Abstract: The purpose of a system for measuring the location and orientation of an ect is to align one object with another by simultaneously measuring the six degrees of freedom of the objects. The system accomplishes the purpose by employing a linear optical detector array sensor on the first object and a pre-selected target pattern on a second object to measure the six degrees of freedom and converting them to six position measurement via a microprocessor which has suitable algorithms residing in it. The six position measurements (azimuth, elevation, range, pitch, yaw and roll) are displayed for viewing by the operator who, then, manipulates the objects until pre-determined desired values of the six position measurements are obtained, indicating a complete alignment between the objects.

Abstract: The device and method for performing an optical Hall test provide means for on-destructive measurement of free carrier concentration or effective mass in semiconductor materials using Faraday rotation spectra. A beam emitted by a Fourier transform infrared (FTIR) spectrometer is transmitted through the sample that is mounted between a polarizer and analyzer and the opposite poles of a magnet before finally being incident on a detector. The ratio of the samples's transmission spectrum with the magnetic field on to that with the magnetic field off is converted, through a suitable mathematical formula, to Faraday rotation. The rotation is, then, plotted versus the square of the wavelength. The slope of the graph at longer wavelengths is directly proportional to the carrier concentration and the effective mass. With one known, the other can be easily determined.

Abstract: A pair of matched filters describing a pre-selected category of objects is ade, each of the filters having a center located at a unique place in the filter. When incorporated into a MACE filter and used in an optical correlator, a line drawn through the correlation peaks caused by the centers of the matched filter pair and a pre-selected axis together produce an angle that is indigenous to that particular category of objects, thus identifying the category of objects.

Abstract: The retro-encoded guidance system guides a flying object in its flight tod its destination by measuring and correcting the angular displacement of its actual trajectory from the straight line-of-sight to the destination. A beam of infrared light emanating from a beacon on the flying object is received and angularly encoded by retro-encoder located at the launcher prior to being returned to the missile. The incident beam and returned beam travel on optical paths that are parallel to each other but opposite in direction. The angular encoding is achieved by a reticle of the retro-encoder imparting frequency modulation to the incident beam, the degree and phase of the modulation depending on the location on the reticle on which the beam is incident.

Abstract: The cool insulator incorporates a water gel coolant and poly-p-ethylene tphthalamide fibers (Kevlar) in an elastomeric rubber binder selected from the group consisting of silicon rubber, ethylene-propylene-diene-monomer, polybutadiene, and polyisoprene. The fiber provides erosion resistance required for long motor burning periods. This insulation includes a submicroscopic particulate water source with high temperature water release properties. The submicroscopic particulate water source is in the form of a flowable solid when formulated and in a weight percent amount from about 10 to about 20. The preferred water source is submicroscopic particulate silica containing over 11.times.10.sup.15 particles per gram and has a surface area of about 200 square meters per gram. The submicroscopic particulate silica is known as "dry water" and specifically described by its method of preparation in commonly assigned U.S. Pat. No. 4,008,170.

Abstract: To remove excess heat from the fin of a flying object that is driven by a opulsion means, heat pipe principle is integrated into the structure of the fin. The heat from hot exhaust gases that flow over the evaporator section of the fin is absorbed by a working fluid within the fin, such as water, which then vaporizes. The resulting vapors flow to the condenser section of the fin where it releases the heat to the ambient air that flows over the condenser section. As heat escapes into the ambient air, the vapors condense, becoming a liquid again. The liquid travels back to the evaporator section where the heat absorption/vaporization process is repeated.

Abstract: The wing deployment device is a simple mechanical device that resides in hollow of the wing and combines a primary and a secondary rotational motions to translate the wing from its stored position to its deployed position. The primary rotational motion occurs when the initial restraint holding the wing to the missile body is severed and the wing, under the influence of the spring component of the device, rotates to a position normal to the missile body axis. After the lapse of a pre-determined duration of time, the secondary rotational motion is started when the tensile force of the spring is transfered to the swivel component via the kevlar rope coupled between the spring and the swivel. As the kevlar rope that is wrapped around the cylindrical shaft component unwinds, the swivel rotates and transmits the rotational motion to the base component which is rigidly coupled to the wing and, in turn, imparts the motion to the wing, thereby engaging the wing in the secondary rotational motion to be deployed.

Abstract: The invented methods provide a means for reducing or eliminating manual astments that are required during the fabrication (winding) of fiber optic dispensers. This reduction is accomplished through the use of a fiber placement pattern that is permanently generated on the bobbin winding surface. Filaments, such as optical fibers, are precisely guided during the winding of subsequent filament layers by the embedded crossover pattern baselayer. The embedded crossover pattern baselayer is generated by first winding in a given direction a wire of a pre-selected diameter upon the polymer coating on the bobbin surface. The polymer is allowed to cure partially before the wire is unwound and removed. Afterwards a pre-selected optical fiber is wound in the direction opposite that of the wire winding direction thereby creating crossover patterns which are, then, manually adjusted to be in desired locations on the bobbin axis.

Abstract: The spinning mine has all of its projectiles concentrated in one small ar It is launched from a spring-loaded threaded screw launcher and acquires angular momentum as it ascends into the air from the launcher to a pre-determined detonation altitude. As the mine spins, the detector assembly on board detects the presence and location of potential targets and sends appropriate indicative signals to a microprocessor, also on board. The microprocessor determines therefrom the location of the largest target or the largest cluster of targets in the environment and triggers the detonation of the mine such that the projectiles are jettisoned in a conical pattern toward the largest target or the largest cluster of targets for a more efficient destruction of the targets.

Abstract: Tungsten is added to fuel gels to increase the density specific impulse. l gels contain monomethylhydrazine or other hypergolic liquids well known in the art. The quantity of tungsten employed can vary from 10%-98% weight percent depending on the specific application. The important parameters to consider during formulation are particle size, concentration, combustion efficiency, physical properties, and plume signature. Tungsten particle sizes ranging from 10 microns to 0.5 micron were compared with carbon of 0.24 when burned in air. It is shown that tungsten burns as well as or better than carbon; however, the increased density specific impulse achieved with tungsten as compared with carbon verifies that tungsten as a high energy additive to hypergolic fuel gels is superior.

Abstract: An Identification-Friend-or-Foe System Using Variable Codes (IFF System) lizes variable codes and pre-selected encryption/decryption technology to querry potential targets as to their battlefield affiliation and also to identify itself as a friend to a potential attacker. The IFF System performs a querry by sending a narrow laser beam to the potential target which is accompanied or closely followed by a radio frequency (RF) wave modulated with encrypted identification information. If the potential target is also equipped with the IFF System and in possession of the valid code, then the received RF wave can be decrypted to reveal the potential attacker as a friend. The potential target, then, encrypts its own identification information using the same code and transmits it via RF wave to the potential attacker. Thus fratricides may be avoided.

Abstract: The Automated Minimum Resolvable Temperature Difference Tester employs the se of tracker based algorithms and automated collection techniques to measure the system's Minimum Resolvable Temperature Difference at various spatial frequencies. The system employs a tracker-type system to resolve bar targets. The system in use provides a means for heating or cooling the target such that a temperature difference between the target and the background is apparent. The temperature difference is then decreased until the algorithm can no longer resolve the target. The candidate tracker system also utilizes a correlation tracking scheme. Changes in spatial frequencies (target sizes) and target temperatures along with data collection techniques is automated to expedite the process while establishing a method for achieving the required measurement which defines the range at which a given task can be accomplished.

Abstract: A gun launched rocket motor is provided with a filler material to fill all f the free volume in the rocket with a void-free incompressible "filler". The described filler material is selected from a solid, semi-solid, or liquid having many properties closely comparable to the rocket propellant, especially match the density, chemical compatibility, coefficient of thermal expansion, and thermal stability. The filler material functions to provide the required physical support to various propellants to survive gun launch. A preferred filler material is a completely fluorinated organic material which is a liquid which is compatible with various solid rocket propellants and can readily be ejected from the chamber by pressurization from conventional igniters or combustible cords such as Rapid Deflagrating Cord, RDC. These completely fluorinated perfluoro compounds, which are designated as C5-18 compounds, are marketed as Fluorinert Brand Electronic Liquids by 3M Corporation, St. Paul, Minn.

Abstract: Reduction of the surface friction of a cured elastomer, sealant or adhesive s accomplished through the use of a dry lubricant such as hexagonal boron nitride powder either as an additive to the uncured polymer mix or applied to the uncured polymer surface prior to effecting a cure.

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: The pulse-coupled automatic recognition system processes information utilizing parallel neural network and transmits information to and from the processing sites as time signals which encode in their pulse phase structure the geometrical content of the spatial distributions of light. A locating device then measures the coordinates of the spatial distributions (pulsating segment) and displays the coordinates of the pulsating segment on a screen for observation. The pulsating segment indicates the presence and location of the component of the input scene that corresponds to the segment.

Abstract: The off-axis joint transform correlator improves on the extant on-axis jo transform correlator by eliminating the requirement for a second laser frequency and the means for blocking the first laser frequency from propagating beyond a given point in the correlator. These eliminations are accomplished by using a beamsplitter and a mirror to bring a second portion of the first frequency at an angle to read the pattern information written onto a spatial light modulator by the first portion.

Abstract: Current state-of-the art injection methodologies for bipropellant engines ly on either impingement or turbulence to mix the fuel and oxidizer streams. The multiple impinging stream vortex injector combines both mixing schemes into a single injector. Both first stage mixing at point of impingement and second stage mixing or turbulent vortex mixing is accomplished by impinging momentum balanced, tangentially injected propellant streams onto one another. The impingement angles are calculated to yield a resultant stream vector that consists of only a tangential velocity component. The two stages of mixing results in increased engine performance and combustion efficiency.

Abstract: A hypergolic fuel formulation which is consistently hypergolic with inhibd red fuming nitric acid is comprised of diethylethanolamine from about 44-72 weight percent, triethylamine from about 11-18 weight percent, and carbon from about 45-10 weight percent The formulation can be gelled with: silica, clays, carbons, or swellable polymers. The gellants can be combined with chemical agents that stabilize the gel under the standard 30 minute, 500 g centrifuge stability test. A preferred combination comprising diethylethanolamine in an amount of about 44 weight percent, triethylamine in an amount of about 11 weight percent, and carbon in an amount of about 45 weight percent when tested at an oxidizer/fuel ratio of about 4.25 reveals theoretical performance values of specific impulse (ISP) of about 250 at a chamber pressure of 1000 Psi and a density specific impulse (D* ISP) of about 350.

Abstract: The disclosed innovative, interceptor seeker discriminator system has the capability to home in on targets containing nuclear materials by detecting the gamma fissions. The gamma signatures can be obtained from activating the nuclear material by a Neutral Particle Beam Weapon, or by detecting the natural fission emissions of the warhead. This system is innovative, in that the following properties are identified: 1) This system uses interactive discrimination techniques, which allows the gamma seeker to accurately home in on a true RV by comparing the return gamma emissions of objects. In this manner, the gamma seeker discriminator is expected to obtain substantially better discrimination K factor performance, when compared to using only IR techniques. 2) This system uses an interceptor/seeker to perform interactive discrimination and gamma sensors in conjunction with infrared sensors on the same interceptor platform (i.e., sensor fusion).