Abstract: A method of supersonic thrust generation includes generating a thrust supersonic exhaust plume having a first average velocity from an engine, and expelling a bypass exhaust plume having a second average velocity from the engine, the first average velocity greater than the second average velocity, so that the bypass exhaust plume inhibits coalescence of an engine exhaust plume compression shockwave.

Abstract: An emergency collective actuator includes an actuator motor to produce an actuation force and an actuator linkage that directly engages a friction control lever that is pivotally supported on the collective stick of a helicopter to apply the actuation force directly to the friction control lever such that the actuation force initially disengages the friction control and then reduces the adjustable pitch toward a minimum collective pitch position. The actuator can include a clutch that slips to allow the pilot to overcome the actuation force and that slips responsive to an engagement of the friction control by the pilot, but otherwise the clutch co-rotates with the motor shaft to bias the adjustable pitch toward a minimum collective pitch position.

Abstract: A safety system for aircraft passenger seats is described. A pallet that can be removably coupled to seats can also be removably coupled to the aircraft floor and one or more brackets, tension fittings, or machined straps that can be coupled to structural beams or components in an aircraft. A keel tension fitting can be attached to a keel beam and then be coupled to the pallet and thereby the seats. By attaching to the keel beam the safety system allows the seating arrangement (pallet and seats) to withstand greater stresses and forces, resulting in increased safety.

Abstract: A tiltrotor aircraft is described and includes a rotor system, a pylon coupled to the rotor system, a spindle coupled to the pylon, an actuator arm coupled to the spindle, and an actuator. The actuator can cause the actuator arm to rotate, thereby causing the spindle to rotate the pylon and the rotor system. In an example, the actuator is in front of a forward spar of the wing of the tiltrotor aircraft and the actuator arm is about one-half (0.5) of an inch to about five (5) inches from the wing.

Abstract: A device is provided for preventing a parachute from being damaged. A parachute device (4) includes a flying body (43) including a parachute (400), a parachute accommodation section (40) configured to accommodate the parachute, at least one flying body (43) connected to the parachute, an ejection section (41) having a tube shape and configured to hold the flying body and to eject the held flying body, a gas generating device (60) configured to generate gas, and an extrusion member (42) capable of being at least partially inserted into the ejection section, the extrusion member being configured to extrude the flying body from the ejection section due to receiving pressure of the gas generated from the gas generating device.

Abstract: A yaw control system coupled to a tailboom of a helicopter includes tail rotors. The tail rotors include a clockwise tail rotor and a counterclockwise tail rotor. The clockwise tail rotor is configured to rotate in a first rotational direction. The counterclockwise tail rotor is configured to rotate in a second rotational direction, the second rotational direction opposite of the first rotational direction.

Abstract: A rotating detonation combustor includes a nozzle coupled to the combustor body at or near the exhaust opening to choke the exhaust opening. A rotating detonation combustor may include a diverting plate positioned radially inward of the inlet annulus and inlet channels for diverting flow of a mixture in an axial direction. A rotating detonation combustor may include a combustor body including an outer shell at least partially defining a detonation combustion chamber and extending axially from a base toward an exhaust opening of the detonation combustion chamber. The base defines a passageway in fluid communication with the detonation combustion chamber and includes an inlet annulus for axially directing a second fluid into the passageway and a plurality of inlet channels for radially directing a third fluid into at least one of the passageway or the detonation combustion chamber, and the detonation combustion chamber is free of any inner body.

Abstract: A removable closure device for a space inside an aircraft includes: a frame comprising at least one upright said frame comprising at least one fixation interface including a structural element, a curtain assembly comprising a flexible curtain and at least one guiding device or ensuring a translational guiding of the flexible curtain with respect to the upright so that the flexible curtain s able to be moved in a direction of movement parallel to a longitudinal direction of the upright between a stowed position, in which the flexible curtain s released from the space, and a deployed position, in which the flexible curtain closes the space.

Abstract: Tail rotor control system is described for helicopters. A pedal position sensor operable by a pilot yields greater tail rotor RPM relative to the main rotor RPM, giving the pilot increased control over the vehicle. This proves especially useful in certain situations, such as high altitude, where increasing tail rotor speed from main rotor speed can give a pilot increased maneuverability and stability.

Abstract: A shrink mechanism for use with a landing gear of an aircraft. The landing gear includes an outer cylinder rotatably coupled to a frame of an aircraft about a trunnion axis of rotation and a shock strut assembly movably coupled to the outer cylinder so as to reciprocate along a longitudinal axis of the outer cylinder. The shrink mechanism incudes a first shrink link member pivotally coupled to the outer cylinder, a second shrink link member coupling the first shrink link member to the shock strut assembly, a crank member pivotally coupled to the outer cylinder, a drive member coupling the crank member to a walking beam of a landing gear retract mechanism, and a driven member coupling the crank member to the first shrink link member.

Abstract: An aircraft including a rear wing attachment, connecting a primary structure of an aircraft pylon to its wing, and including at least one right-hand link connected to the wing by a first right-hand connecting element and to the primary structure by a second right-hand connecting element and configured to react loads oriented parallel to the vertical direction only, at least one left-hand link connected to the wing by a first left-hand connecting element and to the primary structure by a second left-hand connecting element and configured to react loads oriented parallel to the vertical direction only, a shear pin secured to the primary structure and housed in operation in a housing secured to the wing, the shear pin and the housing being configured to react loads oriented in a plane approximately perpendicular to the vertical direction.

Abstract: Spacecraft servicing devices or pods and related methods may include a body configured to be deployed from a host spacecraft at a location adjacent a target spacecraft and at least one spacecraft servicing component configured to perform at least one servicing operation on the target spacecraft.

Abstract: A rotary wing vehicle includes a body structure having an elongated tubular backbone or core, and a counter-rotating coaxial rotor system having rotors with each rotor having a separate motor to drive the rotors about a common rotor axis of rotation. The rotor system is used to move the rotary wing vehicle in directional flight.

Abstract: A self-healing shield panel for protecting a spacecraft against High Velocity Particles (HVPs). The self-healing shield includes an exterior layer and an interior layer connected to define a cavity which contains a dilatant fluid with a plurality of spheroids. The kinetic energy from HVP impact is dispersed by the plurality of spheroids and absorbed by the dilatant fluid. The plurality of spheroids within the cavity move to block a puncture hole in the shield.

Abstract: An assembly includes at least one first collection of a plurality of spacecraft intended to be fastened to a launcher during a launch phase, wherein the spacecraft are arranged about a central axis (Z) in a given transverse plane perpendicular to the central axis, the spacecraft having edges along a longitudinal axis and being moreover arranged in such a way that a spacecraft is linked to a neighboring spacecraft of the collection by one edge by means of at least one fastener (B) positioned on the edge, so as to mechanically hold the spacecraft to one another, and a satellites-launcher adaptor to which the spacecraft are fastened in a transverse plane.

Abstract: Seeker optics and a related method comprising: an objective for collecting and transmitting light from a target; at least one scattering surface; and a photo detector; wherein: the light transmitted from the objective at small off-boresight target angles propagates to and impinges upon the photo detector without impinging upon the scattering surface; the light transmitted from the objective at large off-boresight target angles propagates to, impinges upon and scatters upon the scattering surface; and the light scattered by the scattering surface propagates to and impinges upon the photo detector; whereby: the target may be detected and tracked at both small and large off-boresight angles, in a wide field of regard.

Abstract: A hybrid VTOL jet car comprising a light weight floatable chassis adapted for carrying a payload, a retractable tail section attached to a light weight floatable chassis at the rear end adapted for stabilizing the hybrid VTOL jet car, a plurality of wheels at the bottom of the hybrid VTOL jet car, a plurality of retractable wings on the sides of light weight floatable chassis, adapted for maneuvering the hybrid VTOL jet car. Further features may include a plurality of thrust-producing engines adapted for generating the thrust required for driving the hybrid VTOL jet car on a surface as well as in the air and a plurality of parachutes attached to the hybrid VTOL jet car to safely land the hybrid VTOL jet car under emergency.

Abstract: A method of delivering heavy payload using an autonomous UAV able to deliver supply by way of airdrop with more precision and at a lower cost. The UAV is equipped with two movable wing systems that rotate from a stowed position to a deployed position upon jettison of the UAV from a mothership. The UAV can be controlled remotely or it can operate autonomously and the movable wings can include ailerons to effectuate flight control of the UAV. The UAV can be reusable or can be an expendable UAV.

Abstract: After deploying its payload, the final stage of a launch vehicle is maneuvered to couple the nosecone of the launch vehicle to the ‘rear’, or ‘engine-end’ of the final stage. The nosecone covers the engine of the final stage, to protect the engine and related components from the heat of re-entry and the impact of landing. Placing the nosecone over the engine and orienting the combination such that the nosecone ‘leads’ the final stage during re-entry, places the center of gravity of the combination ahead of the center of pressure in the direction of travel. Accordingly, the combination is inherently stable as it re-enters the atmosphere and falls to earth. Parachutes and directional devices are used to provide a controlled soft landing.

Abstract: A manned or unmanned aircraft has a main body with a circular shape and a circular outer periphery. One or more rotor blades extend substantially horizontally outward from the main body at or about the circular outer periphery. In addition, one or more counter-rotation blades extend substantially horizontally outward from said main body at or about the circular outer periphery, but vertically offset from the main rotor blades.