Abstract: An actively damped steering rate sensing device for an autopilot control system capable of producing angular rotation in a control plane of an intentionally continuously axially rolling airframe such as a homing missile in response to a rotation related guidance command signal. The device includes an elongated armature member mounted to the airframe for pivotal movement about an axis extending through the member intermediate its length. The pivot axis is oriented with respect to the rotational axis of the airframe so that the armature member will pivot by gyroscopic precession in response to rotation in the control plane of the rolling airframe. Sensing and damping coils are mounted on opposite ends of the armature member. Magnets and flux path return elements are fixedly mounted adjacent each of the coils.

Abstract: An anti-armor weapon comprises an outer casing in which a non-explosive, armor-penetrating device, suitably a solid rod of heavy, high density metal or metal composite, is mounted. The penetrating device is mounted in a forward portion of the casing while a launch population device is mounted at the rear end for launching the weapon from a launch tube or firing barrel at a first, subsonic launch speed. A second, boost propulsion device is mounted in the casing adjacent the penetrating device for accelerating the weapon to a second, faster speed sufficient for the penetrating device to penetrate a target, and is associated with an igniter for actuating the boost propulsion device. A sensor is provided within the missile for sensing when the weapon is a predetermined distance from the target and subsequently actuating the igniter.

Abstract: A lateral thruster for missiles is provided which comprises two or more individually rotatable thruster motors with integral nozzles. If the thrusters are located at or near the center of gravity of the missile, the missile can be maneuvered while it remains pointed at the target. Locating the thrusters forward or aft of the missile center of gravity enables steering forces as well as lateral translational and roll forces to be provided. The thruster motors need not be disposed in pairs. The use of integral nozzles obviates sealing problems and allows mountings that permit rapid rotation of the thruster motors to improve missile response time. The lateral thruster disclosed is effective at nearly all aerodynamic angles of attack, missile velocities, and altitudes. The thruster as a unit is enclosed by a shroud that blends into the missile body contour. Possible propellants for the thruster motors include solid propellants and compressed gases.

Abstract: A rocket propelled missile assembly comprises an outer casing defining an internal solid rocket propellant chamber, the casing having an opening at its forward end aligned with an internal tube submerged in the rocket propellant chamber, and at least one exhaust nozzle at its rear end for venting exhaust gases from the propellant chamber. Solid propellant is contained within the propellant chamber surrounding the internal tube, and a separate terminal stage missile is partially or fully submerged in the tube with the capacity to separate from the tube forwardly through the front end of the casing. The missile separates from the remainder of the system on booster burn out.

Abstract: An antenna system having first and second arrays of radiating members, first and second sets of corresponding bifurcated members and two pairs of feed members. The radiating members of the first and second arrays each have a near end and a far end and a linear portion therebetween with radiating slots formed therein. The linear portions of the radiating members are interleaved in a planar spaced parallel relationship. Each bifurcated member has a unitary portion and a bifurcated portion with the bifurcated portion having a pair of coupling ends. Each bifurcated member is coupled at its unitary portion to the near end of a different radiating member of its corresponding array and also coupled at its coupling ends to a different feed member of its corresponding pair of feed members. The antenna system further includes a monopulse comparator coupled to the input ends of the first and second pairs of feed members for operation as an amplitude comparison monopulse antenna.

Abstract: A system and process, including a combination of a solder well and a vacuum system wherein micro through holes are filled with solder. A PC board or the like is supported for contact with solder on one side and with a vacuum apparatus for the application of a vacuum to the other side so that solder is drawn into the through holes for establishing electrically conductive connections therethrough.

Abstract: An apparatus for seating and tightening clamps around joints between tubular sections comprises an elongate flexible member such as a chain for extending around a clamp positioned over a joint, the member having rollers spaced along its length, and a tightening device for applying tension to the member to tighten it around the clamp so that the rollers roll around the surface of the clamp and apply a radial force to the clamp.

Abstract: A missile canister hatch cover is provided which deflects the rocket exhaust from an adjacent uptake channel away from a missile as it leaves the canister. After diverting the uptake exhaust flow away from the missile, the hatch cover is returned to its closed position by the missile rocket exhaust as the missile nozzle clears the canister opening. Overall wear and tear on the launching system from the rocket exhaust is reduced and the uptake flow plume is stopped from expanding above the launcher. During missile launch the hatch cover is unlatched and spring loading opens it more than 90.degree. to a locked position where it interferes with the exhaust flowing from the uptake. The interference deflects the uptake flow away from the missile during flyout to avoid the heating, side thrusts, and contamination associated with the uptake exhaust flow field.

Abstract: The described embodiments of the present invention provide a high-gain antenna while allowing for the inclusion of devices within the antenna array. In one embodiment of the invention an array of receiver/transmitter elements is positioned in a pan-like reflector base. The elements are positioned one-quarter of a wavelength from the surface of the base. The wavelength is the wavelength of the chosen frequency of transmission or reception of the antenna. A partially reflective plate is positioned one-half wavelength from the base and thus one quarter wavelength from the elements. Reflective disks are also positioned one-half wavelength above the base and are positioned directly above the elements. The disks create a resonant cavity around the elements for waves of the chosen frequency arriving from near normal to the plane of the base or being emanated from the elements at a normal or near-normal angle. The partially reflective plate extends this resonant area spatially from the element.

Abstract: A method for making a metalized dichroic parabolic lens reflector for multi-frequency antenna system applications. The reflector is prepared by depositing an etchable conductive metallic layer upon a parabolic work surface of a male mandrel. The metallic layer is adhered to a parabolic support surface of a substrate formed of a low dielectric constant material. The mandrel is separated from the metallic with the metallic layer remaining bonded to the support surface. Photoresist imaging and chemical etching techniques are used to form a dipole grid pattern in the metallic layer.

Abstract: A carbon composite tensile test specimen for high temperature testing and a method of fabricating the same are disclosed. A plurality of holes are drilled in first and second end sections of the specimen and then the end sections are electroplated with nickel. The nickel plating of the end sections prevents breakage of the ends in the jaws of a tensile testing apparatus. For high-temperature testing, a standard-sized specimen may be used with the jaws in the hot zone.

Abstract: An apparatus provides matched filter output characteristics for known signals embedded in noise signals that have varying noise power distributions. The system correlates applied signals with a manipulated version of the applied signals in an analog-to-analog correlator. The manipulated signals are derived by Fourier transforming the applied signals and estimating the noise power spectral density. A filter transfer function is then calculated using the noise power estimates and stored information related to the characteristics of the known signal. The transfer function is then inverse Fourier transformed to provide a filter impulse response characteristic which is correlated with the applied signals. A method of processing applied signals to provide for an enhanced signal-to-noise ratio for varying noise power distributions is also disclosed.

Abstract: A process for producing a copper lead frame tape in which the individual fingers of the lead frame are provided with gold plated bumps. A copper foil is provided with dry film photoresist on both sides and is initially processed to provide openings in one side of the resist for electroforming of the end products directly on the copper foil. Further processing produces openings on the other resist side in locations other than opposite the first resist side bumps whereby a following chemical milling of the exposed opposite side copper yields a plurality of fingers, each consisting of an integral bump/copper foil arrangement. The electroforming step is made possible by a novel double-cell electroplating method in which a relatively high-impedance ion path connects the two cells. Bump heights of as much as 0.0013 inch or greater are produced by the disclosed process, with uniformly excellent quality.

Abstract: A method for manufacturing a probe test structure for microcircuits utilizes a multiple coating method in conjunction with a novel double-cell electroplating apparatus having a relatively high-resistance ion path between the cells. Photoresist is applied to both sides of a copper foil, copper posts are electroformed onto selected areas of one side of the foil through image hole patterns, the remaining photoresist is stripped away, polyimide prepreg is laminated to the post side of the foil, the copper posts are exposed by sanding, photoresist is reapplied to both sides of the sanded remainder, additional copper is electroformed on each post through image hole patterns in the post side of the photoresist, the foil on the side opposite the posts is chemically milled to provide leads integral with each post using appropriate masking techniques and, finally, all of the remaining photoresist is removed to leave the desired test probe set.

Abstract: An in-flight jettisonable protective cover device for protecting fragile, accurate, radomes or signal-responsive components for the major portion of a flight which is capable of being jettisoned in one piece at supersonic speeds from a guided missile, other air vehicles, or space vehicles. The cover device is for use, for example, in combination with a guided missile having a shell structure, a nose portion, and a radome in the missile nose. The cover device is attached to the missile nose for covering the radome such that an inner space is defined. A plurality of shear pins or other quick-release mechanisms attach and retain the cover device to the missile shell. A source of low pressure gas pressurizes the inner space to approximately 50 psi. A rapid-discharging, high pressure gas cartridge produces a high pressure gas for exerting a pressure force on the aft face of the cover device.