Abstract: A process for designing and producing spacecraft more efficiently, without the excessive time, complexity and expense usually associated with spacecraft design. The process moves the design complexity usually associated with spacecraft design to payload modules whose designs are potentially reusable in other spacecraft missions. Each module is designed to be largely independent of a parent spacecraft structure, the design of which can be simplified to accommodate multiple modules that connect to the parent structure through a standardized backbone interface. Each module is designed for independent structural integrity, and to provide its own thermal management. Modules may also provide their own power regulation and, optionally, their own power storage and generation capabilities. Modules may also provide their own attitude control systems. Attachment of modules to the parent structure is simplified because of the modules' independence.

Abstract: A miniaturized bulkhead with a barrier member having a thickness in the range of less than 0.05 inches thick for separating explosive charges on opposites sides. The miniaturized bulkhead is manufactured from an age hardened nickel-base alloy. First and second cavities are separated by the barrier member integral with the initiator body. The first cavity is filled with an explosive donor charge, and the second cavity is filled with an explosive acceptor charge. The composition of the age hardened nickelbase alloy includes nickel in the range of 50-55 percent by weight.

Abstract: Selected rows of seats for a wide body aircraft (i.e., having two or more passenger aisles) have seat groups that can expand or contract to change the number of seats in a row and the seat width. Conversion is possible with all seat components remaining attached to their respective frames, so that no detachable units have to be stowed. The convertible seat configurations are adaptable to incorporating individual amenities, including individual electronic displays.

Abstract: The non-lethal TASER.RTM. Area Denial Device (TADD) can be deployed to prevent enemy reconnaissance troops or small raiding parties from penetrating lines and for their capture. The inventive device comprises 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. This invention comprises improvements which address the issue of deployment. Regardless of which of the two flat sides of the device is in the up position, it provides the ability to launch the proper set of wires at an upward angle to intercept the subject when the target subject is in the correct position. It also simultaneously establishes a ground wire connection and prevents the second (downward facing) unusable set of wires from loading or short circuiting. The possibility of the device landing on the radius edge is eliminated by shaping the housing to make it unstable on that plane.

Abstract: A rotary flying device comprising an inflatable airfoil having an axis of rotation for rotation thereabout, an inflatable stabilizer disk mounted on the airfoil, a bearing assembly attached to the axis of rotation, and a bridle attached to the bearing assembly for receiving a support line. The airfoil is provided with one or more ribs for providing rigidity thereto. Alternatively, or simultaneously, the airfoil is provided with end caps or a periphery cage member for providing the necessary rigidity thereto.

Abstract: A supercavitating water-entry projectile having empennage on the aft end ch provides both aerodynamic and hydrodynamic stability and a supercavitating nose section is provided. A representative projectile is a subcaliber munition adapted for use in a 25 mm weapon using a sabot currently in use with the M919 round. The projectile has circumferential grooves around its center section to match these sabots. A key feature in the invention is the size and shape of the nose section. The projectile has a novel high strength extended blunt nose section followed by a truncated conical section which angles towards the body of the projectile in the range of five degrees. During underwater trajectory, the entire projectile is contained within the cavitation bubble formed by the blunt nose tip. The projectile's aft empennage, which provides both aerodynamic and hydrodynamic stability, fits within the bore of the weapon.

Abstract: A mechanism for locking the fins of a missile in place when the missile is not in use utilizes tabs inserted in slots of the output shafts of the fins to immobilize the output shafts and the fins. In one embodiment, the tabs are cantilevered on a locking plate from which they extend radially toward the output shafts. A cam plate slidably engages the tabs on the locking plate and simultaneously lifts all the tabs out of the slots when it is rotated. for disengagement of the locking mechanism. Operation of the locking mechanism can be effected either manually, using a specialized tool, or remotely, using for example a pyrotechnic actuation device.

Abstract: A fairing (100) for an expandable bay of an has a ramp (108). A front linkage bar (102) has a first end pivotally connected to a finger (106) of the ramp (108) and a second end pivotally connected to the aircraft. A mating panel (112) is next to an interior edge (132) of the ramp (108) and pivotally connected to the ramp (108). An exterior elastomer panel (124) is connected between an exterior edge (126) of the ramp (108) and the aircraft.

Abstract: A tail (14) for an aircraft (10) has a center member (20) pivotally attached to the aircraft (10). A leading edge flap (22) extends along a length of the center member (20). An elastomeric skin (30) is connected between an exterior surface (26) of the center member (20) and an adjacent exterior surface (28) of the leading edge flap (22).

Abstract: A system and method for target reacquisition and aimpoint selection in missile trackers. At the start of iterations through the process, distance classifier correlation filters (DCCFs) memorize the target's signature on the first frame. This stored target signature is used in a subsequent confidence match test, so the current sub-frame target registration will be compared against the stored target registration from the first frame. If the result of the match test is true, a patch of image centered on the aimpoint is used to synthesize the sub-frame filter. A sub-frame patch (containing the target) of the present frame is selected to find the target in the next frame. A next frame search provides the location and characteristics of a peak in the next image, which indicates the target position. The DCCP shape matching processing registers the sub-frame to the lock coordinates in the next frame. This process will track most frames, and operation will repeat.

Abstract: An emergency vision device for use in a smoke emergency to enable an user to look through a windshield or view an instrument, comprises a housing; an inflatable enclosure having a first end for being disposed toward an user, a second end for being disposed toward the windshield or the instrument, the inflatable enclosure being stored within the housing when not in use, the first and second ends having first and second transparent panels, respectively, such that visual information from beyond the windshield or from the instrument is transmitted through the second panel to the user through the first panel; a blower operably connected to the inflatable enclosure adapted to inflate the enclosure; a first switch for operating the blower; and a member operably connected to the inflatable enclosure and the first switch such that the switch is activated when the inflatable enclosure is removed from the housing.

Abstract: A rising table assembly including an extension assembly and tabletop. The table may be stowable beneath a floor surface. The table assembly is typically extendible through an opening in the floor surface to a position above the floor. A set of closure doors may be provided to act as a floor surface when the table assembly is in stowed position beneath the floor. The table assembly is particularly suitable for use in vehicles such as aircraft, trains, motor homes, or boats. The table assembly may be of use in other situations where space is a premium.

Abstract: A selectively actuatable pressure relief valve (110) includes a housing (112) that defines an annular projection (118), an inlet port (120) in the lower surface (122), and a relief vent (124) in the sidewall. A first plunger (128) and a second plunger (138) are longitudinally disposed within the housing and are actuatable between an open position and closed position. The valve is normally biased in the open position by a pair of springs (136 and 146). The valve may be actuated between the open and closed positions by a solenoid (148) or may be locked into the closed position by the manual override device (154). When the valve is in the closed position, the spring may be overcome by the fluid pressure exceeding a predetermined limit, thereby displacing the valve into the open position and providing high pressure relief.

Abstract: A joint assembly and an aircraft wing assembly containing such a joint assembly are provided. Each joint assembly for connecting together a first member (1) and a second member (4) comprises a second channel member (5) affixed to the first member (1) having a first channel member (12) with sidewalls (15, 16) engageable with first and second elements (8, 9) of the second channel member. The second member (4) has a flange which engages a flat surface (14) of a base portion (13) thereof. The various elements are held together by bolts (19, 20, 23) and tolerance adjustment in both horizontal and vertical directions is provided by mutual sliding of the surfaces prior to drilling apertures for the bolts.

Abstract: A submarine signal launcher is disclosed for preventing pinched control ws therein. The submarine signal launcher includes a gas generator, an acoustic device countermeasure, a launch tube for housing the gas generator and the countermeasure, and a ram plate positioned between the gas generator and the countermeasure. A status cable is connected to the countermeasure and intermediately threaded through the ram plate and joined to the gas generator. A collapsible tube connected to the ram plate and to the gas generator. The status cable is confined within the collapsible tube. Securing members are formed on opposing ends of the collapsible tube for securing the collapsible tube to the ram plate and the gas generator, wherein upon assembly of the gas generator with the ram plate and the countermeasure within the launch tube, the collapsible tube will protect the cable from being pinched between joined ends of the ram plate and the gas generator.

Abstract: A multiple missile launcher has a plurality of canister holding chambers. Each canister includes a standard connector for connection by a standard cable to a missile launch sequencer. Each canister is loaded with four missiles. The cable has more than enough signal paths to couple launch and safe signals to a single missile, but not sufficient to independently control four missiles. A missile selection signal generator generates selection signals which are sent over a selected one of four separate signal paths of the cable to directly (without intervening active elements) actuate a relay associated with the selected one of the missiles. The four relays are part of a multiplexer which couples the signal set for launch and safe to the selected one of the missiles.

Abstract: Patent of invention of an electronic delay detonator refers to a detonator meant to initiate explosive charges after an electronically predetermined delay time, transforming thermal energy generated by a heat source (2) into electrical energy through a miniaturized thermoelectronical battery (3), packed inside the detonator shell, placing the referred heating source over the heating face (3-A) of the battery (3) which has its opposing face unheated (3-B), being coupled in the detonator a nonelectrical initiation signal conductor medium (1) for the cap, having in the detonator shell the corresponding stages of a capacitor (4) for storage of electrical energy, an electronic timing circuit (5) which provokes the energization of the electric squib, following the detonation of a primary explosive (7) and a consequent detonation of the secondary explosive (8).

Abstract: A hinge line system (52) for an aircraft has a structural block (22) attached to a first edge of a hinge line. The structural block (22) has a flange (28) attached to a first end of an elastic sheet (32). A second structural block (24) is attached to a second edge of the hinge line. The second structural block (24) has a second flange (30) attached to a second end of the elastic sheet (32).

Abstract: A nautical vehicle for traveling in a fluid environment, the nautical vehe comprising a body having a dorsal fin mounted thereon. The body comprises a sidewall, a forward nose and a rear propulsor for propelling the vehicle in an axial direction. The dorsal fin is mounted on the sidewall, and includes a dorsal fin surface and camber generating element for generating a camber to provide a sideways thrust on said body to facilitate brisk maneuvering of the vehicle in the fluid environment.

Abstract: A vehicle occupant protection apparatus (10) includes an inflator (16) which, when actuated, emits inflation fluid. The apparatus (10) further includes an electrically actuatable igniter (24) which, when actuated, actuates the inflator (16). The igniter (24) includes an ohmic heating element (44) connected between a pair of electrodes (40, 42). An ignition droplet (46) is adhered to the ohmic heating element (44). The ignition droplet (46) is a mixture of pyrotechnic material and a resin binder which is cured by UV irradiation.