Abstract: A drive assembly for use with a mechanical flying or walking device comprises an articulated member (7) having first and second portions (7a, 7b) arranged such that the portions move relative to each other, and a drive mechanism (9) for imparting motion to the articulated member. The drive mechanism (9) comprises: a drive member for imparting a cyclic motion on the articulated member, and a control member for controlling, in a predetermined manner, the relative position of the first and second portions during each cycle of the cyclic motion of the articulated member. In the case of a mechanical flying device, two such drive assemblies may be provided, the articulated member of each assembly forming a wing.

Abstract: A method and system for controlling a movable appendage on an aerospace vehicle independent from the position of the aerospace vehicle. First and second beacons containing actual position information for the movable appendage are tracked and acquired by first and second beacon tracking sites. The beacon tracking sites report the azimuth and elevation data relating to the position of the movable appendage to a processor where a correction command is determined based on an error calculated from the position data and a desired position. The correction command is communicated to the movable appendage so that appropriate correction to the desired position can be made.

Abstract: Structural panels for use in manufacturing aircraft fuselages and other structures are disclosed herein. In one embodiment, a structural panel configured in accordance with the invention includes a skin having at least one offset surface. The structural panel can further include at least first and second stiffeners. The first stiffener can have a first flange portion mated to the skin adjacent to the offset surface. The second stiffener can be spaced apart from the first stiffener and can similarly have a second flange portion mated to the skin adjacent to the offset surface. The structural panel of this embodiment can additionally include a support member mated to the first flange portion of the first stiffener, the second flange portion of the second stiffener, and the offset surface of the skin.

Abstract: A detent body with a center bore is secured to the chamber wall of a paint-ball gun. A floating detent with a hollow core and a domed tip reciprocates within the center bore, allowing the tip to extend into the chamber to restrict movement of a paint ball. Axially aligned slots extend through opposing sides of the floating detent. A pin extends through the slots and corresponding pin holes in opposing sides of the detent body to create a stationary abutment for limiting axial movement of the floating detent. A compressive spring disposed within the hollow core between the pin and the inner end urges the outer tip into the chamber. A set screw threaded into the end of the hollow core engages the pin and the floating detent. Rotation of the set screw regulates axial movement of the outer tip into and out of the chamber.

Abstract: An assault rifle with a hand and forearm guard for protection of the user's hand and forearm. The assault rifle may be aimed from the side or on top of a barrier using an optical sensing system.

Abstract: A modular overhead stowage bin system has an outboard bin support and a center bin support coupleable to the fuselage. First and second stowage bin modules having different storage capacities are connectable to the outboard and center bin supports in first and second configurations. In a first configuration, the first and second stowage bin modules are coupled to the fuselage and have a first overhead aisle therebetween with first opposing edge portions. The first and second stowage bin modules in the second configuration are coupled to the fuselage and have a second overhead aisle therebetween. The second overhead aisle has second opposing edge portions each shifted laterally relative to the position of the first opposing edge portions of the first overhead aisle when the first and second stowage bin modules are in the first configuration.

Abstract: The Mixed Mine Alternative (MMA) System is a military system designed for use in mechanized warfare. The MMA System has three components, MMA smart Antitank mines, MMA Antihandling Sensors linked to the MMA smart Antitank mines, and MMA Remote Control Units (RCU). The MMA smart Antitank (AT) mines contain a primary sensor system hardened against countermeasures and a kill mechanism similar to existing scatterable AT mines. The MMA AT mine is capable of transmit and receive communications with a Remote Control Unit and with the MMA Antihandling Sensors (AH). The communications capabilities and processors in the MMA AT and the MMA AH allow the system to establish MMA AT to MMA AH links after the mines have been scattered. MMA AT will be linked to MMA AH that are within their lethal radius. The MMA AT mine processors allow the mine primary antitank sensor to be on or off. The mine may receive and act on detonate instructions from the primary antitank sensor, from the antihandling sensors, or from the MMA RCU.

Abstract: An installation includes at least a pressurized lubricating circuit for elements housed in the rocking crankcase, each circuit including a radial transfer bearing between two opposite cylindrical journals coaxial about the rocking axis, one fixed journal on a fixed part and one pivoting journal on a pivoting part integral with the pivoting crankcase. Each transfer bearing has two U-shaped annular gaskets facing each other and spaced apart along the rocking axis so as to define between them an annular pressurized liquid lubricant chamber. The annular chamber is supplied with pressurized liquid lubricant by at least a supply duct integrated in the fixed part and whose upstream part is connected to a pressurized lubricant source, and feeds the rocking crankcase with pressurized lubricant through a dispensing duct emerging into the rocking crankcase. The invention is useful for lubricating rocking power transmission boxes for convertible aircraft tilt rotors.

Abstract: Structural panels for use in manufacturing aircraft fuselages and other structures are disclosed herein. In one embodiment, a structural panel configured in accordance with the invention includes a skin and at least first and second stiffeners. The first stiffener can have a first flange portion mated to the skin and a first raised portion projecting away from the skin. The second stiffener can have a second flange portion mated to the skin and a second raised portion projecting away from the skin. At least one of the first flange portion of the first stiffener and the second flange portion of the second stiffener can extend toward the other of the first flange portion and the second flange portion to form an at least approximately continuous support surface to which a frame can be attached.

Abstract: A lightweight, laminated structural component, such as a skin section for an aircraft fuselage, is constructed of at least two sheet metal plies that are adhesively bonded to each other. One ply is an uninterrupted ply. The other ply is a lattice with open fields surrounded by strip shaped lands which fortify load exposed areas of the lamination. The open fields of the lattice make mechanical or chemical pocketing operations unnecessary. By shaping and positioning the strip shaped lands including struts in accordance with load patterns to which an aircraft skin is exposed in use, the skin characteristics can be tailored as required.

Abstract: A human body attached wing device (20) for use during downhill alpine activities such as skiing and snowboarding. Wing device (20) includes independently operable, mirror image, left and right wings (24) and (26), which may be joined to a user (22) on or about the shoulders via a harness (28) that is worn by user (22). Each of wings (24) and (26) generally include ram-air canopies, (30) and (32), respectively, that inflate during use to form lift-providing airfoils. The surface area of canopy (30) is defined by first and second ends (34) and (36), a leading edge (38), and a trailing edge (40). Canopy (30) may include additional stiffening members to help maintain the shape of wings (24) and (26) when it is either deflated or only partially inflated, or when it is used as an air brake. Canopy (30) may also include flexible triangular struts (110) that stabilize trailing edge (40).

Abstract: A fireworks stand for elevating fixed-position fireworks, especially cone type fountains, having a body with an inner cavity for storing the fireworks and an upper platform for supporting the fireworks during discharge. The platform is nested into an upper end of the body and receives an upper keeper that is sized and shaped to fit inside of the nested platform in order to secure the fireworks. The cavity has a lower keeper and base structure that is removed to provide access to a plurality of inserts, which house the fireworks.

Abstract: A lower sling attachment adapter for use in the M-16 rifle and M-4 carbine and their equivalents utilizing a rear or butt stock mounted on a tube, one end of which tube is threaded into the rear of the receiver of the weapon, the improvement comprising a lower sling attachment means mounted on said threaded tube near the receiver and having a hole through which the said threaded end of said tube is passed, said lower sling attachment means having sling mount means on at least one side thereof to which the lower end of a weapon sling is attached.

Abstract: An ETC igniter and compatible electrical connector for enabling an ETC gun to be used in a battlefield setting in close proximity with personnel and sensitive electronic equipment. This is accomplished by providing a current path to and from the igniter that is electrically isolated from all other portions of the gun. The connector and igniter are adapted to be capable of withstanding the high connection forces necessary to prevent arcing and the extreme stresses imposed during firing of the gun.

Abstract: A warhead device comprising explosive charges and effect elements or effect agents for incorporation in a missile. The warhead device consists of a number of modules or modular charges (1a–1f) arranged to be actuatable between two or more pivotal positions in the cross-section of the warhead device. Each module comprises outer walls (9–14) that one by one are directed outwards depending on the position or pivotal position assumed by the module. Each outer wall of each module comprises warhead effect elements and/or effect agents that differ from the other warhead effect elements or agents. The outer walls that are directed outwards simultaneously form or are part of the common outer wall of the warhead device, and project a selectable warhead effect from the warhead device.

Abstract: An apparatus and associated method for launching and recovering a lighter-than-air aircraft are provided. The aircraft includes an envelope that is substantially filled before launch with a lift gas and a second gas. The lift gas and second gas are substantially separated in the envelope by a boundary layer of mixed gas, formed by the lift and second gases. The aircraft is supported by one or more masts as the lift gas is injected to achieve the required buoyancy for launch. The aircraft is then released and rises, for example, in an inclined orientation. As the aircraft climbs, the lift gas expands in the envelope, and the second gas is vented therefrom. During horizontal descent, air can be pumped into the envelope to maintain the envelope in a substantially filled configuration. The air and lift gas can be mixed to avoid sloshing and pooling.

Abstract: A low-cost airliner defense system utilizing self powered, retrievable, towed decoys against man portable heat-seeking missile (MANPAD) systems provides both high power and a large IR radiating surface area. An efficient and lightweight integrated turbine-alternator extracts sufficient electric power from an air stream directed through a small decoy deployed and towed behind an aircraft during the vulnerable phases of a flight to power a large and intense IR emitter. Unfurled IR radiator “petals” present large area arrays of rear-facing IR emitters. During the high-altitude cruise phase the radiating petals furl down folding around the retrieved decoy body as it is stowed in a streamlined housing for minimizing fuel consumption and maneuverability penalties.

Abstract: A detachable tray of the type usually pivotally attached to the seat back of a conventional airliner includes a layer of threat-resistant material for precluding penetration of a projectile from a firearm or sharp edged or sharp pointed weapon and serves in the manner of a shield to prevent injury to a person's shielded body parts. Where the economics of manufactur permit, the whole tray may be made of threat-resistant material. One or more handles or straps may be disposed on the bottom side of the tray to facilitate manipulation in positioning the tray to render it most effective to ward off an attack.

Abstract: Anti-personnel tank fired ammunition designed for attacking personnel at various ranges includes a hollow base member adapted with an electric primer and a plastic or aluminum canister containing a payload at one end thereof. In operation, the hollow cartridge is loaded with a solid propellant. The electric primer which is centrally located in the solid propellant is fired and provides a flash together with the gasses needed to ignite the propellant. The burning propellant then provides the gasses needed to force the canister from the gun tube in which the ammunition is positioned.

Abstract: A projectile in a cartridge designed to be launched from a grenade launcher. The projectile is adapted to be secured to the housing of the cartridge. The projectile includes a camera contained in the projectile body and connected thereto by a cord, and a transmitter contained in the projectile body and connected to the camera. In addition, the projectile includes elements for pinning the front part of the projectile body to a target, and elements for separating the front part of the projectile body from the back part of the projectile body and expelling the camera from the projectile body when the projectile is pinned to the target so that the camera is freely suspended from the projectile by the cord and can rotate in a wind through 180 degrees to observe its surroundings and transmit images thereof.