Abstract: A covering element for the interior the interior of a vehicle, particularly an aircraft, is provided with at least a first and a second covering portion each of which comprises a covering wall with a front side pointing to the interior of the vehicle in the installed state and a rear side Each covering portion also includes a width extension and a longitudinal extension directed transverse thereto to one another. The covering walls of the two covering portions overlap each other, and the second covering portion is supported so as to be displaced substantially in the direction of its longitudinal extension and/or to be pivoted about a pivot axis extending substantially perpendicular to its longitudinal and width extension-on the first covering portion.

Abstract: The electric pyrotechnic igniter of the present invention comprises a controlled power source providing low-voltage electricity to one or more remotely located, replaceable ignition elements which are housed in compression clips capable of holding the ignition elements into direct contact with firework fuses.

Abstract: The cockpit door has a hinge on one side and a latch device on the other side that can be operated only from the cockpit side. To the inner side of the door panel is mounted a reinforcement member 100 having a body formed by laminating layers of aromatic polyamide fiber sheets and thermoplastic adhesive and subjecting the same to hot pressing to form an integral member. Mounting portions 150 and 160 are formed to the rim portion of the reinforcement member body 110, and rivet inserting holes 180 are machined to the portions. The mounting portions are bent by 90 degrees, and fixed to a frame using rivets.

Abstract: The center of pressure of a projectile is caused to move upon the occurrence of an event that changes the static margin, such as the jettisoning of a body previously attached to the projectile, as noted above. In particular embodiments, this is achieved by a flare disposed toward the rear of the projectile. The flare has petals that deploy from a first, stowed position to a second, deployed position upon the occurrence of the event. In the stowed position, the petals are aligned with the air stream, in order to minimize drag. In the deployed position, the petals project into the air stream in such a way as to move the lift center rearward. A slide ring within the flare has sufficient inertia that it shifts aft in response to an acceleration that occurs when the attached body and the projectile are separated from one another. The slide ring is linked to the petals in such a way that the petals are deployed by the displacement of the slide ring.

Abstract: An apparatus comprising: an aerodynamic surface adapted for producing an adverse pressure gradient in a fluid flow; and a first pulse detonation actuator disposed adjacent the aerodynamic surface and adapted for impulsively detonating a fuel/air mixture to produce a pressure rise and velocity increase of combustion products therein, the aerodynamic surface having a plurality of separation control holes adapted for communicating combustion product flows from the first pulse detonation actuator to the aerodynamic surface for modulating separation of the fluid flow from the aerodynamic surface.

Abstract: A safety device for preventing unauthorized or accidental use of a gun. The safety device includes a solid body of material, a muzzle end plug and an elongate threaded rod inter-connecting the same. The solid body is sized and shaped to simulate a live cartridge. It has an outwardly directed flange at one end for engaging an end wall surrounding entry into the cartridge chamber of the gun and a threaded bore extending inwardly a selected distance from the opposite end. An O-ring fits into a groove it the solid body and projects outwardly frictionally to engage the inner wall surface-of the gun barrel in the cartridge chamber. The muzzle plug has an outwardly directed flange at one end thereof that engages an outer end of the gun barrel.

Abstract: A fluid conduit is provided for use in a hydraulic actuating system for controlling an instrumentality disposed on a rotating portion of a machine. The fluid conduit transports pressurized fluid between a fluid source disposed on a non-rotating portion of the machine and the instrumentality and comprises a rigid tubular member formed in the shape of a helix having at least about 2 revolutions and a non-constant pitch length. The ends of the tube are adapted to be sealingly connected between the fluid source and the instrumentality. The fluid conduit is used, for example, in an apparatus and system for controlling a hydraulic actuator mounted on a rotating blade.

Abstract: The two-payload decoy device has a square outer case, containing a manifold/delay body assembly, a round payload assembly, and a square payload assembly. The square outer case is closed with an end cap. The manifold/delay body assembly is attached to the round payload assembly, which rests against the square payload assembly. Firing a standard impulse cartridge ignites a booster pellet and delay element in the manifold/delay body assembly. Gases flow through openings in the manifold/delay body assembly and down the corner cavities between the round payload assembly and the square case, pushing the square piston against the square payload, which separates the end cap from the case and ejects the square payload. The delay element burns for a specific time, and then ignites a round payload expulsion charge, which creates gases that push the round piston against the round payload, which dislodges a retaining ring, and ejects the round payload.

Abstract: A dual stage invention is designed to autoignite an autoignition material before a low temperature gas generant melts. Low temperature gas generants include a high nitrogen content organic fuel with ammonium nitrate as the oxidizer. The dual stage inflator has a first gas generant and a second gas generant that are ignited by separate igniters. The first gas generant and the second gas generant are insulated from the inflator housing to delay the heat transfer from the housing to the first gas generant and second gas generant during a bonfire test, which needs to be passed to receive Department of Transportation classification. The dual stage inflator also has an autoignition cartridge for disposing of the second gas generant by the first gas generant after the first gas generant burns for a predetermined amount of time.

Abstract: A rotor system that allows an aircraft to operate as a helicopter and as an airplane is disclosed. The invention incorporates an annular airfoil attached at the tips of the rotor blades. The rotor system stops and is secured from rotation for operation at high forward speeds. The annulus acts as the primary lifting surface in airplane mode at high speed. The rotor blades incorporate leading and trailing edge flaps for control in transitional and fixed wing flight modes.

Abstract: A method of removing a canopy from a cockpit of an aircraft comprising providing an airbag in the cockpit adjacent the canopy; inflating the airbag; and as the airbag inflates, applying a force to the canopy from the inflating airbag to thereby jettison the canopy.

Abstract: An explosion simulator including a chamber at least partially filled with a pyrotechnic material, the chamber being formed with a plurality of holes arranged for fluid products of an explosion of the pyrotechnic material to pass therethrough, and a delaying detonator adapted to detonate the pyrotechnic material, the detonator being adapted to delay onset of the explosion of the pyrotechnic material a period of time after actuation of the detonator.

Abstract: The disclosure relates to a supply vessel for transporting a plurality of payload carrying containers having powered self-burying mechanism to enable the containers to bury themselves in the seabed when released from the vessel. Each container is connected to the vessel by an umbilical including a power supply from the vessel to the container for powering the self-burying mechanism.

Abstract: An energy-absorbing connecting strut comprises a substantially straight rigid body with means of connection to two components which it links, and undergoing tensile/compressive stresses. The body comprising a buckling portion with a calibrated buckling load corresponding to a compressive load threshold, a hollowed portion housing a component absorbing energy by plastic deformation in compression, and a piston moving integrally with a rigid axial end part of the body. The body is configured so that under a compressive load greater than the compressive load threshold, the buckling portion deforms causing axial shortening of the connecting strut and movement of the piston with the rigid part, so that the piston crushes and plastically deforms the energy-absorbing component, limiting the load amplitude. The energy-absorbing strut may be used as a suspension strut of a main gearbox on the structure of a rotary wing aircraft.

Abstract: An ammunition article includes a molded plastic cartridge casing body having a first end and a second end, and a projectile attached to the first end of the cartridge casing body. The cartridge casing body is molded around at least a portion of the projectile. A molded plastic base for an ammunition article, a molded plastic blank cartridge, and a molded plastic cartridge casing body having a pronged web are also disclosed.

Abstract: A detonator assembly for use with explosive devices includes a support structure, an exploding foil initiator mounted on the support structure, and a barrel attached to the support structure and adjacent the exploding foil initiator. The support structure may include a flex cable. An explosive is placed in the proximity of the exploding foil initiator.

Abstract: A cartridge feed tray for belt ammunition is modified to receive shorter ammunition and exclude ammunition of standard length by inclusion of an insert positioned along the forward containment wall of the tray. The insert carries a feed lip that fits through a loading port orifice in the feed tray to direct shorter ammunition downwardly as it is being advanced towards the weapon breach for loading.

Abstract: Various launch vehicles configurations each include an X33 aeroshell of a booster or orbiter both of which use bell nozzle engines, and a feeding stage for supplying liquid propellant to the engines for providing primary lifting thrust for lifting a payload into orbit. The feeding stage can be an external tank without engines or a core vehicle also with bell nozzle engines. The orbiter or booster use three, two-two or five bell nozzle engines configurations and the feeding stage uses a zero or two bell nozzle engines. The combination of orbiters, boosters, external tanks and core vehicles offer a variety of configuration to meet particular mission requirements.

Abstract: The invention relates to a wall (2)-protection device (1), notably for a vehicle wall, against attack by a projectile. This device comprises at least one explosive charge (3) able to project at least one metallic block (7) in the direction of the projectile. The device is characterized in that the block or blocks (7) are in the shape of elongated bars, that is which have a maximal length greater than or equal to 10 times their smallest crosswise dimension, the explosive charge (3) being position opposite a longitudinal surface of the bar (7).

Abstract: The apparatus of the invention enables a two-brake torque limiting device to fix the position of one or more flaps and/or slats on an airplane wing when unplanned or abnormal conditions exist. The two-brake torque limiting device may include a trigger brake, a lock down brake, and a speed-increasing device. The trigger brake may use an electromagnetic brake to apply a braking force to the lock down section. The braking force transferred to the lock down section from the trigger section may be transferred through a speed-increasing device. The speed-increasing device allows for the use of a small and a lightweight electromagnetic brake. The invention also provides a method for reducing asymmetry in the wings of an aircraft using an asymmetry detection device, using a trigger brake, using a speed-increasing gear, and using a lock down brake.