Abstract: Inhibited Red Fuming Nitric Acid (IRFNA) type IIIB and monomethyl hydrazine (MMH) ignite when contacted with each other because of a hypergolic chemical reaction and are the preferred oxidizer and fuel for bipropellant rocket propulsion systems. These propellants can deliver a specific impulse of 284 lbf sec/Ibm and density impulse of 13.36 lbf sec/cubic inch when the engine operating pressure is 2000 psi. Special precautions must be used when handling because of its toxic properties. A fuel gel propellant fuel that would be a suitable replacement for MMH must be less toxic and have a competitive density impulse for the same engine operating conditions. Three compounds meeting the specified requirements have been synthesized and their physical and ballistic properties are evaluated herein as shown in Table 1. The chemical names for these compounds are dimethylaminoethylazide (DMAZ), pyrollidinylethylazide (PYAZ), and bis (ethyl azide)methylamine (BAZ).

Abstract: Sticky high water content gelled fire extinguisher compositions hold the antage of providing a high water content, slightly viscous (sticky) gel with flow properties similar to water. The ability of this material to stick to burning surfaces is what sets it apart from water extinguishers. Not only are fires extinguished, but also surfaces are cooled by the sticky gel as the water evaporates. The basic gelled fire extinguisher composition is comprised of about 88 weight percent water and about 12 weight percent of a 7 nanometer particle size silicon dioxide gellant. The silicon dioxide gellant is available as EH5 tradename by Cabot for this silicon dioxide gellant. Other ingredients such as dispersants, wetting agents and flame retardants can be used as additives in combination with the gelling agent. The actual gel system is inexpensive, made from readily available ingredients and easily prepared.

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 fly over homing guidance system for terminal homing missile guidance is fire and forget missile guidance method wherein on board target sensing tracks the target and guides the missile to the target, but instead of being guided to a direct impact as is conventionally done, the missile is guided toward a precise distance over the top of the target, intentionally avoiding impact. A second sensor on the missile detects the leading edge of the target, such as the turret of a tank. The warhead is then fired down onto the top of the target as the missile is guided or directed over it. Further, the shot line of the warhead is substantially perpendicular to the top of the target, maximizing lethality. This allows the use of the same angle of attack and warhead for all modes of target engagement and thus maintains high lethality for every firing scenario.

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: Tracking means for establishing a line-of-sight between a control point to which the second craft is being guided and tracking the line-of-sight to follow the second craft and deriving a signal .sub.a representing the rate of rotation of the line-of-sight about the control point; monitoring means for deriving a signal representing the displacement e of the first craft from the line-of-sight, a signal representing the range R.sub.m between the first craft and the control point, and a signal representing the rate of change R.sub.m of the range R.sub.m, presetting means for providing a signal representing a positive quantity k; and a computer for deriving signals representing .sub.c, .sub.c, and k to satisfy the equation ##EQU1## and minimize the difference -.sub.a, k being initially set equal to k.sub.1 ; control means for deriving from the representations provided by the computer a signal representing f(e)+R.sub.m .sub.c +2R.sub.m .sub.

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: Tracking means for establishing a line-of-sight between a control point towards which the second craft is being guided and tracking the line-of-sight to follow the second craft and deriving a signal .theta..sub.a representing the rate of rotation of the line-of-sight about the control point; monitoring means for deriving a signal e representing the displacement of the first craft from the line-of-sight, a signal representing the range R.sub.m from the control point to the first craft and a signal representing the rate of of change R.sub.m of the range R.sub.m ; ranging means for deriving a signal representing the range R.sub.t from the control point to the second craft and a signal representing the rate of change R.sub.t of the range R.sub.t ; a computer for deriving representations of .theta..sub.c, .theta..sub.c and .theta..sub.c which satisfy the equation.sub.c =-2.theta..sub.c.sup.3 -3.theta..sub.c (R.sub.t /R.sub.t)where the difference .theta..sub.c -.theta..sub.

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: A substantially cylindrical symmetrically wound coil for a fiber optic rotation sensor, having a flat cylindrical disc, with a central aperture, disposed in the center of the coil. A continuous optical fiber of substantially uniform cross section having two substantially symmetrical segments extends through the aperture. A spirally wound first fake of a first segment of the fiber is disposed on one side of the disc in a helical spiral extending from the inner diameter of the aperture of the disc to its outer circumference in closely spaced spiral loops. A spirally wound first fake of a second segment of the fiber is disposed on the other side of the disc in a helical spiral extending from the inner diameter of the disc to its outer circumference in closely spaced spiral loops. A first connecting portion of the first segment of the fiber extends from the outer circumference of the one side of the disc across the outer circumference of the disc and the first fake of the second segment of the fiber.

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: An optical switch in a one-dimensional multilayer dielectric stack having a photonic band gap, composed of at least two groups of layers of dielectric material whose operating wavelength is near the edge of said photonic band gap. At least one layer of each of the groups is composed of a nonlinear c.sub.3 dielectric material, which creates an intensity-dependent shift in the location of the band gap and produces a dynamical change in the transmissive and reflective properties of the multilayer dielectric stack in response to changes in the intensity of light or the transmittance of electromagnetic radiation passing through the multilayer dielectric stack. The width of the photonic band gap is determined by the differences between the refractive indices of the nonlinear dielectric material and that of the other layers of dielectric material in the multilayer dielectric stack.

Abstract: An automatic landing system for guiding an unmanned aerial vehicle along a predetermined path to a predetermined point on the ground. The system includes an image processing means resident in the motion compensation processor that computes aerial vehicle parameters. The computed parameters are altitude, changes in altitude, changes in pitch and yaw angles, roll angle and changes thereto, and changes in cross range and down range position. These computations are based on the movement of elements in the video of an imaging sensor onboard the aerial vehicle. The motion compensation processor also measures the distance (in pixels or picture elements) between two beacons placed a known distance apart on either side of the apparent touchdown point. A recovery control processor uses these parameters to compute both desired and actual altitude as a function of range from the vehicle to the apparent point of touchdown and to provide offset error in azimuth from the desired flight path to the landing area.

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.