Abstract: A snap-on coupling for mounting accessories on the end of a cylindrical gun barrel characterized by its ability to be quickly operated. The gun barrel is provided with an annular groove axially spaced from the gun barrel end, and an adapter includes a bore receiving the gun barrel end region and radially displaceable ball detents in the adapter are received within the barrel groove upon radial alignment. A spring biased detent operator collar axially displaceably mounted on the adapter controls the radial position of the ball detents wherein manual axial displacement of the detent operating collar may be accomplished quickly with one hand.

Abstract: A deployment device for stabilizing fins of a projectile includes at least one pallet and a holding device for each fin. The pallet is oriented to receive an aerodynamic flow when the projectile is fired and thus transfers a resultant strain to the fin to deploy it away from the projectile. The deployment device can be used for fins of a projectile fired from smooth barrelled weapons.

Abstract: A radar highway motor vehicle guidance apparatus for guiding a land vehicle along a roadway using a forward looking, lateral position sensing, monopulse tracking radar guidance apparatus which transmits radar pulses forward of the vehicle. The pulses are reflected back to the vehicle by a stripe distributed along the roadway. The stripe is a frequency selective surface which generates retro-reflective grating lobes at an operating frequency of the tracking radar. Operating the radar at two frequencies allows the radar to look at regions spaced at two different distances from the front of the vehicle. Highway related information may be encoded in the frequency selective surface by variations in the shape or dimensions of the frequency selective stripe morphology in order to modulate the reflected signal with highway information which is then also detected at the radar receiver. Target discrimination is enhanced by using pseudo random codes and matching antenna polarization with stripe polarization.

Abstract: A ballistic containment device for use in inspecting, loading and unloading firearms having an outer drum with a rim portion defining an open end, an inner wall surface and a closed end, together forming an outer chamber into which is suspended a semi-rigid kinetic energy absorptive member, which member is constructed from a plurality of layers of fabric woven from long chain synthetic polyamide fibre, which layers are bonded to one another by a non-rigid adhesive material. The kinetic energy absorptive member is suspended into the catchment member, from the rim portion as aforesaid, by means of a support web constructed of a plurality of overlapping straps of fabric woven from long chain synthetic polyamide fibre bonded to the kinetic energy absorptive member by means of the non-rigid adhesive material.

Abstract: A monolithic semiconductor igniter for igniting a charge of explosive material. The igniter includes a semiconductor substrate, and one or more fuse which is diffused in the semiconductor substrate such that the fuse ignites the charge when an electrical current is passed through it. Also provided is a process for manufacturing a monolithic semiconductor igniter. The process includes providing a semiconductor substrate, and diffusing one or more fuses in the semiconductor substrate. An additional embodiment provides an igniter with multiple sawtooth bridge elements. The resistance of this igniter may be adjusted by cutting individual bridge elements.

Abstract: A method and apparatus is for imparting, in a continuous sequence, a predetermined rotational movement to a warhead releasably housed in a protective canister and ejected out in ballistic ejection trajectories from the canister. The canister is spun to the desired rotational speed by flow of combustion gases through gas outlet nozzles discharging in the outer periphery of the canister and supplied from a central combustion chamber in which a propellant powder charge is combusted. The combustion gases are then led from the combustion chamber, in the final phase of the propellant charge combustion, through gas outlets facing towards the warhead and initially covered by the propellant charge and exposed as a result of the combustion, for ejecting the warhead out of the canister.

Abstract: A barrel stabilization unit is provided for stabilizing a barrel and controlling recoil of a rifle or shotgun having a barrel guide means for providing a fulcrum attachment point adjustably along the barrel of a rifle or shotgun, and fillable ballast containment means affixed to said barrel guide means for providing a counter ballast at said fulcrum attachment point, and an attachment means affixed to said fillable ballast containment means for firmly connecting the barrel stabilization unit to a rifle or shotgun.

Abstract: A bulkhead in the form of a rib extending spanwise adjacent the leading edge of the airfoil of a turbine blade of a gas turbine engine serves to stiffen the airfoil to attain protection from impact by foreign objects, but doesn't materially affect cooling effectiveness in the event of a puncture of the skin. Holes extending spanwise in the rib reduce the mass, allow radial flow, and restrict flow into the leading edge. This construct allows a reduction in the thickness of the skin of the airfoil, and hence a weight reduction.

Abstract: A non-lethal weapon for temporarily immobilizing a target subject by means of muscular tetanization in which the tetanization is produced by conducting a precisely-modulated electrical current through the target. Because the electrical current is a close replication of the physiological neuroelectric impulses which control striated muscle tissue, it tetanizes the subject's skeletal muscles without causing any perceptible sensation. The transmission of this current to the distant target is via two channels of electrically conductive air. The conductive channels are created by multi-photon and collisional ionization within the paths of two beams of coherent (laser) or columnated incoherent ultraviolet radiation directed to the target. A single beam may be used to tetanize a grounded target. The high-voltage tetanizing current flows from electrodes at the origin of the beams along the channels of free electrons within them.

Abstract: An ignition tube for use with electrothermal chemical combustion ignition projectiles in guns, comprising a tube positionable in a combustion chamber for receiving plasma ignition from a plasma chamber. The tube is formed from high density polyethylene or other materials adapted to release plasma upon contact by plasma ignition electrical energy or pulses. The tube is specifically designed to provide an increasing exit area from the proximal end of the tube toward the distal so as to act upon the longitudinally attenuated plasma, thereby substantially decreasing the amplitude of any reflected shock in the plasma stream. The exit area comprises a plurality of radially extending orifices or holes that have a decreased angle of inclination to the longitudinal axis from proximal end to distal end, such that the orifices form a spiral pattern on the circumference of the tube. This pattern provides a uniform action of plasma on the propellant over the entire length of the ignition tube.

Abstract: Described is a sensor device (10) for a missile (16) having a matrix detector (12) and an electronic evaluation circuit connected thereto. A ray source (20) is stationarily arranged on the missile (16). Provided between the ray source (20) and the matrix detector (12) which is stationarily provided on the missile (16) is a gyro optical device (22) which is cardanically mounted in the missile (16). The sensor device may be employed to determine the roll position and roll rate of a missile (16).

Abstract: A spin-stabilized projectile for destroying distant targets uses the projectile's spin to carry out other functions such as target imaging, course-correction and warhead aiming. By using the spin to carry out such functions, in addition to stabilization, the projectile can be implemented with fewer or no moving parts. The projectile may utilize either right or skewed-core fusing for the warhead.

Abstract: A method for determining the rates of turn of the missile/target line of sight with a seeker head rigidly mounted on the missile, characterized in that the azimuth and elevation deviation angles (.psi..sub.sm and .THETA..sub.sm) of the target measured with the rigidly mounted seeker head (2) in the missile-fixed coordinate system (s.sub.1, S.sub.2, s.sub.3) are transformed to the azimuth and elevation deviation angles (.psi..sub.v and .THETA..sub.v) of the target based on the coordinate system (v.sub.1, v.sub.2, v.sub.3) of a virtual, gimbal mounted and gyrostabilized seeker head (2v) that tracks the missile/target line of sight (SL) by rotation with the rates of turn (p.sub.v, q.sub.v, r.sub.v) about its three axes (v.sub.1, v.sub.2, v.sub.3).

Abstract: An aerodynamic buffer zone in the gap between the tip of an air cooled axial flow turbine blade of a gas turbine engine and its surrounding shroud or seal (outer air seal) is created by discretely discharging a high velocity stream of cooling air from the tip of the blade in a judicious direction. The stream is angularly oriented relative to the plane of rotation of the turbine so that it is discharged in the gap in the direction of the pressure side of the turbine and preferably at between a 15.degree.-45.degree. angle relative to the flat surface of the tip of the blade.

Abstract: A propulsion system to provide silent firing of a mortar weapon using standard and nonstandard mortar tubes or launch assemblies has been invented. The system utilizes a precision rupture disc mechanism to control combustion and energy release to effect consistent operation. The gases generatedd by combustion of the propellant charge are contained by the rupture disc which insures uniform and efficient propellant combustion. After rupture of the disc at a prescribed pressure, the projectile is accelerated by the expanding gases through the action of a piston on the warhead. The gases are retained within the projectile after accelerating the projectile, preventing release of high pressure gas and resulting in a silent launch condition.In a first embodiment the warhead and piston moves first and then the heavier cylinder is moved. In a second embodiment the cylinder moves with the warhead and picks up the lighter piston.

Abstract: The Nutated Beamrider Guidance Using Laser Designators provides a means of roducing an accurate laser beamrider command guidance link between the launch platform and the missile during its flight through the addition of a simple variable offset nutator mechanism to existing Army laser designators. Such a beamrider guidance enables the missile to determine its position in the guidance field by measuring the angle of arrival of side scatter from the pulsed beam. These measurements result in the production of correctional signals which cause the missile to move closer to the boresight axis for eventual impact on the target.

Abstract: A method for the self-protection of an aircraft or the like against radar-guided missiles and a self-protection device for use in aircraft and the like against radar-guided missiles, which enables in-flight cutting and dispensing of chaff dipoles of a preselected length into the airstream along the flight path of the aircraft. The device comprises a housing enclosing a motor having a flywheel providing a motor inertia that enables the motor to maintain a substantially constant rotational speed when a load is applied, a magnetic clutch, gearing for rotating a platen roller and a cutter roller, as well as means for controlling the operation of the device, and an exit opening with a spoiler for dispensing the cut dipoles into the airstream.

Abstract: The invention relates to a device for self-defense of aircraft against missiles and provides for a combination of a proximity sensor for the enemy missile, an intercepting rocket, and an aimed light beam, with the light beam optionally being used alone as an optical jammer against an optical homing head on the missile, or being used together with the intercepting rocket to steer it optically by either a semi-active or a beam rider steering method.

Abstract: A control fin assembly for a water vehicle includes a multiplicity of fins onnected together and grouped in an array mounted on the vehicle. A portion of the array is of a shape-memory material responsive to heat to assume selected shapes different from the shape of the array portion otherwise. The array portion is electrically conductive and adapted to increase in temperature upon application of electrical current thereto to effect the assumption of the selected shapes.The invention further relates to a control fin for a water vehicle, at least a portion of the fin being of a shape-memory material responsive to heat to assume selected shapes different from the shape of the fin otherwise, the fin portion being electrically conductive and adapted to increase in temperature upon application of electrical current thereto to effect the assumption of the selected shapes.

Abstract: A turbine blade squealer tip has a cooling passage arrangement which includes a peripheral end wall surrounding a central portion of an end cap of the squealer tip, an outer peripheral groove defined in an outer surface of the peripheral end wall being spaced outwardly from the central portion of the end cap, and a multiplicity of holes extending through the end wall from the outer groove to an internal source of cooling air flow within the turbine blade, bypassing the central portion of the end cap of the squealer tip. The outer groove which receives the flow of cooling air from outlets of the holes tends to trap the air therein so as to form an annular air seal about the outer surface of the squealer tip end wall which impedes leakage of hot gas flow past the squealer tip.