Abstract: A casing for a shaped explosive charge wherein an explosives container, a metal cavity liner and a stand-off element are joined together at their peripheral margins. The joint may be a metallurgical joint but may also advantageously be a water-destructible joint, for example, a bolted flanged joint comprising a sea-water-destructible packing element.

Abstract: An ignition device for igniting a rocket motor comprising a striker adapted or displacement by pressure generated by an auxiliary charge, a percussion-operated priming device for impact by the striker, and an ignition charge for ignition by the priming device and for igniting the rocket motor. The striker, in its inoperative position, is mechanically keyed within a hollow container body having an axial bore therethrough by a pair of diametrically opposed circumferential grooves within which an O-ring is retained. For operation, a fluid generates pressure on the striker, thereby dislodging it from its mechanical keying and driving it to impact the percussion-operated priming device.

Abstract: A control system for an internal combustion engine wherein the torque developed by an internal combustion engine is detected to provide optimum control of the ignition timing of the engine and thereby to ensure an improved engine efficiency as well as an improved fuel economy. The system comprises an engine torque detector for detecting the torque developed by the engine, a signal generator for generating signals used to periodically change the ignition timing of the engine, a phase discriminator for discriminating the phase relation between the output signals of the engine torque detector and the periodic change signal generator, and ignition timing control means for controlling the ignition timing in response to the output of the phase discriminator.

Abstract: A hypervelocity projectile is provided with aluminum components, such as s and windshields, which possess a coating having high resistance to thermodynamic ablation on the aluminum components. The coating is formed by first producing a "hard" anodic coating on the aluminum component by anodic oxidation of the aluminum in an acid electrolyte maintained below 10.degree. C, and sealing the hard coating with a hot aqueous solution of an alkali metal silicate of the formula Me.sub.2 O:x.SiO.sub.2, wherein Me is an alkali metal and x is at least about 2.0, e.g., a 5 - 10% aqueous solution of Na.sub.2 O:x.SiO.sub.2, wherein x is about 3.25.

Abstract: Training ammunition for mortars having a projectile disposed in a cartridge case and provided with a propellant charge for being fired from a barrel insert of a dummy shell. An ejector charge is associated with the cartridge case and is provided with an ignition device and is arranged for ejecting the dummy shell together with the cartridge case from the mortar barrel. A flash hole is arranged between the propellant charge and the ejector charge, and an ignition jet conducting tube is disposed coaxially within the ejector charge and extends from the ignition device to the end of the ejector charge facing the flash hole. The ignition jet conducting tube is provided with at least one radial ignition aperture therethrough.

Abstract: This invention is a solid fuel air turbo rocket. A solid propellant charge, hich is richer in fuel than conventional propellant compositions, burns in an initial chamber. The gases so produced pass through turbine blades into a second chamber. The turbine, which is rotated by the gases impinging on and passing through the blades, drives a compressor which compresses air from the atmosphere. This compressed air is fed into the second chamber where the oxygen in the air reacts with the fuel rich gas to produce further combustion and gas expansion. The gasious products so generated pass through a nozzle into the atmosphere, resulting in thrust to the missile. As the missile accelerates a variable area air inlet is reduced to maintain a normal shock at the throat. When ramjet take-over velocities are reached, the turbo-compressor is jettisoned to allow the second chamber to function as a ramjet burner.

Abstract: A missile guidance system in which a projectile or missile is fired toward predetermined target with the missile being tracked on its flight toward the target by radar, processing the radar information in a computer apparatus and finally computing a new trajectory from the missile to the target and transmitting correction signals to a correction device on the missile including thrusters on the missile to cause the trajectory of the missile to be changed to the newly computed trajectory for the missile. This system corrects the trajectory of the missile while in flight by recomputing a trajectory from the missile to the predetermined target and making appropriate corrections each time. Thisenables the missile to only contain radar reflecting means, and correction detection and control means on the missile rather than having gyro and other type devices on board the missile which take up a considerable amount of space and weight.

Abstract: A motion-induced stimuli initiation system for actuating various missile otechnic devices based upon attainment of specified values of acceleration, velocity and distance after launch. Data from accelerometers are integrated to obtain velocity, the velocity data are integrated to obtain distance. Comparison of acceleration, velocity and distance with predetermined values by appropriate logic circuitry provides the signals to initiate the pyrotechnic devices.

Abstract: A magnetic pickup type electrical signal generator is mounted in cooperative relationship with the movable member of each fuel injector of an associated fuel injected-spark ignited internal combustion engine. In response to the initiation of actuation of the movable member to inject fuel into the combustion chamber of the corresponding engine cylinder, the magnetic pickup signal generator produces an output signal to which an associated electronic ignition system is responsive to produce an ignition spark creating potential. Each ignition spark creating potential is directed to the spark plug of the engine cylinder into which fuel is being injected by the actuated fuel injector.

Abstract: An incendiary projectile having a plastic jacket made from glass reinforced Nylon, a mischmetal/aluminum core and a Teflon tip is actuated by kinetic energy on impact with the target. The mischmetal/aluminum core is octagonal in configuration and is composed of a pyrophoric alloy containing 87% mischmetal and 13% aluminum. The Teflon tip provides greatly increased effectiveness against targets of aluminum construction especially those containing aircraft fuel and the like.

Abstract: A reactor core having tandem arranged fuel regions for use in a water moderated nuclear reactor. An upper core region is fueled with enriched uranium oxide; while, a lower core region is fueled with a plutonium oxide. An intermediate core region contains natural uranium oxide.

Abstract: A system for transferring fuel assemblies between a nuclear reactor core and a fuel storage area while the fuel assemblies remain completely submerged in a continuous body of coolant. The system comprises an in-vessel fuel transfer machine located inside the reactor vessel and an ex-vessel fuel transfer machine located in a fuel storage tank. The in-vessel fuel transfer machine comprises two independently rotatable frames with a pivotable fuel transfer apparatus disposed on the lower rotatable frame. The ex-vessel fuel transfer machine comprises one frame with a pivotable fuel transfer apparatus disposed thereon. The pivotable apparatuses are capable of being aligned with each other to transfer a fuel assembly between the reactor vessel and fuel storage tank while the fuel assembly remains completely submerged in a continuous body of coolant.

Abstract: A vehicle driven by a combustible fuel propulsion system, in which the fuel emaining upon arrival at the target is exploded to act as a warhead. The vehicle has a fuel tank incorporated into the structure, which will hold more than enough fuel to complete the mission. The residual fuel is atomized into the vacant space in the fuel tank and mixed with air or oxygen, which can be used as the driving agent for the atomization. The fuel/air mixture is then detonated. The fuel tank may be thin walled for maximum blast effect, or be of heavier structure which is grooved for fragmentation.

Abstract: In a lighting fixture, glare-free uniform illumination is achieved by means of a plurality of nested generally frusto-conical reflectors surrounding the light source of the fixture. The reflectors are shaped and positioned relative to one another and to the light source to concentrate light in the range of 65 to 71 degrees from downward vertical and to cause the intensity of the light to progressively decrease as the angle from downward vertical decreases from 65 degrees toward zero. The projected light from the fixture is concentrated in the 65 to 71 degree range from downward vertical in part by light radiated from the source at near horizontal and higher angles being doubly reflected between the frusto-conical reflectors and then projected in the high angle range. The reflectors are positioned relative to one another, to the light source and to baffles, to cut off any light from being projected at an angle from downward vertical greater than 75 degrees.

Abstract: A propellant charge is assembled by stacking together a plurality of extrd longitudinally grooved polygonally shaped high packing density propellant grains. An hexagonal configuration provides for nearly full utilization of the circular volume of a propellant chamber. Selective location of a plurality of perforations and grooves through each grain member is used to provide propellant charge assemblies having uniform web distribution and improved burn characteristics.

Abstract: This invention relates to a method of fabricating and assembling the electrodes of an electron discharge device and includes in one illustrative embodiment the steps of processing within a first evacuated chamber an electrode such as a photocathode element, processing within a second evacuated chamber another portion(s) or electrode(s) of the device, assembling the first and second chambers together, evacuating the space therebetween, and assembling the photocathode element with another portion of the device. This assembling process is dependent upon providing an appropriate vacuum tight seal for both the first and second chambers which will withstand the processing temperatures and the vacuum established within the chambers, and which may be easily penetrated to bring the photocathode element and the portion of the electron discharge device together.

Abstract: A spin stabilized projectile containing an annulus of incendiary liquid sounding a burster tube, in which the liquid is compartmentalized to minimize rotational spin loss of the projectile due to centrifugal force effect on or anti-spin inertia by the liquid.

Abstract: A variable burn rate/variable burn time parachute flare, adapted to be trported by a gun cannon or howitzer to a desired height and then ignited to burn at an intensity of 1.6 to 1.8 .times. 10.sup.6 candlepower for 25 to 35 seconds, followed by a second burn at about 0.8 .times. 10.sup.6 candlepower for 75 to 35 seconds and comprising a flare case having a hollow cylindrical wall about 4.5 inches in diameter and about 7 inches long, closed at one-end and open at the other end, and a 0.03 inch coating of polyester or epoxy resin on the closed end and on one-third to two-thirds of the inner wall thereof adjacent to the closed end.

Abstract: A fuze is disclosed for use on projectiles fired generally at high speed. A unique delay arming mechanism is incorporated which utilizes pressure build-up within the fuze to control the period of delay in arming the fuze. The delay mechanism is unique in that fuzes incorporating the invention can be used interchangeably on either fin or spin stabilized projectiles.

Abstract: A mobile missile system that is automatic in operation and that is designed to simultaneously defend against a multiplicity of air born targets as well as moving ground targets by using a time-sharing radar installation that performs the functions of acquisition, tracking and discrimination of the targets, simultaneous tracking of discrete units of the targets, transmission of command signals to the launchers for launching the missiles, and command control of the missiles after the launch, all on the same time-sharing basis.