Abstract: A high average-power microwave window is provided whose thermal conductivity has been enhanced to enable it to transmit higher average RF power levels than conventional windows of the same size. Such a window is suitable for use with high-average power RF sources such as klystrons and magnetrons. The window comprises a ceramic substrate, typically a low-loss ceramic such as alumina or quartz, to which narrow strips of a high thermal conductivity material have been bonded. One such high thermal conductivity material is synthetic polycrystalline diamond, which can be bonded to the surface of a dielectric substrate using a high-temperature cement or can be directly deposited on the surface by a process such as chemical vapor deposition (CVD). High-purity alumina, a commonly-used material for high-power RF windows, has a thermal conductivity of 26.4 W/m.multidot..degree. C., while synthetic diamond has a thermal conductivity of 1000 W/m.multidot..degree. C., 2.6 times that of copper and 38 times that of alumina.

Abstract: A flight launched fiber optic dual payout system (10) for a command guided missile (12) is disclosed which combines a missile (12) with two fiber optic cable dispensers (18, 20) into a single unit that can mount to a single launch station of a launch platform (14). The dual payout system (10) of the present invention includes a missile (12) having a missile dispenser (18) for dispensing a first fiber optic cable (22) connected to the missile (12) and a launch platform dispenser (20) for dispensing a second fiber optic cable (24) detachably connected to the missile dispenser (20). The first and second fiber optic cables (22, 24) are connected by a length of reinforced cable splice or leader line (26) which is housed in a protective retainer (28) on a launch platform interface unit (16) that operates to mount the missile (12) to the launch platform (14) and complete a fiber optic data link between the missile (12) and the launch platform (14).

Abstract: A process for reducing background clutter of a scene, and isolating an object of interest. The process includes calculating a minimum output from a plurality of appropriately configured anti-median filters representing a minimum difference processor (MDP) filter. In a first embodiment, the MDP filter includes a (5.times.5) matrix of elements wherein each element has an intensity value representation of the scene. A first anti-median filter array is configured as a horizontal array of 5 pixel elements in which the center element of the matrix is the center element of the horizontal array. A median value of the 5 elements of the horizontal array is determined, and is subtracted from the value of the center element to determine an anti-median value of the horizontal array. The same process is performed for a vertical 5 element anti-median array, and two diagonal 5 element anti-median arrays, all including the center element of the matrix as the center common element of the arrays.

Abstract: An apparatus for propagating electromagnetic waves at a predetermined reduced guide wavelength. A waveguide (27b) is provided for receiving and guiding the electromagnetic waves. A dielectric (28) is disposed in the waveguide (27b) to decrease the guide wavelength of the received electromagnetic waves. The dielectric (28) allows the width of the waveguide (27b) to be reduced without significantly compromising its power-carrying capability.

Abstract: A tracking system (200) adapted to receive input imagery and provide standard television format video input signals in response thereto. The video input signals are processed (228) to provide intermediate analog and digital signals. The intermediate analog signals are further processed (239) to provide centroid tracking of a target. The intermediate digital signals are processed (236) to provide correlation tracking of the target. In a specific implementation, the standard television format video input signals are provided by a charge coupled device (214), a Vidicon camera, an infrared focal plane array, a Newvicon camera or other device which generates standard television format video signals. A video rotation circuit may be used to provide proper image orientation regardless of the mounting orientation of the system.

Abstract: A system (30) for determining a missile kinematic property. The inventive system includes a radar system (36) for obtaining radar range measurements (34). An inertial reference unit (40) tracks changes in missile acceleration without the use of the radar range measurements and provides a signal (38, 42) in response thereto. An altitude Kalman filter (32) and a subtractor circuit (48) are used to combine the signal (38, 42) and the radar range measurements (34) to provide an accurate estimate (50) of the property. In a specific embodiment, the kinematic property includes missile vertical velocity and missile altitude. A radar system (36) supplies radar range information (34) to the Kalman filter (32). A loop (52) from the Kalman filter (32) to the radar system (36) facilitates estimating the radar range measurements (34) when invalid radar range measurements are provided by the radar system (36).

Abstract: A cryogenic cooler and a dewar assembly including a cooled surface; a cooling surface for removing thermal energy from said cooled surface; and an adapter disposed between said cooling surface and the cooled surface for conducting thermal energy therebetween. A first fluid is disposed between the cooled surface and the adapter for conducting thermal energy from the cooled surface to the adapter. A second fluid is disposed between the cooling surface and the adapter for conducting thermal energy from the adapter to the cooling surface whereby the cooling surface remains free to move axially relative to the adapter at a temperature of the cooling surface at which the first fluid is susceptible to freezing. This allows for movement of the cold finger relative to the dewar and adapter, due to differential thermal coefficients of expansion or support structure motion, without adversely affecting the communication of thermal energy from the load.

Abstract: Improved magnetron oscillators that controllably form a plasma within each of its resonant cavities to rapidly change the resonant frequency of each cavity. The present invention also provides for frequency tuning methods for use with magnetron oscillators. The plasma is controllably formed in one or more subcells of each resonant cavity in a manner that alters the electromagnetic field within each cavity. Preferably, a magnetized collisional plasma is controlled to rapidly change the resonant frequency of each cavity. However, many types of plasmas may be used to implement the present invention. Controlling formation of the plasma within each cavity tunes the magnetron oscillator on a submillisecond time scale.

Abstract: An antenna system includes a beam source of a microwave wave beam, a gimbaled antenna, and a waveguide including a mirror system that directs the microwave wave beam from the beam source to the antenna. The mirror system is formed of a series of mirrors operable to reflect the microwave wave beam and includes a first paraboloid mirror positioned to receive the microwave wave beam from the beam source, a first planar mirror positioned to receive the microwave wave beam from the first paraboloid mirror, a second paraboloid mirror positioned to receive the microwave wave beam from the first planar mirror, and a second planar mirror lying on the system azimuth axis and positioned to receive the microwave wave beam from the second paraboloid mirror. The first planar mirror may be controllably tilted to finely steer the aim of the microwave wave beam to the antenna.

Abstract: A low cost diaphragm actuated absolute pressure regulator. The regulator comprises a housing having first and second sections that are secured together. The first section has a cavity and a diaphragm that seals the cavity and first section of the housing. An O-ring seal is disposed in a groove of the first section that seals against the diaphragm. The second section of the housing houses a movable and sealable vent plug that moves in response to movement of the diaphragm, and one or more vent openings for venting the interior of the second section to external pressure in response to motion of the diaphragm. The pressure regulator may be preferentially used in an upper atmospheric system that needs to maintain a specified pressure, but requires venting capabilities. Such systems include missiles that fly into the upper atmosphere.

Abstract: An optical system includes a housing having an axis of elongation, and a non-spherical window affixed to the housing. An optical corrector, preferably in the form of an aspherical strip of transparent material, is positioned adjacent to the curved inner surface of the window. The optical corrector is mounted on an optical corrector support, which is rotatable about the axis of elongation. An optical rain is positioned such the the optical corrector lies between the window and the optical train. The optical train includes at least one optical element operable to alter an optical ray incident thereon, and a gimbal upon which the at least one optical element is mounted. The gimbal is pivotable about a transverse axis perpendicular to the axis of elongation. The optical train is mounted on an optical train support, which is movable independently of the optical corrector support. A sensor is positioned to receive the optical ray passing sequentially through the window, the optical corrector, and the optical train.

Abstract: A cryostat (12) with an actuator (40) which reacts to sensed temperature changes via externally controlled thermal heating generated therein. The actuator (40) is constructed with material having a high coefficient of thermal expansion. A flexible heating element (44) is embedded in the actuator material. A temperature sensor (62) provides a signal to cryostat control electronics. Responding to the temperature signal, the control circuitry (60) regulates current to the heating element (44) in the actuator (40). As the actuator temperature increases due to the heat generated by the heating element (44), it expands and moves open an attached needle (50) relative to an orifice (30), thereby increasing cryogen flow and regulating cooling. When the desired cold temperature is attained, current and heating are stopped. Flowing cryogen cools the actuator which shortens the actuator and pulls the attached needle into the orifice to regulate flow.

Abstract: A system and method of processing data in a sensor system which receives signal returns from pulsed coherent transmitted signals which are transmitted at a pulse repetition rate and with a pulse repetition interval (PRI). The method includes providing range-filtered data in response to the received signal returns; formatting successive sets of data received during a post detection integration (PDI) interval into a plurality of overlapping coherent processing interval (CPI) data sequences; performing FFT processing on the overlapping CPI data sequences to provide transformed data sequences; performing range-sample CPI processing on the transformed data sequences; and performing noncoherent integration (NCI) processing on output data from the range-sample CPI processed data sequences over a range trajectory in accordance with hypothesized radar-target range rate to provide noncoherent gain-enhanced output data.

Abstract: A system for measuring the roll angle of a rotating projectile. The system includes a transmit system mounted on the projectile. The transmit system has a linearly polarized transmit antenna system, a first transmitter coupled to the transmit antenna system for transmitting a first transmit signal at a first frequency, and a second transmitter coupled to the transmit antenna system for transmitting a second transmit signal at a second frequency. The first frequency is different from the second frequency, and the first and second transmit signals are in phase coherency. The system further includes a receiver system located remotely from the projectile. The receiver system includes a linearly polarized receive antenna system for receiving the first transmit signal and the second transmit signal. A first receiver section is provided for receiving and downconverting the first transmit signal to provide a first receiver signal.

Abstract: An antenna is provided that receives electromagnetic radiation and includes a dielectric substrate (106). First and second spirals (60 and 70) on a first surface of the substrate (106) radiate the electromagnetic radiation. A third spiral (80) is utilized on a second surface of the substrate (106) and is substantially underneath one of the first and second spiras(60 and 70). The resulting spiral antenna is compact and has multioctave bandwidth capability.

Abstract: A surface-protected composite article, such as a missile component, is prepared with a heat-sink substrate, a first composite layer of an pre-ceramic-matrix structural composite material, and a second composite layer of a reinforced silicone pre-ceramic material. The silicone material is co-curable with the organic matrix of the first composite layer. The silicone at the surface of the article is thereafter converted to a silica refractory by an appropriate treatment such as exposure to an oxygen-rich plasma or a high-surface temperature. The silica protects the surface of the composite material.

Abstract: A broadband, high power balun which includes plural sets of first and second coaxial cables. Each cable has a center conductor and a shield conductor. Each shield conductor of each cable within each set is connected to a shield conductor of the other coaxial cable of the set. The first input lead is connected to a first end of a center conductor of a first coaxial cable of each set. The second input lead is connected to a first end of a center conductor of a second coaxial cable of each set. A second end of a center conductor of a first coaxial cable of a set of coaxial cables provides an output lead for the balun. A second end of a center conductor of a second coaxial cable of a set of coaxial cables provides an output lead for the balun. A second end of each remaining center conductor of each coaxial cable of each set of coaxial cables is connected to a second end of a center conductor of a coaxial cable of another set of coaxial cables.

Abstract: A system (10') for generating a missile guidance gain factor adapted for use with guided missiles. The inventive system includes a guidance control system (52) for obtaining current guidance parameters(55, 57) including ideal navigation gain, closing rate, line of sight rate, missile maneuverability, and missile velocity parameters. Software (56) running on a guidance control processor (54) computes a current guidance gain factor reflective of the current maneuverability of the missile from the guidance parameters (55, 57). In the illustrative embodiment, the system 10' further includes a nonlinear notch circuit (56) that generates an acceleration command (59) from the guidance parameters (55, 57) that varies in response to varying missile maneuverability parameters (57). The guidance control system (10') includes a conventional guidance law computation circuit (54, 55) and electromagnetic sensing equipment (52).

Abstract: A locking assembly that mechanically locks an attachment bolt, such as one used to secure a missile launcher to an aircraft, for example, thus preventing the bolt from vibrating loose as a result of vibration experienced during flight. The locking assembly has a spring loaded locking nut that mechanically engages a hex head of an extension shaft that is coupled to the attachment bolt. Transverse pins permit axial movement of the locking nut but prevent rotation thereof. A socket is used to push the locking nut away from the hex head of the extension shaft, so that the attachment bolt can be loosened or tightened. When the socket is removed, a spring pushes the locking nut over the hex head of the extension shaft, locking the attachment bolt and preventing it from turning.

Abstract: A suspension lug system for use with a jettisonable weapon that provides a mechanical interface between the weapon and a multiplicity of aircraft. The system has a dual-function lug that is disposed in a well when it is in a stowed position, and that is pivotable in opposite directions on a transverse pivot pin. A first end of the lug is configured as a saddle lug that is exposed above the outer surface when the lug is rotated into a saddle-deployed position. The second end of the lug is configured as a clevis that is exposed above an outer surface of the system when the lug is rotated into a clevis-deployed position. A spring is coupled to the lug that spring loads it and returns it to a stowed position when it is not engaged with the ejector release unit to preserve the outer contour of the weapon.