Abstract: A radome useful with high-speed guided missiles has an inner conical shell made of a strong, high temperature resistant material transparent to radiant energy in the operative frequency range of a sensor mounted inside the shell. An outer ablative layer covers the exterior surface of the shell. This layer is made of a material which is also transparent to radiant energy in the sensor frequency range and which melts or sublimes and displaces from the shell at a predetermined elevated temperature and/or velocity during high-speed flight. The thickness of the ablative layer is selected so that it compensates for increased thickness and/or refraction resulting from thermal expansion of the shell, thereby minimizing guidance errors.

Abstract: An imaging radar system for generating images of objects disposed behind an obscuring structure. The system comprises a low power, frequency tunable, continuous wave transmitter and an antenna array coupled to the transmitter that includes a transmit antenna and a plurality of receive antennas. A radar receiver is coupled to the antenna array, and a computer processor is coupled to the radar receiver that comprises a digital signal processor and a computer. A radar display is coupled to the computer for displaying the images of the objects disposed behind an obscuring structure. A power source is coupled to the antenna array, the transmitter, the radar receiver, and the computer processor for providing power thereto. Time difference of arrival processing is performed in the computer for providing radar angle scanning upon receipt of radar return signals from the objects using the antenna array.

Abstract: A device for use in a rapid-fire weapons system wherein a gun is movable in both elevation and azimuth. The device is designed to have a high round storage capacity and transfers rounds across the azimuth axis, thus allowing the gun to move in azimuth with respect to the magazine. The storage, or accumulation, feature of the device allows rounds to be fed to the gun before the magazine has been driven to the demand rate.The device also provides a closed loop round carrier system which allows for the return of expended round casings to the magazine.

Abstract: A fast and reliable switch (50) for multi-channel, bi-directional fiber optics data link (FODL) systems. The FODL channel switching is accomplished through a software command on the subcarrier frequency (SCF) code without using any moving components or wavelength sensitive optical devices. A fiber star coupler (92) and in-line erbium doped fiber amplifiers (94A-94Q) transform the FODL system into an electrically switchable, fiber star network with low optical power loss penalty. The switch can be used in multiple fiber optics guided missile launch systems and fiber optics based surveillance systems with multiple outposts. The switching scheme allows the launcher/controller (60) to perform a time-sharing control on multiple missiles (or outposts) (80-80P) by switching the SCF code sent to the programmable SCF generator of the OE unit in the controller (launcher).

Abstract: A system for cleaning contaminants from small areas with minimal uncontained waste. The invention (10) includes a nozzle (60) having a first aperture for ejecting a fluid and a second aperture for providing suction. The first nozzle ejects a pressurized fluid and the second nozzle provides suction. In a particular embodiment, the first and second apertures are coaxial. Thus, contaminants and residues are dislodged and dissolved by cleaning solvent ejected through the first aperture while the second aperture effectively removes the waste material from a small cleaning area.

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: This invention is directed to an electronic gimbal system (10) which stabilizes a digital video image of a particular scene taken by a sensor which is under disturbance forces. The video image is stored as a two-dimensional array of pixel locations (12) and is applied to an address look-up calculator (14) along with a signal from an inertial sensor (16). The inertial sensor (16) determines the offset of the array of pixel locations from an inertial reference frame and adjusts the input array accordingly. In one particular implementation, the address look-up calculator (14) applies a bilinear interpolation to the pixel location in order to provide a weighted sum of pixel intensities for each offset pixel location.

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 method that provides precise target location measurement using a synthetic aperture radar (SAR) system jointly with a global positioning inertial navigation system (GPS/INS) located on a moving aircraft. The SAR system provides a precise measurement of the round trip elapsed radar wave propagation time from the aircraft location to a selected pixel in a ground map that includes a portion of the target. The velocity of radar wave propagation is measured at the same time that the range time lapse to the designated SAR map pixel is measured. When combined with position and velocity information derived from the GPS/INS inertial navigation system, the radar wave propagation time is used to calculate the position of the target pixel in GPS/INS coordinates, thereby improving measurement accuracy. The method comprises flying an aircraft containing GPS/INS and SAR systems along a predetermined flight path.

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: 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: 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: 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: A method and apparatus for non-uniformity compensation for infrared focal plane arrays in an infrared imaging device (10) including a calibration operation and a correction operation. The calibration operation measures the response (24) generated by the detector elements (14) in the focal plane array (16) to a wide range of known signal flux levels of infrared radiation (22) produced by a uniform black body under controlled conditions. The responses (24) are then stored as a digital video signal (27) in a look-up table memory (38). The correction operation achieves the near real-time compensation of a second response of the detector element (14) to the signal flux level of infrared radiation (22) produced by objects in the field of view surveyed by the imaging device (10) by comparing the second response to the stored digital video signals (27) and interpolates the second response to a corrected digital video output signal (31).

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: An apparatus (10) for testing an operational status of a missile interface system includes a portable control unit (16) having an interface panel (28). The interface panel (28) has a plurality of umbilical ports adapted to receive data from a plurality of missile stations (12) via a corresponding plurality of umbilical cables (18). The interface panel (28) is further includes a coaxial port (40), adapted to receive data from a radar trap (22) via a coaxial cable (20). The apparatus further includes a fixture assembly (116) having a main body portion (120). The main body portion (120) has a channel (122) through which a first end of the umbilical cable (18) is allowed to pass. The fixture assembly (116) is adapted to be releasably mounted to a missile station (12).

Abstract: An optical fiber evaluation test station (20) includes optical fiber supply (26), translation, and rewinding mechanisms (52), and at least one module performing a test of optical fiber quality through which the optical fiber (22) continuously passes. The test station (20) includes a supply section wherein the optical fiber (22) is paid out from a supply spool (24) and cleaned by a cleaning and static discharging unit (30). There is a high tension test section wherein tests such as a buffer cure test (46) and a bend proof test (48) are performed. In a low tension test section, tests such as an optical fiber diameter test (58), a buffer flaw test ( 60 ), and a visual observation test (64) are performed. Tension-isolating capstans (40, 44) separate the various sections, optical fiber guides (62) direct the optical fiber (22) and stabilize its movement, and spring-mounted dancers (36, 42) measure the tension in the optical fiber (22) in the tension-isolated sections.

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: The mode convertor employs two intermediate modes, a coaxial TEM and a rectangular waveguide TE.sub.10 mode, in the transition between the TM.sub.01 and TE.sub.11 circular waveguide modes. The coaxial line provides isolation while acting as a mode filter between the device input and output ports. The rectangular waveguide provides a wide mode separation ratio between the TE.sub.10 and TM.sub.11 modes. The TE.sub.10 mode then transitions into the TE.sub.11 in the circular output waveguide. The coaxial section keeps the output TE.sub.11 mode from scattering back to the input, and the rectangular section keeps the TM.sub.01 from being excited in the output.