Abstract: The disclosed embodiments relate essentially to a primary structure of an aircraft fuselage that has at least a first strut linked at one end to a crossbeam and at the other end to a reinforcing frame. A second strut has one end fastened to the structure below the end of the first strut, and another end linked to the first strut through an intermediate sliding linkage. A deformable member is linked to the struts so that in case of a crash, the compressive forces press against the second strut, so that the end of the second strut slides along the first strut so as to stretch the deformable member longitudinally to absorb the shock.

Abstract: A device for fixing a seat rail, designed to maintain passenger seats on a floor, wherein it includes a connecting bracket, secured to the floor and to the seat rail, the bracket being adapted to support the stresses perpendicular to the plane of the floor, and the stresses parallel to the plane of the floor. The bracket extends obliquely between the floor and the rail seat, a lower end of the bracket being secured to the floor and an upper end of the bracket being secured to the seat rail.

Abstract: A hybrid parachute, method of deploying a parachute and method of landing a payload. The hybrid parachute utilizes a reefing system that provides for the initial deployment of a deceleration stage that is configured to withstand the stresses of high-speed and/or high altitude openings. The deceleration stage has operating characteristics similar to known high-speed parachutes. After sufficient deceleration has been achieved with the deceleration stage, reefings are released deploying one or more low-speed high drag stages of the device. The high drag stage(s) provide the landing characteristics of a low-speed parachute, including the possibility of controlled descent and landing.

Abstract: A hybrid helicopter (1) includes firstly an airframe provided with a fuselage (2) and a lift-producing surface (3), together with stabilizer surfaces (30, 35, 40), and secondly with a drive system including: a mechanical interconnection system (15) between firstly a rotor (10) of radius (R) with collective pitch and cyclic pitch control of the blades (11) of the rotor (10), and secondly at least one propeller (6) with collective pitch control of the blades of the propeller (6); and at least one turbine engine (5) driving the mechanical interconnection system (15). The speed of rotation (?) of the rotor (10) is equal to a first speed of rotation (?1) up to a first flightpath air speed (V1) of the hybrid helicopter (1), and is then reduced progressively in application of a linear relationship as a function of the flightpath air speed of the hybrid helicopter.

Abstract: An aircraft engine thrust reverser cascade assembly includes a plurality of circumferentially spaced cascade segments, each cascade segment including a plurality of spaced vanes including an aft-most vane, and an aft end. The cascade assembly also includes an aft cascade ring removably attached to the aft ends of the cascade segments. The aft cascade ring includes a deflector portion that at least partially extends forward of the aft ends of the cascade segments. The deflector portion is configured to at least partially redirect at least a portion of a volume of air as the air outwardly passes between the aft-most vanes and the aft ends of the cascade segments.

Abstract: A motion generating system for propelling and/or lifting a craft exploiting explosive and implosive processes, whereby a propulsive or lifting force on the craft arises from two sources: generation of a stream of fluids which imparts thrust to the craft; and generation of zones of reduced pressure and density in front of and above the craft allowing the craft to be thrust forward and lifted by ambient pressure on the rear and underside of the craft. Furthermore, reduction of fluid density in front of the craft results in a reduction of frontal drag allowing the attainment of higher speeds. The motion generating system may have other applications; for example, the motion generating system may be used to propel a stream of liquid in the manner of a pump.

Abstract: In conformance with the invention, based on the incident conditions and velocity, the steering of the ailerons is weakly negative (b0) or corresponds either to the maximum sharpness of the aircraft (b1), or the optimal lift of the latter (b2).

Abstract: A balanced thrust vectoring system for an aircraft designed to provide even weight distribution, simple thrust vectoring, and hover stability. The system includes a main diverter that connects to a jet output port. Located inside the diverter is a 4 way splitter that divides the diverter into four equal volumes. Attached to the diverter and adjacent to the two upper volumes are two front upward extending ducts. Attached to the diverter and adjacent to the two lower volumes are two rear upward extending ducts. Each duct includes an upper bend that and diagonally aligned nozzle opening. Each duct has only two bends which help vector the exhaust downward in an efficient manner. The diameter of each duct is consistent to allow their entire length to maximize air flow.

Abstract: An energy management system for lighter-than-air vehicles which includes a reactor means for generating energy, storage means for storing the reactants used in the reactor means, and an integrated pipeless reactant and power distribution means.

Abstract: A wing-to-body fairing for reducing noise due to wing-to-body fairing vibrations in an aircraft, spacecraft, or vehicle may include a honeycomb center having a cavity which is at least partially filled with particle material.

Abstract: A nose cone formed from a shape memory alloy (SMA) having a recoverable strain of at least 2% collapses about the dome for storage, deploys at launch to protect the sensor dome and reduce drag during atmospheric flight and is shed to allow sensing for terminal maneuvers. The SMA is shape-set at elevated temperatures in its Austenite phase with a memorized shape having a radius of curvature greater than that of the sensor dome to reduce aerodynamic drag. The temperature is reduced and the SMA collapsed to conform to the curvature of the sensor dome within the recoverable strain for storage. A first mechanism is configured to return the collapsed SMA to its memorized shape at launch or prior to going supersonic. In one embodiment, the SMA is stored below its Martensite finish temperature in a temperature-induced Martensite phase in which case the mechanism heats the SMA above the Austenite finish temperature to return the material to its memorized shape.

Abstract: A closet comprises a support rail, a light, a raceway, a rub strip, and a hinge unit. The support rail is capable of providing structural support for the closet and having a plurality of connecting elements. The light has a first set of connecting elements capable of being engaged to the plurality of connecting elements. The raceway has a second set of connecting elements capable of being engaged to the plurality of connecting elements. The rub strip has a third set of connecting elements capable of being engaged to the plurality of connecting elements. The hinge unit has a shape capable of being connected to the support rail.

Abstract: A system for use in monitoring, measuring, computing and displaying the rate of compression of aircraft landing gear struts experienced while aircraft are executing either normal or hard landing events. A high speed computer attached to high speed cameras, or range-finders, mounted in relation to each of the landing gear struts are used to monitor, measure and record the landing gear compression rates and aircraft touch-down vertical velocities experienced by landing gear struts, as the aircraft landing gear initially comes into contact with the ground. The system also determines through landing gear strut compression rates if aircraft landing limitations have been exceeded.

Abstract: A paneled partition assembly is designed to close an opening and collapses to uncover the opening by a movement of at least one panel that initiates the rotation and translation of at least one other panel. When the paneled partition assembly is in a closed or extended position, the plurality of panels covers the opening regardless of the opening's shape, size, or irregularity. When the paneled partition assembly is in an open or retracted position, the plurality of panels collapse to a smaller configuration. In moving between the extended and retracted positions, the panels rotate and translate fluidly with minimum user interaction.

Abstract: An airplane door window of a passenger plane, includes an outer pane, an inner pane, an intermediate pane situated parallel between the outer pane and inner pane and designed as an optical lens body for the inspection of impact surfaces for emergency slides, portable staircases or boarding fingers. The outer pane and the inner pane are spaced apart from each other, arranged substantially parallel to each other in a continuous window gasket, and form an intermediate space. The intermediate pane is inserted into a continuous groove of the window gasket, and extends essentially parallel to the outer pane and the inner pane over a partial area of the intermediate space.

Abstract: An actuator load path monitoring system for an aircraft having an aircraft structure, a control surface, and, an actuator connected between the aircraft structure and the control surface to support and position the control surface as desired relative to the aircraft structure. The actuator is of a type including a) an upper actuator assembly securely connected to the aircraft structure, including a motor assembly and gear assembly; b) a ball screw assembly operatively connected to the gear assembly; c) a tie-rod assembly positioned within the ball screw assembly; and, d) a lower actuator assembly securely connected to the control surface, wherein actuation of the ball screw provides selected positioning of the control surface. The actuator load path monitoring system includes an upper load sensing assembly positioned in an upper load path between the upper actuator assembly and the aircraft structure.

Abstract: A system for communicating electrical signals between two spaced apart seat assemblies on a mobile platform, for example an aircraft. The seat assemblies are secured to seat tracks mounted on a floor of the aircraft cabin. The seat tracks have a plurality of spaced apart holes that enable seat assembly mounting. A seat track cover is snap-fit onto one or more seat track mount devices. Each of the seat track mount devices includes one or more cleats or knobs that can be snap fit into the openings in the seat track to quickly and easily secure the seat track cover to the seat track. The seat track cover and mount devices enable a simple, planar seat track having spaced apart holes to be employed, rather than a C-shaped seat mounting track.

Abstract: The invention reduces the impact of flowfield forces on objects launched from high speed aircraft during flight. For example, the invention provides a solution for overcoming ejection windblast injuries to pilots and increases the probability of injury-free or low-injury ejection. The gas flow is used to rapidly create a very short duration protective “bubble” in the incoming air flow ahead of the ejecting pilot. The bubble reduces the local flow velocity and aerodynamic forces on the pilot during the injury-critical time period of ejection. The invention also is suitable for reducing the intensity of flowfield forces that act on released military aircraft ordnance, such as bombs and missiles.

Abstract: An airship comprises a shell, a gas storage system, an air storage system, a cargo storage system, a heating system, and a propulsion system. The shell encompasses a volume. The gas storage system is located within the volume, wherein the gas storage system is capable of storing a lighter than air gas. The air storage system is located within the volume, wherein the air storage system is capable of storing heated air. The heating system is capable of heating air. The propulsion system is capable of propelling the shell during flight.

Abstract: A wheel assembly (10) is disclosed, including a wheel base (14) and a wheel rim member (16). The wheel base (14) has along at least a portion of its length a non-circular cross sectional outer surface (86). The wheel rim member (16) has along at least a portion of its length a mating non-circular cross sectional inner surface (88). The inner surface (88) of the wheel rim member (16) interacts with the outer surface (86) of the wheel base (14) to restrict relative rotation of the wheel rim member (16) on the wheel base (14).