interface and a cargo release harness assembly; receiving an energizing voltage signal at the cargo release harness assembly; energizing a relay in response to receiving the energizing voltage signal, the relay being electrically coupled to the cargo release harness assembly; automatically transmitting the voltage release signal from the cargo release harness assembly to at least one cargo hook release pendant in response to energizing the relay; and automatically releasing the cargo from at least one cargo hook release pendant in response to automatically transmitting the voltage release signal. Also, the cargo hook release system includes the cargo hook control interface, the cargo release harness assembly, and at least one cargo hook release pendant.

Abstract: A battery-structure that may be located at least partially in the wings of an aircraft. The battery-structure forms a portion of the structural support of the wings and includes a plurality of battery receiving compartments; and a plurality of batteries located in the battery-structure. The batteries are configured to fit snugly within the battery receiving compartments, thereby increasing the rigidity of the battery-structure and the wings. The structural constituent of the battery-structure may be made from a carbon or graphite reinforced composite material or from a fiberglass composite material. The battery-structure may include a top panel, a bottom panel, a pair of side panels, and a plurality of web members. The panels and the web members may define the battery receiving compartments. The batteries can be received snugly between the web members to reinforce the rigidity and/or strength of the battery-structure.

Abstract: An aircraft fuselage part (31) located in a section of an aircraft (11) having a propulsion system (13) attached by upstream pylons (17), the fuselage part includes a skin (35); a plurality of frames (37) arranged perpendicularly to a longitudinal axis (33); a single or internally divided upper longitudinal box (41) and a single or internally divided lower longitudinal box (51) which are configured to form with the skin (35) a multi-cell structure, belonging in each cell the external side to the skin (35) and the internal sides to the longitudinal boxes (41, 51); a plurality of lateral beams (61) that are interconnected with the frames (37) to form together with the skin (35) a structural unity. The fuselage components (35, 37, 41, 51, 61) are dimensioned so that the aircraft can withstand the effect of pre-defined failure events keeping a sufficient number of closed cells.

Abstract: A compound rotorcraft including a rotary wing aircraft having a fuselage and at least one rotor and a fixed-wing aircraft coupled to the rotary wing aircraft, wherein the rotary wing aircraft can fly on the rotor or the fixed-wing aircraft, and wherein the fixed-wing aircraft is detachable from the rotary wing aircraft to fly independently.