Abstract: A fitting for trimming the horizontal stabilizer of an aircraft, made of composite material, the fitting including side walls of a torsion box as well as joining elements which join the fitting to the frames of the tail fuselage of the aircraft, the side walls being joined together by a central element which includes a first end part joined to the first side wall of the fitting, a second end part joined to the second side wall of the fitting and a central part which joins together the end parts, the fitting includes end elements which are joined to the side walls on their outer face, the fitting having, owing to its greater rigidity in response to side load and vertical load stresses which tend to close the side walls, its greater integration and the simplicity of the load path, an optimum structural behavior in response to the aircraft stresses.

Abstract: An apparatus for orbital change of a satellite incorporates a capture mechanism for space debris and a tether connecting the capture mechanism to a satellite. The tether is extendable to position the capture mechanism relative to the space debris. A controller is employed for timed release of the space debris by the capture mechanism for orbital change by the satellite.

Abstract: The present invention is an improved charging handle for a firearm. The handle is generally non-reciprocating and features a user activated forward assist. The major components are an actuator to provide charging function and upon which other components are mounted, a spring biased lever with a hook which biases downward so that the hook may interface a bolt carrier when the lever is activated, and a blade upon which handle structure is mounted. In the preferred embodiment, the handle is ambidextrous and features a spring detent to keep it in stowed position until the user desires use. The handle will only reciprocate when the lever is activated, which in turn requires intentional user action, thereby providing a relatively safer weapon to operate.

Abstract: A safe and arm (S&A) device is disclosed. The device utilizes a no-fire separation distance and a mechanical configuration of primary explosive/booster explosive and secondary explosive to establish a safe mode. While in safe mode, the device would allow no more than 1 in 1 million detonation transfers to occur from primary to secondary. In armed mode, the no-fire separation distance is taken away, allowing reliable detonation transfer. Two arming environments, which occur after launch and safe separation, are used to move the S&A device to armed mode. The first environment is the release event of the projectiles from their packed state in a dispenser. The second environment is a target sense mechanism. If either arming environment returns to its original state, the mechanism returns to safe mode. The S&A device will not allow inadvertent packing into the dispenser of explosive devices in the armed state.

Abstract: The present development relates to an improved wing having a tip tank assembly. The tip tank assembly is attached to a distal end of an outer wing section. The tip tank assembly includes a tank, a pair of mounting brackets and a fairing assembly. The fairing assembly includes a nose piece, a central piece, a tail piece, an inner end plate, and an upper close out piece. The inner end plate extends perpendicularly downward from a lower surface of the outer wing section eventually terminating at a bottom portion of the central piece. The inner end plate acts as an air dam to trap high pressure air that is generated during flight, substantially increasing the lift of the wing. Lastly, the upper close out piece extends between an upper wing surface and an upper portion of the central piece increasing the overall wingspan of the aircraft.

Abstract: Embodiments of the invention relate to a vane assembly formed by a forward airfoil segment and an aft airfoil segment. The aft segment is made of metal and can define the trailing edge of the vane assembly. The forward segment can be made of ceramic, CMC or metal. The forward and aft segments cannot be directly joined to each other because of differences in their rates of thermal expansion and contraction. The forward and aft segments can be positioned substantially proximate to each other so as to form a gap therebetween. In one embodiment, the gap can be substantially sealed by providing a coupling insert or leaf springs in the gap. A separate metal aft segment can take advantage of the beneficial thermal properties of the metal to improve cooling efficiency at the trailing edge without limiting the rest of the vane to being made out of metal.

Abstract: A fuze for a submunition comprises a fuze housing with a stabilizer ribbon for aerodynamic orientation, a fuze slider released by tension on the stabilizer ribbon, an air-powered electric generator extended into the airstream by the fuze slider and powered in flight by high-speed airflow, a MEMS safety and arming device, a fuze circuit board including an explosive fireset, and an electrically initiated firetrain. The fuze is fixed to and communicates explosively with the end of a grenade warhead.

Abstract: An alignment device for telescopic sight mounts (101) utilizes a front alignment portion (103) and a rear alignment portion (105) installed on a firearm 405. A front bushing (109), clamped in a front mount assembly (401) of the firearm provides a precision sliding fit with a front alignment rod (107). A rear bushing (113), clamped in a rear mount assembly (403) of the firearm provides a precision sliding fit with a rear alignment rod (107). Acceptable alignment of the front and rear mount assemblies is indicated by full engagement of a male indicator portion (115) of the front alignment rod and a female indicator portion (117) of the rear alignment rod when the respective rods are slideably engaged. A bore sight engagement element (151) allows bore sighting of the mounts with the rifle bore (425).

Abstract: A noise generation device is taught which is used in conjunction with a shotgun generating a blast which has a) at least one chamber for receiving the blast from the barrel; b) a connecting bolts for joining the one chamber to the barrel; c) at least one exhaust port for venting the blast from the barrel; d) a channeling ramp for directing the blast towards the vent, and a blade and drive for pushing the device through a wall. It also includes various noise and blast generators which may be used to supplement the initial blast.

Abstract: Preferably a seat mounting rail for a passenger aircraft includes a base connected to a crown by a web. The crown includes two support flanges protruding laterally in opposite directions from a reinforcement zone that connects to the web and that has a seat-securing groove extending longitudinally therealong. Floor panel elements can be supported on the support flanges. The reinforcement zone top surface preferably does not protrude above the support flange top surfaces but rather is at least substantially flush and planar therewith. The single horizontal base flange forming the base, the single vertical web and the support flanges preferably form a generally I-shaped sectional profile. The reinforcement zone may include a triangular sectional hollow lower reinforcement structure tapering to the top of the web. Large-area floor panels can span continuously laterally over the rail and can be arranged independently of the spacing between the rails.

Abstract: Aircraft and leading edge apparatuses and corresponding methods are disclosed. In one embodiment, an aircraft system includes an airfoil with a leading edge device that is movable among a retracted position, at least one first extended position, and a second extended position. A first actuator can be operatively coupled to the leading edge device to move the flow surface between the retracted and the at least one first extended position. A second actuator can be operatively coupled to the leading edge device to move the flow surface between the at least one first extended position and the second extended position.

Abstract: The invention relates to a device for the electrical initiation of at least one pyrotechnic microcharge (3), this device being characterized in that it comprises a support element having at least one conductive finger (6) connected to a first terminal of a central control unit (8), a second terminal of said central control unit (8) being intended to be electrically connected to an electrically conductive support for the pyrotechnic microcharge (3). The invention also relates to a microactuator (1, 1a, . . . , 1h) and a microsystem (1?) that use such an initiation device.

Abstract: The present invention provides an apparatus and a method for reducing wing-tip vortex energy during seismic exploration. The apparatus includes a vortex concentrator of deployed proximate a tip of a hydrofoil and a vortex reducing device deployed proximate the vortex concentrator.

Abstract: Launch and recovery of an aerial vehicle by a forwardly moving surface vehicle relies on a winch module having a winch to selectively reel out and reel in a towline and a sensor capable of sensing tension in the towline. A lifting body assembly having a pair of lifting bodies and a snagging wire is connected to the towline. The lifting bodies lift and laterally extend the snagging wire between the lifting bodies. An aerial vehicle flying through the air engages the snagging wire by a hook. A first signal representative of tension of the towline causes the winch to reel in the towline and to bring the aerial vehicle to the surface vehicle, and a second sensor associated with the hook generates a second signal representative of tension in the hook and causes the aerial vehicle to cut its motor.

Abstract: A “non pyrotechnic explosion device” closely replicates in sound and visual cue a “real” exploding device, but without the accompanying safety concerns. This device is not only realistic and safe, but is inexpensive to operate and maintain, durable, and easy to transport and operate. It provides the user with numerous options for employment from mine, bomb, and improvised explosive device (ied) simulators to an artillery impact simulator. The device is comprised of a pressurized chamber, a pressure release device, an expulsion substance container, and a rupture-able/explosion tube assembly.

Abstract: An aircraft landing assist apparatus is designed to be retrofit to existing aircraft having internal constructions that have been modified to support the apparatus. The apparatus is designed so that on rough landings of the aircraft on a ship deck, the apparatus will collapse in a controlled manner to avoid any damage to ammunition and/or fuel storage areas of the aircraft. In one embodiment the apparatus includes a plurality of support struts that each include an eccentric bushing. A locking pin can be used to selectively position the eccentric position to adjust the overall length of its associated strut.

Abstract: A generally cylindrical security door module is designed for retrofit into the passageway of an aircraft leading to the cockpit. Two doors, forward and aft, are provided which are mounted for opening and closing upon commands emanating from the cockpit. Both doors are normally closed and only one normally opens at a time. A candidate for entrance to the cockpit is permitted to enter the module when the cockpit personnel open the aft door, which is then closed. Sensing apparatus may be employed to establish the identity and clearance of the candidate. Upon approval, the cockpit personnel open the forward door to admit the candidate. Emergency release apparatus is also described.

Abstract: An in-flight refueling system, boom, and method are provided for extending the range of motion of an in-flight refueling boom carried by a first aircraft so as to facilitate an in-flight refueling operation between the first and the second aircraft. More specifically, in some embodiments the present invention provides a rotating device, operably engaged with at least one airfoil, and configured to substantially surround and rotate about the in-flight refueling boom such that the rotating device and the at least one airfoil operably engaged therewith, may be actuated so as to extend the range of motion of the in-flight refueling boom.

Abstract: A vertical fore grip for a firearm with an integrated pressure switch pocket. The vertical fore grip includes a body with internal storage cavity, a mount adapted to secure a firearm, a pocket for a pressure switch on the perimeter of the body, and a cap to secure a pressure switch and waterproof the internal storage cavity. The mount has a groove for a firearm rail, at least one locking bar, and a spring for engaging the locking bar to a firearm rail.

Abstract: A universal cylinder of a revolver comprises a cylindrical case, this case has apertures for cartridges, executed in the case, and the open zone grooves of a lateral cylindrical surface for input and output cartridges.