Abstract: The fastening together of structural elements formed from carbon-carbon is accomplished by a fastener constructed from 2-D or 3-D carbon-carbon in the form of a high angle helical threads on one end and a countersunk head with a carbon-carbon central insert on the other end with the threaded end inserted through the carbon-carbon structural elements to be joined. A metal is painted on the threads and the shank on the fastener. A collar formed from carbon-carbon is fitted over the course threaded end of the fastener with the distal end of the threads extending therefrom. While passing a heating current through the fastener, the head and the collar of the fastener are forced together. The fastener is heated to an elevated temperature in the presence of an Oxygen gas cover which causes the powered metal to expand up to 100% binding the fastener to the carbon-carbon components, collar and insert.

Abstract: A holographic device and method encrypts a time dependent data signal, s(t), by a complex time dependent phase shifting signal. This produces a new signal whose modulus is equal the absolute value of the data signal, s(t), but has widely spread the frequency of the data signal. This new complex signal is mathematically transformed, producing an amplitude and phase spectrum (or a real and imaginary transform spectrum) of signal components. The amplitude and phase signals are modulated into a radio frequency carrier (or some other radiating source) as quadrature components and transmitted. At the receiver, the quadrature signals are separated into an amplitude and phase components which are then mathematically inverse transformed. The result is a complex signal with a real and imaginary components. The resulting signal is an accurate representation of the original data signal if a complete signal is recovered.

Abstract: A lateral thruster for missiles is provided which comprises two or more individually rotatable thruster motors with integral nozzles. If the thrusters are located at or near the center of gravity of the missile, the missile can be maneuvered while it remains pointed at the target. Locating the thrusters forward or aft of the missile center of gravity enables steering forces as well as lateral translational and roll forces to be provided. The thruster motors need not be disposed in pairs. The use of integral nozzles obviates sealing problems and allows mountings that permit rapid rotation of the thruster motors to improve missile response time. The lateral thruster disclosed is effective at nearly all aerodynamic angles of attack, missile velocities, and altitudes. The thruster as a unit is enclosed by a shroud that blends into the missile body contour. Possible propellants for the thruster motors include solid propellants and compressed gases.

Abstract: An electronic digital system for performing discrete Fourier transforms in real time. Read only memory (ROM) modules are used as look-up tables for providing inputs for multiplier stages corresponding to sequences of sample signals as well as for logic and other input converting elements of the system. Two such systems are coupled together so that their real and imaginary output signal components may be additively and subtractively combined. The entire transform output is available one cycle period after the last sample input.

Abstract: A rocket propelled missile assembly comprises an outer casing defining an internal solid rocket propellant chamber, the casing having an opening at its forward end aligned with an internal tube submerged in the rocket propellant chamber, and at least one exhaust nozzle at its rear end for venting exhaust gases from the propellant chamber. Solid propellant is contained within the propellant chamber surrounding the internal tube, and a separate terminal stage missile is partially or fully submerged in the tube with the capacity to separate from the tube forwardly through the front end of the casing. The missile separates from the remainder of the system on booster burn out.

Abstract: The invention is directed to targets for use where precise alignment and location measurements on an object is required. Several embodiments of the invention are described. The targets have at least a portion of their outer surface curvilinear. The target is supported on a convex supporting surface on a support body. Various configured single targets and multiple targets are described for use on flat as well as curved surfaces. Some of the targets have either non-reflective or reflective target surfaces. The various embodiments of the ball targets are used in conjunction with either optical or laser theodolites or the like to preform the required location measurements.

Abstract: A method and device for protecting a first stage liquid rocket booster from impact damage and environmental damage so as to permit recovery from a sea water landing and reuse without major rehaul of the rocket engine of the booster. A cylindrical double walled structural member encircles the nozzles of the rocket engine and precludes impact damage after the booster has landed nose first in the water. A flexible water impervious sleeve means is carried within the double walled structural member and deployed prior to impact. The sleeve extends from the booster and collapses inwardly upon itself to prevent entry of sea water into the rocket engine and associated equipment.

Abstract: An antenna system having first and second arrays of radiating members, first and second sets of corresponding bifurcated members and two pairs of feed members. The radiating members of the first and second arrays each have a near end and a far end and a linear portion therebetween with radiating slots formed therein. The linear portions of the radiating members are interleaved in a planar spaced parallel relationship. Each bifurcated member has a unitary portion and a bifurcated portion with the bifurcated portion having a pair of coupling ends. Each bifurcated member is coupled at its unitary portion to the near end of a different radiating member of its corresponding array and also coupled at its coupling ends to a different feed member of its corresponding pair of feed members. The antenna system further includes a monopulse comparator coupled to the input ends of the first and second pairs of feed members for operation as an amplitude comparison monopulse antenna.

Abstract: A pulsed transformer having a superconducting primary winding and a normal conducting secondary winding. The secondary winding is connected across a load. One side of the secondary winding has a switch in series to the load. A high energy storage inductor is connected in parallel across the switch. With the switch closed and the primary winding and storage inductor charged to their maximum capacity, a high level of current now flows through the switch. The primary is then caused to go into its normal conducting mode collapsing the primary field which induces current into the secondary winding. As the secondary winding current increases the high level of current normally flowing through the switch decreases to substantially zero. When the switch current reaches substantially zero, the switch can be opened without damage thereto releasing the high energy from the storage inductor into the load. The switch primary winding can be constructed from a high temperature superconductor for improved performance.

Abstract: A modular segment that is adapted to receive heat generating electronic assemblies therewithin. The modular segments may be joined together to form a housing and the electronic assemblies are electrically interconnected through a hollow channel provided in the joined modular segments. The segments are configured with fins and ribs that form air channels on all vertical outer surfaces of the segments to promote cooling by convective air flow through the channels and between the segments. Segments may be added to form a housing with expanded capacity.

Abstract: Self-dissipating projectiles for use in anti-satellite weapons or warheads are made from suitable solid materials capable of sublimation after relatively short periods of time at the low pressures found in outer space. The material is suitably a volatile organic compound such as naphthalene, paradibromobenzene, benzoic acid, or similar compounds which change directly from the solid to the gaseous phase without becoming liquid.

Abstract: A portable target locator system capable of being transported and utilized by an individual combatant is disclosed. The portable target locator system comprises a rifle-like target locator and a transmitter/modem capable of transmitting target location coordinates to a weapons delivery system. The rifle-target locator preferably includes a Global Positioning System (GPS) receiver capable of determining the location coordinates of the target locator automatically and with a high degree of accuracy from signals transmitted from a network of orbiting satellites. A laser rangefinder and digital azimuth and inclination sensor are then utilized to accurately determine the range, azimuth and inclination of an identified target from the target locator. This information is then processed in conjunction with the location coordinates of the target locator to generate location coordinates for the selected target.

Abstract: The disclosure is directed to a distance measurement system for monitoring changes in distances between a source of illumination and a reflective surface. A white light source is directed into a transmit fiber optic element which terminates at a graded index lens (grin) which collimates the light. The light output from the grin lens passes through a single grating or a plurality of different gratings which dispose the white light into a spectrum which is directed to the reflective surface spaced therefrom at an unknown distance. The dispersed light bouncing off the reflective surface enters a receiver fiber optic device connected to a detection system for determining the spaced distance between the grating or gratings and the reflective surface.

Abstract: An expandable telescoped airframe for a missile provides a shorter configuration for convenience in handling and a longer configuration to provide added predetermined clearance in front of a shaped charge warhead after launch. The airframe is mechanically locked into its extended configuration upon deployment of its expansion feature by means of a wedge brake collar. Possible deployment means include gas pressure, one or more springs, and a drogue parachute. Tail and other control surfaces spring open after clearing the airframe tube to provide aerodynamic stability.

Abstract: A rail gun utilizing a combination of chemical energy for propelling a piston and a projectile. The piston movement creates electromagnetic energy in rails which further increases the velocity of the projectile as it leaves the gun barrel. In operation, propellants are introduced into the gun and ignited. High pressure gas produced from the combustion accelerates the piston and the projectile along the rails. An external field normal to the piston is applied from a dipole magnet wound around the gun bore. The piston movement induces emf thus charging the rails which act as an inductor. The current flowing in the rails further increases the velocity of the projectile along the barrel to its final exit velocity.

Abstract: A laser fabricated from a substrate having top and bottom surfaces. A first stack of mirror layers of alternating different refractive indices are formed upon the substrate top surface. An active layer defining a mesa is formed on top of the first stack of mirror layers. A second stack of alternating different refractive indices mirror layers are formed upon the active layer mesa. A current confinement layer is formed about the side of the active laser mesa. A first contact is formed upon the substrate bottom surface while a second contact is formed upon a portion of said active layer remote from the active layer mesa.

Abstract: A process is described for enhancing superconductor characteristics by application of strong magnetic and/or electric fields to the constituent component materials from which ceramic superconductors are being formed and during the time that these superconductors are being synthesized. This process has particular applicability to the production of superconducting oxide ceramics such as the cuprates. The required magnetic fields are on the order of 1-10 tesla and the required electric fields are on the order of 0.1-1 MV/cm. The fields act as ordering mechanisms and induce grain orientation. The magnetic field aligns the magnetic moment of the grains. The electric field induces electric polarization in the grains and then aligns them. The superconducting structure formation occurs during the sintering, cooling and annealing phases of the fabrication process. Superconductivity is strongly affected by the oxygen stoichiometry in the lattice elemental cell. Applied electric fields cause elongation of the unit cell.

Abstract: A system and process, including a combination of a solder well and a vacuum system wherein micro through holes are filled with solder. A PC board or the like is supported for contact with solder on one side and with a vacuum apparatus for the application of a vacuum to the other side so that solder is drawn into the through holes for establishing electrically conductive connections therethrough.

Abstract: An apparatus for seating and tightening clamps around joints between tubular sections comprises an elongate flexible member such as a chain for extending around a clamp positioned over a joint, the member having rollers spaced along its length, and a tightening device for applying tension to the member to tighten it around the clamp so that the rollers roll around the surface of the clamp and apply a radial force to the clamp.

Abstract: A missile canister hatch cover is provided which deflects the rocket exhaust from an adjacent uptake channel away from a missile as it leaves the canister. After diverting the uptake exhaust flow away from the missile, the hatch cover is returned to its closed position by the missile rocket exhaust as the missile nozzle clears the canister opening. Overall wear and tear on the launching system from the rocket exhaust is reduced and the uptake flow plume is stopped from expanding above the launcher. During missile launch the hatch cover is unlatched and spring loading opens it more than 90.degree. to a locked position where it interferes with the exhaust flowing from the uptake. The interference deflects the uptake flow away from the missile during flyout to avoid the heating, side thrusts, and contamination associated with the uptake exhaust flow field.