Abstract: A method and system for providing navigational data required to guide an air-to-air missile to a target. The missile is equipped either with an infrared seeking sensor or a radar system. The trajectory of the target is predicted on the basis of a series of location measurements. A flight path of the missile is predicted such that the missile will intercept the target. Based on the predicted missile flight path, signals corresponding to the required rotational angle of the missile's sensor or radar antenna are generated and supplied to the sensor or radar's rotation control unit to cause the missile to move along the predicted flight path.

Abstract: A thermal de-ice and anti-ice system for aircraft surfaces employs a laminate in which flexible expanded graphite foil is an electrical and heat conducting layer that is disposed below an outer heat conducting layer, with an electrically insulating layer below the graphite layer. The flexible expanded graphite layer requires about three times less wattage than known resistance heating pad thermal systems to achieve de-ice and/or anti-ice temperatures. The temperature of the surface is controlled by varying the power supplied to the flexible expanded graphite layer of the laminate in response to a real time temperature value transmitted to a power control.

Abstract: Disclosed are devices and methods for the destruction of an explosive device, such as mines and other unexploded ordnance, without the detonation of the explosive device. The devices comprise an explosive charge that penetrates and opens the casing of an explosive device and forces reactive material into the explosive device, thus neutralizing it.

Abstract: A non-lethal alternative to the anti-personnel landmine. The TASER.RTM. alternative uses electronic stun capability in combination with a landmine housing and deployment system. The device can cover a radius of 15 feet (30 feet possible) and can be triggered by various sensors. Although the TASER.RTM. non-lethal area denial device would cause no deaths or injuries if accidentally triggered by friendly forces, it can also be permanently disabled when no longer needed, by remotely using a secure code to shut down the TASER.RTM. system. When triggered, the device launches darts in multiple directions at 10 or 20 degree intervals in a direction generally facing the enemy. The darts temporarily incapacitate any persons within an inch of the darts by causing uncontrollable spasms of the near surface motor control muscles causing temporary loss of the subject's motor control functions. The subject will fall and temporarily be completely incapacitated.

Abstract: A method of assembling, preparing, transporting to a launch site, and launching a rocket is disclosed. The rocket includes multiple stages and a payload to be carried into space. The rocket's longitudinal main axis extends horizontally during the assembling, preparing, and transporting of the rocket. The completed rocket may be transferred from a ship to a floatable structure with the rocket's main axis extending horizontally. The floatable structure can be movable and can raise the rocket prior to launching the rocket into space.

Abstract: An active reinforced elastomer system (50) has a rigid attachment block (56). A stiffening member (58) slides through an opening in the rigid attachment block (56). A shape memory alloy structure (62) is attached to the rigid attachment block (56). An elastomer panel (52) is attached to the rigid attachment block (56) and covers the stiffening member (58).

Abstract: To permit operators to change dies quickly and easily and to remove shot shells from any station, inspect them and replace them, bayonet snap in dies may be easily inserted into a tooling section of a reloader and shot shells can be removed from shell plates by pivoting the retainer free.

Abstract: A system for guiding the end phase of guided autonomous missiles consists of a marker unit having a sensor, a signature transmitter and a device for attachment to the target, as well as a cooperating direction finder in the guided missile.

Abstract: A self-deploying airfoil for a missile or the like of the type that is launched from a launch tube, the airfoil being formed of a flexible and resilient material and being movable by its own resilience from a stowed position in close proximity to the exterior surface of the missile when it is in the launch tube to a deployed position when the missile leaves the launch tube wherein it extends outwardly from the missile to provide lift and stabilize the flight of the missile. The airfoil comprises in its deployed position a first panel extending laterally outwardly from both sides of the missile and being secured at its midportion to an adjacent exterior surface of the missile, a pair of second panels secured at their outer ends to the outer end of the first panel and extending inwardly toward the missile, and a third panel secured at its midportion to an adjacent exterior surface of the missile opposite the first panel.

Abstract: An expandable fuel cell (72) for an aircraft (70) has a flexible structure (126) having a perimeter (124) attached to an airframe of the aircraft (70). The flexible structure (126) has an empty position, in which the flexible structure (126) approximately conforms to a moldline (76) of the aircraft (70), and a full position, in which the flexible structure (126) forms a smooth curvilinear protrusion from the moldline (76) of the aircraft (70). A fuel bladder (152) is positioned between the flexible structure (126) and the airframe.

Abstract: An aircraft engine mount includes a mounting platform fixedly joinable to an aircraft pylon, and a cooperating mounting ring fixedly joinable to an aircraft engine. The platform includes a pair of spaced apart lugs defining therebetween a failsafe slot. The mounting ring includes an inner flange fixedly joinable to the engine, and an outer flange extending from the inner flange into the failsafe slot. A pair of side links are pivotally joined to the outer flange and at least one of the lugs to carry loads therebetween. A failsafe pin extends across the failsafe slot and is fixedly joined to the lugs. A clearance hole is provided in the outer flange for receiving the failsafe pin and providing a failsafe alternate loadpath between the mounting ring and platform upon failure of the links to carry loads.

Abstract: A projectile is propelled from a location in air, through an air/water interface, and toward a submerged underwater object. The projectile includes a forward end that forms a cavitation void around the projectile in water, avoiding water drag on the remainder of the projectile. The projectile further includes an outwardly flared or finned rearward end that aerodynamically stabilizes the projectile in air and flare stabilizes it in water, in each case against yaw.

Abstract: An improved system is disclosed for upending/reclining an extraterrestrial vehicle. In one embodiment, first and second trunnion supports may be positioned on opposing sides of a u-shaped opening provided at the rearward end of a mobile support platform. A launch vehicle may be pivotably supported via trunnions received by the first and second trunnion supports for pivotal movement between a reclined position on top of the support platform to an upended position. In the upended position a launch vehicle will extend through the u-shaped opening. A bridge assembly may be selectively interconnected to the launch vehicle to facilitate handling, transport and storage therewith.

Abstract: An aircraft engine mount includes a mounting platform fixedly joinable to an aircraft pylon, and a cooperating mounting ring fixedly joinable to an aircraft engine. The platform includes four lugs arranged in forward and aft pairs. Four links are arranged in forward and aft pairs pivotally joined at opposite ends thereof to respective ones of the four lugs and to the mounting ring. The four links are symmetrically arranged both circumferentially and axially to carry both thrust loads and in-plane vertical and side loads between the mounting ring and mounting platform with failsafe redundancy.

Abstract: An electro-thermal or hot gas anti-icer of the "running-wet" type is mounted at the leading edge of an airfoil. Mechanical de-icers are mounted on the surfaces aft of the anti-icer. The mechanical de-icers throw off ice without creating runback water, thereby eliminating runback refreeze ridges caused by a known hybrid ice-protection system. Advantageously, the de-icers are of a type in which the airfoil has a semi-rigid skin that forms an aerodynamic surface of the airfoil, and in which there is at least one mechanical actuator for flexing the skin.

Abstract: A retractable sensor system (12) for an aircraft has a sensor (16) coupled to an actuation mechanism (18). The sensor (16) moves from a retracted position to an expanded position. A reinforced elastomer section (14) in an exterior surface (48) of the aircraft covers the sensor (16) and the actuation mechanism (18). The reinforced elastomer section (14) has an interior surface and an exterior surface and the sensor (16) has a portion adjacent to the interior surface. The reinforced elastomer section (14) has a flush position and an expanded position.

Abstract: An electrical mechanical blow-down mechanism for use with an aircraft spoiler avoids possible damage due to high inertial loading when a power failure occurs as the spoiler (10) is moving toward or is at an extended position by means of a structure including a ball screw mechanism (18) adapted to be connected to the spoiler (10) and including an input gear (34) adapted for rotation about an axis (36). The mechanism is ultimately driven by an electrical motor (20) having a rotary output (22) with at least one gear (26, 28) interconnecting the input gear (34) and the rotary output (22). A pawl (36) is mounted for movement between positions engaged with and disengaged from the input gear (34) and a spring (78) is utilized to normally bias the pawl (36) toward the engaged position. A solenoid (50) is operable to move the pawl (36) against the spring (78) toward the disengaged position and a motion sensor (90) is associated with the input gear 34 to determine the direction of rotation thereof.

Abstract: A seat belt hanging and holding member of the present invention is capable of reducing manufacturing cost by reducing the material cost required for a coating member while improving safety. The seat belt hanging and holding member 10 slidably hangs and holds a seat belt by folding back an intermediate part of the seat belt (waving belt) 74. The member 10 comprises a base member, 20 made of a metal plate having a slot 22 and a coating member 30 made of a synthetic resin which covers at least the periphery of the slot 22 of the base member 20 and is provided with a seat belt-inserting hole 31 on a part corresponding to the slot 22. The slot 22 is provided with an edge part 22a corresponding to at least the part on which the seat belt 74 is folded back, which is formed in a smoothly curved surface along the direction in which the seat belt 74 is folded back.

Abstract: A device for assembling, transporting and launching rockets carrying a payload for transportation into space includes a ship and a floatable structure. The ship includes facilities on a covered deck to assemble multiple rockets in a horizontal orientation. The assembled rockets are hoisted from the ship to the floatable platform in a horizontal orientation. The floatable structure includes a hanger for the rockets, and facilities necessary for moving each horizontally oriented rocket to a launching pad, and for raising the rocket into a vertical position. A control room, onboard the ship, permits monitoring and control of the assembly of the rocket onboard the ship and of the launching of the rocket from the floatable platform.

Abstract: A weapon includes a barrel for firing ammunition therefrom; and an apparatus for monitoring firing stresses of the barrel. The apparatus includes a body sound sensor mounted on the weapon and emitting a first signal representing body oscillations of the weapon upon firing; and an electronic evaluating device connected to an output of the sensor. The electronic evaluating device includes a comparator for comparing measuring signals, representing the first signals, with reference signals representing different charges and for emitting second signals representing results of the comparison; and a non-volatile memory operatively connected to the comparator for additively receiving the second signals and for releasing, on demand, the number of firings and information on an accumulated firing stress of the barrel.