Abstract: A power source (10) for providing energy to drive a mechanical device including a receiving chamber (11) and discrete propellant charges (23) for selective detonation whereby gases generated by the selective detonation expand into the receiving chamber (11) wherein said receiving chamber includes a reactive closure (15) which dynamically responds to pressure changes in the receiving chamber and wherein said power source further includes a linkage (16) associated with the reactive closure for transmitting energy from the dynamic response of the reactive closure to the mechanical device.

Abstract: The invention proposes to address the vibration transfer function transmitted by a turbo-fan engine or equivalent to the aircraft structure, with two types of isolators mounted on a unique assembly but with a different physical response to the transfer function, an absorbing one and a resonating one. The difference in nature of such responses induces a non-interaction effect between the two isolators. The invention concerns more specifically a two-tone isolator assembly adapted to be mounted on an aircraft or equivalent comprising in particular a head, a cabin yoke and a power engine structure having a longitudinal axis crossed by a radial plan. The two-tone isolator assembly comprises, located at the head side of the aircraft, at least one support for, at least, one fluid mount isolator and two dynamic absorbers, and mechanical means to couple said support to the power engine structure and to the cabin yoke.

Abstract: The invention concerns a land and flying vehicle with its tubular frame, 2 main rotors with blades and adjustable pitch-propellers, with its drive propelled by the force of a hydraulic turbine located at the end of its driving shaft. Said force is propelled by a very high pressure pump driven by an internal combustion engine or jet engine. Streamlined pusher propellers (already patented) located on the side are driven by hydraulic turbines located at the shaft end of rotating propellers from 0° to 180°, once they are extended. Drawings describe the revolutionary design and unable the installation of said system on some current helicopter. By said method the present drive assembly, gimbal joints, gear boxes, are replaced with turbine drives with smooth and lightweight start. Said method can be adapted on running vehicles, including trains, whereof the designs and applications are reserved.

Abstract: A foldable tail assembly for an aircraft includes a stabilizer and a pair of right and left fins mounted with respect to the stabilizer so that the fins may lay flat over the stabilizer during periods when the aircraft is not flight-ready, and so that the fins may be erected above the stabilizer to form a triangular configuration when the aircraft is ready to fly.

Abstract: Accessories for firearms. They are designed to reduce the recoil felt by the shooter when a firearm is discharged. The accessories meet this goal by modifying the decay pattern of vibrations set up in the stock when the firearm is discharged. Kick may be further reduced by elastic compression and also by pneumatic compression of air in sealed pockets formed in and by accessory components.

Abstract: The hammer of a gun has a channel in its front face, making direct contact between the hammer and the gun's firing pin impossible. The tip of a transfer bar retained within the channel moves to fill the channel and thus permit firing of the gun, only when the trigger is pulled. This construction avoids certain types of accidental discharge.

Abstract: An apparatus for the section-wise autofrettage of gun barrels (22) by a hydraulic pressure generated inside the barrel. The apparatus (1, 1?, 1?) comprises a mandrel-shaped insert (2, 2?, 2?) inserted into the barrel (22) from the breech opening. A first sealing device (3) is disposed at one end of the insert (2, 2?, 2?), and has a seal packet (5) disposed on a seal seat (4) of the insert (2, 2?, 2?). The seal seat (4) is limited at the front by a threaded sleeve (7) screwed onto the insert (2, 2?, 2?), and an annular intermediate part (8) adjoining the threaded sleeve (7) at the rear. The seal packet (5) includes at least one O-ring (10) held by a shoulder (9) of the mandrel-shaped insert (2, 2?, 2?), and a high-pressure seal (15) formed by two partial rings (13, 14) that are connected to one another by a conical contact surface (16).

Abstract: The present invention resides in an infrared identification system for identifying military vehicles as friendly or hostile. The infrared identification system includes a seed introduction system, in each friendly vehicle, that introduces trace quantities of a particular seed formulation into the vehicle's exhaust. An infrared detection system, also in each friendly vehicle, detects the spectrally-discrete thermal emissions of the seed formulation to identify those vehicles having the thermal emissions as friendly. The infrared identification system provides rapid and positive friend or foe identification of land, sea and air vehicles at long ranges without being jammed, intercepted or mimicked.

Abstract: The invention is a low shock detachment device that includes an expandable latch with a plurality of fingers. The anterior surface of each finger has a stud-mating mechanism. A mechanism for repositioning each finger from a closed position to an open position is provided. A stud with a head and a stem is provided. The stem has a finger-mating mechanism sized and shaped to mate to the stud-mating mechanism on each finger. A first housing sized to slideably receive the stud is also provided. A second housing holds the plurality of fingers. The first and second housings have a mechanism that permits attachment to a structure. The first housing is attached to the second housing when the stud-mating mechanism of each finger interlocks with the finger-mating mechanism of the stud. The repositioning of each finger from the closed position to the open position by an explosive charge separates the housings.

Abstract: A weapon system comprising a firearm having a barrel through which a projectile may be propelled and further comprising a non-lethal means for selectively ejecting a stream of fluid, such as an incapacitant, in a direction substantially parallel to the axis of the barrel and aligned with the sights of the firearm. The system removably houses a fluid containing pressurized canister, the outlet of the canister co-operating with a nozzle for the release of said fluid from said canister under control of a nozzle trigger mechanism. The pressurized canister, nozzle and trigger mechanism may be removably mounted on said firearm.

Abstract: Several ceramic armour systems are provided herein. One such system is a ceramic armour system for personnel. Such system includes an integral ceramic plate, or a plurality of interconnected ceramic components providing an integral plate. The ceramic has a deflecting front surface or a flat front surface, and a rear surface. A front spall layer is bonded to the front surface of the ceramic plate. A shock-absorbing layer is bonded to the rear surface of ceramic plate. A backing is bonded to the exposed face of the shock-absorbing layer. A second such system is a ceramic armour system for vehicles. Such system also includes an integral ceramic plate, or a plurality of interconnected ceramic components providing an integral plate. The ceramic plate has a deflecting front surface or a flat front surface, and a rear surface. A front spall layer is bonded to the front surface of the ceramic plate. A shock-absorbing layer is bonded to the rear surface of the ceramic plate.

Abstract: An airfoil member (14) is provided including a geometric morphing device (18). The geometric morphing device (18) has an inflatable member (30). The inflatable member (30) has an exterior wall (32) and multiple inflated states. A fiber mesh (34) is coupled to at least a portion of the exterior wall (32) and changes in shape according to fiber angle. Shape and size of the geometric morphing device (18) are adjustable by changing inflated state of the inflatable member (30). An airfoil member altering system (12) and a method of performing the same are also provided as well as a method of forming the geometric morphing device (18).

Abstract: A carrier assembly for a gun comprises a gun bolt carrier disposed to reciprocate axially with respect to the central axis of the gun, and a gun bolt disposed to reciprocate axially within the carrier. The gun bolt has a locking groove therein. The assembly also comprises a bolt locking mechanism extending through a portion of the bolt carrier to selectively engage the locking groove and thereby prevent the bolt from moving with respect to the carrier. The assembly further comprises a generally axial groove in a non-reciprocating portion of the gun that engages and selectively rotates the rotatable bolt locking mechanism to selectively lock the bolt to the carrier.

Abstract: An ordnance system of the present invention may include or feature any one or more of: a control unit, one or more effectors (detonators, initiators, shaped charges and the like), and a two-, three- or four-wire communication bus between the control unit and the effectors; an addressable system in which all the effectors can be connected to the same communication bus and the control unit can issue coded signals on the bus addressed to a specific effector; inductive coupling between the effectors and the communication bus; and a multi-voltage level communication system in which communication signals are carried at a first voltage and arming signals are provided at a second, higher voltage. Other features may include two-way communication between effectors and the control unit and the de-centralization of firing control so that the control unit does not have exclusive control over whether the effectors function.

Abstract: The present invention relates to a fin-stabilized artillery shell (1) comprising a body part (8, 26, 36) which can be axially displaced rearwards, in the direction of flight of the shell, once the latter has left the barrel from which it has been fired, and which in the original position is fully retracted in the shell (1), and in which a number of deployable fins (18, 24, 29-30, 42-47) are in turn secured, and from which the fins are automatically deployed as soon as the body part has reached its rear position in which it is locked relative to the rest of the shell. One of the advantages of the invention is that in the flight position it gives the shell a greater length than is permitted by the charging position of the artillery piece launching the shell. This gives the shell considerably better stability in its trajectory towards the target.

Abstract: An aircraft having a propulsive power unit supported in a fuselage mounted configuration and including an engine and a nacelle structure housing the engine. The nacelle structure is provided with upper and lower displaceable nacelle portions, such as thrust reverser cowls and fan cowl doors which are displaceable between closed dispositions which they occupy during operational conditions of the aircraft and open dispositions which they take up to provide access to engine components. The upper and lower nacelle portions are so mounted as to be displaceable to their open and closed dispositions in movements in which one is assisted by gravitational force and the other is displaced against gravitational force. A force transfer mechanism is provided for transfer during opening and closing movements of the nacelle portions of gravitational force assisting displacement of one of the nacelle portions to assist in displacement of the other nacelle portion being displaced against gravitational force.

Abstract: The borehole of many wells, including oil and gas production wells, is frequently cased with a steel or similar metal casing. In order to extract oil or other material existing within the surrounding geologic formation, it is necessary to puncture the casing. Currently, this is accomplished with tubes (guns) containing explosive charges being lowered into the well bore and detonated, causing the tube and well casing to be punctured and the geologic formation shattered. The guns are made from high strength, thick-walled and machined metal. This invention discloses a multi-layered or composite tube that enhances the directional orientation of the explosive charges utilizing less costly and more easily fabricated material. The invention also discloses a gun having properties to allow the desired directionally oriented perforation by the explosive charge without being deformed and jammed within the well casing. Other advantageous are also disclosed.

Abstract: An improved aircraft includes a thrust source, a wing, and a boom functioning as a “free lever” and having a distal end upon which the thrust is acting and a proximal end about which the boom is freely rotatable to balance forces acting on the proximal and distal ends of the boom. The proximal end is pivotably mounted at or below the center of lift of the wing and above the center of mass of the aircraft. The distal end is located above the center of mass of the aircraft, when the lever is in the vertical position to establish a gravity pendulum, and forward of the center of drag of the aircraft, when the lever is in the horizontal position, to establish a drag pendulum. All transition flight is a resolution of the force vectors of the two pendulums. A director adjusts the vertical and horizontal thrust components of the propulsion system.

Abstract: A single-wheel driving mechanism for floor transport vehicles is comprised of a gearing housing with at least one gear stage, a flanged-on drive motor, and a driven running wheel. For obtaining the smallest possible installation space or achieving a simplified installation or removal of the single-wheel driving mechanism, in conjunction with high transmission of force at the same time, the running wheel is directly connected with torsional strength with a gear of the transmission, and the gear of the transmission is rotatably supported on a support element.

Abstract: A system for modifying ice adhesion strength of ice adhered to an object comprises a composite coating containing wire electrodes covering the surface to be protected. In one embodiment, a composite coating contains electrode wires and insulator fibers. The composite coating is applied to the surface of an object on which the ice adhesion strength is to be modified. The electrode wires are connected to a dc bias source, and they function as cathodes and anodes alternately. The source generates a DC bias to an interface between the ice and the surface when the ice completes the circuit between anode and cathode wires. In another embodiment, a wire mesh is disposed on an electrically conductive surface of the object an opposing DC biases are applied to the mesh and the surface. In another embodiment, the coating has anode and cathode wires woven by insulator fibers as a composite cloth applied to the surface to protect the surface from ice.