Abstract: Gimbal system, including method and apparatus, for mounting a gimbal apparatus to a support platform with a mount assembly. The mount assembly may include first and second bar assemblies that are rotationally coupled to each other by a pair of gears.

Abstract: A flexible tip for integration in a wing trailing edge employs a wing structure rear spar. A flexible upper skin is attached at a forward boundary to the spar and a rigid lower skin is interconnected to the flexible upper skin at a rigid tail piece. At least one actuation link is attached to the rigid tail piece and has a hinge at a forward edge of the rigid lower skin. At least one positioning slider is attached to the hinge which is movable from a neutral position to a first extended position urging the hinge aft for rotation of the rigid lower skin upward and flexing of the flexible upper skin in an upward camber and to a second retracted position urging the hinge forward for rotation of the rigid lower skin downward and flexing of the flexible upper skin in a downward camber.

Abstract: An autonomous system for a satellite which calculates collision paths of debris from anywhere within the spheroid around the satellite by using its radar/ladar data and from data on its own orbit derived by onboard sensors such as star, earth and sun sensors or from stored data sent from its ground control station through the satellite's command subsystem. If a collision would be likely, the system calculates the minimum change in the satellite's orbit to avoid such collision and generates and executes commands for firing on-board orbital control thrusters to put the satellite in a suitable avoidance orbit.

Abstract: A mounting set for use in mounting an external stores to a mounting station of an aerospace vehicle includes a mounting bracket arrangement and a strap arrangement. The bracket arrangement is configured for selective reversible engagement with respect to the mounting station and for cooperating with the strap arrangement. The strap arrangement is configured for securing the bracket arrangement to the stores in load bearing abutment therewith to enable transfer of loads between the stores and the mounting station via said bracket arrangement, in operation of said mounting set. A mounting system is also provided for mounting an external stores to an aerospace vehicle having two or more mounting stations, including a mounting set for each mounting station. Mounting methods are also provided.

Abstract: Under-wing pylon for an aircraft which has on the upper side a pin (2) for attaching to the fuselage or to the wings of the aircraft itself, and a connector (3) for connecting the pylon to the aircraft. The pylon has a monolithic framework made with stratified unidirectional and/or woven carbon fibres, impregnated with epoxy resin.

Abstract: A foreign object damage protection system comprises a sensor for detecting a foreign object, a fluid in a reservoir, a means for dispensing the fluid, the means for dispensing the fluid in communication with the reservoir, and a control unit, whereby when the sensor detects a foreign object, the control unit causes fluid to be dispensed from the reservoir through the means for dispensing and towards the foreign object. The sensor is attachable to one or more locations on an aircraft, such as a wing, nose, windshield, fuselage or tail. The sensor can be a radar sensor, weather radar sensor, weather radar sensor modified to detect objects at short ranges, infra-red sensor, forward-looking infrared sensor, a light detection and ranging sensor, motion sensor, thermal sensor, or video sensor. The system provides a way to protect an aircraft from striking foreign objects, such as birds, in the path of the aircraft.

Abstract: The present invention relates to a spindle drive having a first load path which is formed by the spindle and having a second load path which is formed by a torsion bar which is exposed to torsion, which is arranged in the spindle and is connected to it such that a rotary movement is exerted onto the spindle in at least one state of the threaded drive by the torsion bar, with the spindle drive having a sensor unit which is made such that it detects a relative movement between the spindle and the torsion bar.

Abstract: A lighter than air emergency beacon platform as part of a hydrogen generation and filtration apparatus includes at least one power source having at least one activation switch. At least one reaction chamber is electrically connected to the at least one reaction chamber by at least one low-resistance electrical conductor. The reaction chamber is configured to house a hydrogen generating material. At least one flow disruption chamber is in fluid communication with the reaction chamber. The flow disruption chamber(s) are configured to provide fluid communication with the next flow disruption chamber in the direction of fluid flow. At least one inflatable housing is configured to carry payload and is in fluid communication with the flow disruption chambers. The inflatable housing is detached from a fill tube to lift the payload above terrain blocking line-of-sight signal communication.

Abstract: A flow body is disclosed, particularly for aircraft. The flow body includes an outer side impinged on in a predetermined manner by a fluid in a direction of impinging flow, the flow body having on its outer side at least one flow control device including micro-perforations arranged in at least one segment of the outer side, at least one connecting passage communicated with the micro-perforations via at least one suction chamber so fluid flowing through the micro-perforations flows via the suction chamber into the connecting passage, at least one suction device having a first inlet communicated with the connecting passage, a second inlet communicated with at least one ram fluid feed line, wherein the ram fluid feed line is in a region of the flow body opposite to the direction of impinging flow of the flow body, and an outlet device for discharging the fluid.

Abstract: A method of landing a capsule-spacecraft having a crew compartment containing crew, light cargo, and whatever other elements are associated with crew safety and comfort during emergency recovery, such as survival equipment and a service component including any propulsion components, heat shield, heavier structure, or other equipment not directly connected with the crew component. In the event of a propulsion system failure, the crew compartment component is immediately separated from the service component, either by automatic or crew action. One or more parachutes are then deployed by rapid methods, such as rocket extraction, from the crew compartment. Because the space craft is separated into two parts the weight of the parachutes is reduced in proportion as the weight of the crew compartment is to the total capsule-spacecraft.

Abstract: For emergency piloting of a manual flight control system (7) of an aircraft (1), in the event of flexible connection means (26) breaking, an upstream control device (8) takes authority over the electronic control unit (29) of series actuator (21). An output pivoting quadrant (25) is subjected by a centering rod (22) to a blocking and centering action. In the event of the system breaking, the output pivoting quadrant (25) forms a bearing point for the series actuator (21), so that an emergency control actuate a airfoil surface (11).

Abstract: A compact, purely mechanical wing deployment assisting mechanism uses torsion springs and lever arms to apply a deploying force to a guidance wing during its initial deployment through a wing slot in a rocket or missile, thereby assisting the wing to burst through a cover seal protecting the wing slot. The wings are then fully deployed by centrifugal force. Various embodiments include two “extreme duty” springs and two lever arms per wing, working in parallel. Embodiments provide a total of at least 24 pounds of force per wing at the end of a spring travel of 0.30 inches. In some embodiments, the entire mechanism weighs less than 0.5 pounds and/or occupies less than 2.5 cubic inches per wing. In embodiments, an assembled group, including two springs and two lever arms, is located between each pair of wings, whereby each assembled group applies one lever arm to each adjoining wing.

Abstract: A fastening assembly for the fastening of systems in an aircraft comprising frames, a skin, and clips between the skin and the frames. The fastening assembly includes: ramps, that extend between two consecutive frames of the aircraft; brackets for fastening the ramps to two of the clips situated respectively on two consecutive frames of the aircraft; system supports, fastened to the ramps, each system support being able to receive at least one system.

Abstract: A gun-fired projectile or ballistic missile (1) is equipped with a pair of canards (3) and an array of tail fins (2). Selected tail fins can be retracted or jettisoned following the ballistic phase to vary the geometry of the array from a rotationally symmetrical configuration to an asymmetric configuration for the glide phase, which together with the canards tends to stabilize the projectile in roll. The canards (3) can be independently extended and retracted with respect to the body of the projectile to generate differential lift for banking the projectile to turn. The canards (3) also preferably have a positive dihedral angle with respect to the intended gliding attitude. In an alternative embodiment the canards are replaced by functionally equivalent thrusters.

Abstract: An apparatus and method are provided for reducing the drag caused by a complex-section part in an airflow, for example the landing gear of an aircraft, making it possible to optimize the lift/drag ratio and to reduce the aerodynamic noise by reducing the local noise source. To do so, the complex-section part is masked with a special casing. More specifically, the aero-acoustically optimized complex-section metal mechanical part is fitted with an aerodynamically shaped cover made of several longitudinal parts articulated with hinges to facilitate their installation. This cover is attached to at least two supports placed away from one another along the axis of the part, each support locally mating with the section of the part.

Abstract: There is provided an insulation system and method for a transport vehicle. The system has first and second frame members; a first rigid foam insulation member extending between the first and second frame members; a second rigid foam insulation member, where a first sidewall of the first insulation member integrates with a second sidewall of the second insulation member; and, a third rigid foam insulation member where the second sidewall of the first insulation member integrates with a first sidewall of the third insulation member. Each of the insulation members is surrounded by a protective layer. When the insulation members are integrated, the second and third insulation members impart one or more compression forces on the first insulation member and on the first frame member in order to secure the first insulation member in place without use of any fastener device.

Abstract: A system and method for reducing the noise penalty of a pusher propeller, allowing an aircraft to retain its advantages for UAV configurations, while allowing acoustic performance similar to that of a tractor propeller by reducing, or eliminating, propeller noise emissions. The system and method provide an airfoil-shaped flight surface with (i) a scoop configured to route boundary layer air and associated wake from said flight surface, and (ii) a suction device configured to provide a suction pressure, wherein the scoop routes boundary layer air from the flight surface to the suction device via an opening in the flight surface.

Abstract: A device for assisting the piloting of a rotorcraft, the rotorcraft having a flight control (10) for controlling a rotor (20, 21) via at least one linkage (35. An additional force is generated by at least one piloting assistance means (100) mechanically linked to the linkage (35. The additional force is a function of the position of the flight control (10) and of an instantaneous force as measured on the linkage (35).

Abstract: Aircraft are provided with a pair of auxiliary power units (APUs) adjacently mounted in parallel relative to one another within the tail cone section of the aircraft's fuselage. In some embodiments, the APUs are mounted generally vertically adjacent to one another. Alternatively, the APUs may be mounted generally horizontally adjacent to one another. The aircraft fuselage may include a pair of downwardly and outwardly oriented strakes adjacent the tail cone having lower edges which establish a maximum take-off pitch angle of the fuselage and define a spatial zone therebetween. The APUs are positioned within such a spatial zone defined between the strakes so that the maximum take-off pitch angle is not required to be changed when modifying an existing single APU aircraft with dual APUs.

Abstract: A deployable solar panel assembly including a housing, a solar panel receivable in the housing, and first and second support structures disposed on the housing proximate the lateral edges of the solar panel. The first and second support structures each include an extension member connected to the housing and a pair of tethering members pivotably connected to the housing on opposite sides of the housing. The pair of tethering members are foldable against the housing and, upon deployment, a distal end of each tethering member projects outward from the opposite sides of the housing. The distal end of a deployed solar panel is supported in an extended position by the extension member, and supported against displacement out of the plane of the panel by tethers connected to the distal ends of the pair of tethering members. Spacecraft employing the deployable solar panel assembly and methods of deploying the assembly are also disclosed.