Abstract: An air vehicle control system utilizing variable incidence aerodynamic control surfaces deployed from within the missile body and locked in place. Only two control surfaces (instead of the four usually required for a missile which maneuvers in three dimensions) are required. The number of control surfaces required is reduced by utilizing missile roll to achieve control in any direction. Flight control of the air vehicle is achieved by a single pair of aerodynamic control surfaces located forward of the missile center of gravity. In order to produce a turning moment in any direction, the missile is rolled at a predetermined number of revolutions per second. The control surfaces are operated during the proper portion of each missile revolution to achieve the desired directional control.

Abstract: A missile and launcher system that shields a missile from external electromagnetic radiation. Shielding is accomplished by separating the shielding system of the missile from the shielding system of its launcher system. Unique and separate shielding of the missile is accomplished by utilizing the missile launching enclosure. External signal isolation is accomplished by providing insulation on the interface cable between the missile and the launcher system to attenuate high frequency electromagnetic radiation signals. The present invention is implemented using an unconventional combination of technologies that includes the use of composite materials, vapor deposited conductive coatings, high frequency dielectric insulation filtering, and high frequency coupling of the radiation on the surface of the enclosure and the launcher system.

Abstract: A guidance system for directing a vehicle toward a target which includes a measurement processing section, a target state estimator, and a command processing section. The measurement processing section determines the inertial orientation and length of a line-of-sight vector which conceptually connects the vehicle with the target from measurements taken by a plurality of sensors. The target state estimator provides an estimation of the speed and angular aspect of the target relative to line-of-sight vector, by relating the vehicle and the target to each other through a mechanical conceptualization. This mechanical conceptualization treats the line-of-sight as a collapsible rod which is connected at one end through a mechanical gimbal set, and connected at the other end through a universal joint with four degrees of freedom. The command processing section generates command signals for the autopilot of the vehicle.

Abstract: The improved diamond composite (10) exhibits increased oxidation resistance at elevated temperatures, as well as anti-reflective properties. The composite (10) includes a diamond (12), the surfaces (14) of which are protected by an adherent coating (16) consisting essentially of a layer (18) of hafnium carbide adhering and chemically bonded to the diamond (12), a layer (20) of hafnium oxy-carbide adhering and chemically bonded to the hafnium carbide layer (18) and an oxidation-resistant layer (22) of hafnium oxide adhering and chemically bonded to the hafnium oxy-carbide layer (20). Preferably, the coating (16) is sufficiently thin so that it or at least the hafnium oxide layer (22) thereof has about one-quarterwavelength thickness.

Abstract: Apparatus for reducing the pressure and thermal impingement effects of a supersonic exhaust gas plume emanating from a rocket motor nozzle. A pair of wedge-shaped pieces comprise a disrupter positioned on opposite sides of the central longitudinal axis of the rocket exhaust plume in order to disrupt and disperse the plume concentration. The positioning of these pieces is such that at least a portion of the exhaust gas plume may pass between them. The disrupter defines a flow area normal to the central axis of the exhaust flow which is less than the cross sectional area of the exhaust plume at the position of the disrupter pieces. The reduced flow area causes the exhaust flow to undergo a normal shock wave adjacent the position of the disrupter device before the exhaust gases pass between the disrupter body pieces at subsonic velocity.

Abstract: A low phase noise oscillator 10 having a balanced feedback transformer 24 and a push-pull resonant circuit 12 for generating an oscillation excitation signal. The resonant circuit 12 is loaded by an output buffer 20 connected between first and second feedback terminals 16 and 18. The feedback transformer 24 provides first and second feedback paths of opposite phase polarity which link the resonant circuit 12 with the first and second feedback terminals 16 and 18.

Abstract: An electro-thermal gatling gun (12) includes a plurality of gun barrels (46) and a gun rotor (10) defining a plurality of channels (30). Each channel (30) guides a breechblock (32) between a rear position (50) and a breech position (52). Each said guide channel (30) is aligned with and rotatably fixed to one of the plurality of gun barrels (46). A cam guide (49) moves the breechblocks (32) reciprocally and in series from the rear position (50) to the breech position (52) as the gun rotor (10) rotates. An electro-thermal round (60) includes a projectile (62) and a casing (64) and is electrically connected to one of the breechblocks (32) when the breechblock (32) is in the breech position (52).

Abstract: A radar system with a main antenna that is rotatably supported to permit use in searching about a search axis includes an auxiliary antenna that is rotatably supported to permit use in complementing main antenna coverage. Rotational components and control circuitry are provided, both for simultaneously rotating the antennae with the auxiliary antenna poised in position relative to the main antenna to stop and face a direction just searched, and for separately stopping the auxiliary antenna in position to face a selected direction as rotation of the main antenna continues. One embodiment includes a coaxially-masted antenna support having a pair of coaxial masts mounted on a common support structure, one mast being rotatably mounted to support the main antenna and the other mast being fixed. A carriage is rotatably mounted on the coaxial masts to support the auxiliary antenna.

Abstract: An apparatus for decreasing stray radiation incident upon an infrared detector includes a concavely curved lens surface adjacent the detector, the center of curvature of which concave surface is located on the surface of the detector. This arrangement limits stray radiation originating rearward of the concave lens surface to black-body radiation emitted forward from the surface on which the detector is mounted, and the detector itself. That stray radiation may be reduced to a low value by decreasing the temperature and/or increasing the emissivity of the detector mounting surface and the detector itself. Stray radiation out of a desired wavelength band and originating forward of the rear concave lens surface may be attenuated by means of a spectrally selective filter.

Abstract: A modulated bunched electron beam incident on the inner conductor 16 of a coaxial structure launches TEM waves that are distributed to multiple radial waveguides 22 around the outer conductor 14 of the coaxial structure. A tuning piston 32 may be moved axially within the outer conductor for matching the impedance of the coaxial structure to the waveguide array.

Abstract: The target seeker system includes two radio frequency antennas consisting of two sets of radio frequency selective annular slot patch excited radiator receiver elements, one set for K-band energy, the other for X-band energy, sharing a common ground plane. The radio frequency antennas have a single multi-band image plate consisting of resonant dichroic surfaces which will selectively reflect X- and K-band energy. An image plate is formed with conductive patterns on each side of a low dielectric material. The reflective pattern acts as a quarter wavelength thick plate at the operating frequency. The top of the image plate which has X-band reflectors is spaced at one-half of the desired X-band wavelength above the ground plane and the K-band reflector on the bottom of the image plate is spaced at one-half of the desired K-band wavelength.

Abstract: A missile includes an optical fiber canister with the optical fiber wound as an annular fiber pack having an initial payout region extending from the inner annular surface. A reinforcing leader overlies the initial payout region of the optical fiber to form a leader composite structure. The leader composite structure is wound into a flat outwardly spiraling coil lying perpendicular to the axis of symmetry of the annular fiber pack, with the outer turn of the spiral leading away from the optical fiber pack. The coil is encased in a mass of potting compound. At the initiation of optical fiber payout, the turns of the coil progressively tear free of the mass of potting compound to achieve a gradual loading of the optical fiber and opening of a path for the axial payout of the portion of the optical fiber not protected by the reinforcing leader.

Abstract: An improved local vertical reference determination technique for use with projectile guidance systems. The vertical reference determination apparatus uses a passive retroreflector mounted on the projectile to direct a portion of the incident electromagnetic radiation produced by a launching device transceiver as a return signal back to the launching device transceiver. A preferred embodiment of the invention employs a retroreflector having an axis canted with respect to the central axis of the projectile, such that the return signal is a function of the instantaneous angle of rotation of the projectile. The return signal therefore has a minimum magnitude at a first instantaneous angle of rotation and a maximum magnitude at a second instantaneous angle of rotation.

Abstract: A rotary breech mechanism (10) is provided for loading large caliber guns. The mechanism comprises a rotary transfer member (12) which is cylindrical and mounted in the gun barrel (16) near the breech end (18). A hole (14) through the rotary transfer member (12) is aligned either with an ammunition magazine tube (48) for loading or with the gun barrel (16) for firing of a projectile (20). Once the projectile (20) has been fired, the rotary transfer member (12) is rotated to accept the next projectile, no matter what position the gun is in. The azimuthal orientation of the barrel (16) does not affect the operation of the loading mechanism.

Abstract: A retro reflection guidance and control system for a projectile, and a method of obtaining flight characteristics and controlling the projectile. A launch platform based transmitter/receiver and processor sends signals to a projectile, which signals are received at the back thereof. The transmitted signals are selectively reflected, to provide flight characteristic information to the transmitter/receiver, and detected to provide flight control information to the projectile.

Abstract: An array of antenna elements are configured in a lattice-like layer, each element being similarly oriented such that the elements form a two-dimensional antenna aperture that may form a planar or curved surface of a desired shape. The antenna elements are connected in a one-to-one correspondence in both number and form to a lattice of identical, multiport, isotropic, wave-coupling networks physically located under the antenna element array as a backplane of the antenna element layer. Each wave-coupling network or "unit cell" couples signals to and/or from its corresponding antenna element and further functions as a phase delay module in a two-dimensional signal distribution network. This invention can be embodied in a two-dimensional signal distribution network and in a wrap-around, conformal, millimeter-wave, phased array antenna, such as on the nose of a missile.

Abstract: A motion detection radar system comprised of a low power frequency tunable continuous wave transmitter and antenna, a receiver, an FM transmitter and antenna, and a handheld remote FM receiver. The radar system may be adapted to operate at any frequency from 600 MHz to 1.2 GHz. The motion detecting radar system uses a technique for measuring the changes in phase difference and the rate of change of phase differences detected thereby. The receiver captures the total energy reflected from all reflective objects within the antenna field of view and compares that signal with the transmitted signal in a mixer. If all objects are stationary and the radar system is stationary, the total complex phase pattern of the return signal is constant, and a fixed DC output signal is provided from the mixer. Any motion within the field of view changes the fixed phase relationship and causes a phase rate of change at the receiver output.

Abstract: A three dimensional imaging radar system and method for generating and processing radar information to produce a three dimensional image of objects viewed by the system. The system is designed to create three dimensional images of physical objects at relatively short range, up to a distance of about 1000 feet. The radar system comprises a servo controlled antenna system, wherein the servo system provides azimuth and elevation pointing angle output signals. Two radar transmitters provide radar signals in two different radar bands that are selectively transmitted by the antenna system as a radar beam. A radar receiver preprocesses radar return signals reflected from targets.

Abstract: A system for controlling the arming and firing of a weapon that is suspended from a parachute at an oblique angle and spun so as to be aimed over a spiral rotational scanning pattern on the earth as the parachute descends toward the earth. The weapon is supported by a platform so that the weapon is aimed in a predetermined direction relative to the platform. A detection system is supported by the platform and aimed in the same direction as the weapon for detecting predetermined radiation characteristics from targets of opportunity. A ranging system is supported by the platform and aimed in the same direction as the weapon for determining the range to the earth in such direction.

Abstract: Method and arrangement for an airborne radar system particularly adapted to detect large metal targets that are concealed from the air by camouflage or natural foliage. The arrangement includes an antenna that transmits a continuous wave electromagnetic signal having a selectable frequency that preferably has a wave length generally twice the length of an anticipated target and which is carried by a flying vehicle. The frequency of the transmitted signal is chosen to provide maximum penetration of the camouflage or natural foliage and maximum re-radiation from a metal target. Receivers connected to an in-line receiving antenna and to a crossed receiving antenna carried by a flying vehicle detect the radiation that is reflected from the terrain and a target with the same polarization as that transmitted. The co-linear antenna and receiver respond to the reflected radiation while the cross-polarized antenna does not detect this reflected radiation.