Abstract: A method for augmenting a noise-adaptive predictive proportional navigation terminal guidance scheme. In a second order configuration with noise adaptive varying gain parameters calculated as a function of time-to-go, this system implements an optimal control law to augment proportional navigation with a missile acceleration feedback term and a navigation ratio to account for first order autopilot time lag. This configuration results in nearly optimal miss distance behavior, with sensitivity to unmodeled errors being substantially less than that in modern guidance systems. The system is particularly useful for high altitude, minimally maneuvering targets.

Abstract: A highly accurate rapid gimbal assembly method utilizes two fixtures for establishing the critical gimbal assembly parameters of yield and axis of intersection and an adhesive for bonding each mating surface of the gimbal assembly for holding the components of the gimbal assembly in their adjusted positions. The fixtures include an inner/outer gimbal fixture for holding the inner and outer gimbals in relative position for bonding and a gimbal/post fixture for holding the gimbal assembly in alignment on the support post for bonding. These fixtures and assembly method eliminate the need for use of shims between the mating surfaces for establishing alignment of the critical parameters.

Abstract: A projectile body has a gyro mounted therein including a rotor and a mechanism for supporting the rotor for rotation about a spin axis initially coincident with the longitudinal axis of the projectile body and pivotable away from the longitudinal axis of the projectile body. The rotor is initially locked to the projectile body so that it is spun with the projectile body during launch. Thereafter, the rotor is unlocked and the projectile body is de-spun to a relatively slow rate of rotation while transferring angular momentum to the free spinning rotor which continues to rotate at a high rate relative to the projectile body. Rotationally phased steering commands, which are generated from on-board homing sensor signals or up-link data signals received from a remote error sensor, are applied to a linear actuator within the projectile body. The actuator pivots the spin axis of the rotor away from the longitudinal axis of the projectile body.

Abstract: A man portable shoulder fired rocket weapon system including a two section tubular launcher, sections of which are hingedly foldable one over the other to reduce the launcher length for storage and transport, and permitting the launcher to be holster carried in the manner of a sidearm. A lock and seal coupling connects the unfolded launcher tube sections to extend the launcher for firing and also serves as a safety element in the firing circuit. Two tubular blast shields are mounted concentrically upon the launch tube sections and are extendable therefrom to further lengthen the launcher and provide protection for the user against rocket motor exhaust. A compatible rocket round is carried in the folded launcher as a ready round. A waist worn holster and reload pack complete the weapon system elements.

Abstract: A firing mechanism for portable rocket launchers that includes a percussion activated thermal battery to supply electrical power for arming the warhead and igniting the motor of the rocket contained within the launcher. The energy to activate the thermal battery is not available until a firing pin spring is compressed by the opening of the firing mechanism cover preparatory to firing, and the output of the battery is isolated from the rocket by a normally open electrical switch that is not closed until the trigger mechanism moves to initiate the activation sequence. A safety plate physically blocks movement of the battery firing pin and trigger until positioned by the operator. The trigger and safety plate are arranged for single handed operation while at the same time maintaining a firm grip on the firing mechanism in aiming and firing the rocket launcher.

Abstract: A burner casing having a vertical support sleeve mounted at its center forms a combustion chamber below the sleeve and an annular duct space that surrounds the sleeve. A self supporting fuel cartridge containing consolidated solid fuel particles fits slidably within the support sleeve and has one end resting upon a mandrel located in the combustion chamber. Air to support steady state combustion of the fuel particles at a surface of the cartridge is forced downwardly through the cartridge. The heat of combustion and exhaust products pass from the combustion chamber through the annular duct space and then to other furnace components.

Abstract: A flexible printed circuit card assembly includes an insulating sheet positioned over the foil of a flexible printed circuit card and adapted to accommodate the passage of electronic component leads therethrough for soldering to the printed circuit card. A layer of protective insulating foam, having a backing thereon, is positioned over the components and the assembly is rolled into a spiral configuration with leads extending from at least one end.

Abstract: A simple, retractable, self-erecting wing for a low speed missile having a fabric wing cover affixed to a leading edge structure that is the only erected structural member in the wing operative position. The wing cover forms a pocket that contains air. The leading edge structure is hinged and folds, along with the wing cover, into a compact slotted space adjacent the outer wall of a missile body. In the folded position the leading edge structure forms a cover for the slot and the cover coincides with the outer shape of the missile body. A large fabric wing can be completely stored within the missile body for minimum drag during any high speed portion of the missile flight, the wing being released to the operative position by a simple mechanism.

Abstract: A missile launcher tube from which a missile is fired from a forward end causing gases to exit out the aft, or exhaust gas, end of a launcher tube in which the aft end is provided with a conical surface (flare) forming a nozzle so that as the missile exits from the forward end, a forward pressure force created by the exhaust gas acting on the conical surface as the exhaust gas exits from the aft end opposes and reduces an aft end directed recoil force. The conical nozzle is located entirely within the outer surface of the launcher tube so that the launcher tube envelope is not disturbed.

Abstract: An articulated nose is locked in axial alignment with the longitudinal axis of a rolling projectile body. Pyrotechnic means within the nose is actuated to unlock the nose and tilt it toward the target when the error between the projectile path and the path to the target exceeds a predetermined threshold.

Abstract: A signal processor for an array of charge injection device (CID) radiation detector elements is disclosed. An integration time control system effectively increases the dynamic range of the detector array by varying the integration times of the detector elements in accordance with measurements of the magnitudes of data signals respectively produced by the detector elements in relation to the saturation thresholds and of the detector elements so as to maintain the amount of radiation stored in a predetermined percentage of the detector elements within a predetermined operating range below their saturation thresholds and above their noise level. A responsivity compensation system adjusts the data signals prior to such measurements to compensate for variations in the responsivity of the detector elements. In response to the identification of a defective detector element, the last previously provided adjusted data signal in the data stream corresponding to a non-defective detector element is reproduced.

Abstract: A pedestal gimbal drive assembly includes a yoke and a cross shaft mounted for movement about separate orthogonal axes for affording a sensing platform for being driven by differential drive mechanism for sweeping a hemispherical segment. One embodiment of the drive means includes an endless cable drivingly connected by means of two separate reversible motors to a pair of fixed pulleys on the platform and trailed over a plurality of idler pulleys and operative to move the platform in the desired motion. An alternate embodiment includes a driven gear connected to the ring and a pair of bevelled gears connected to the driven gear and connected by link members to the two independent reversible motors.

Abstract: A system for proportionally navigating an airframe to a target wherein the airframe is maneuvered by an onboard flight control system including body rate gyros for detecting the movement of the airframe relative to a fixed reference. A target sensor is mounted for pivotal movement in the pitch and yaw planes on a gimbal assembly rigidly connected to the airframe body. Mechanisms, such as motor/tachometer/potentiometer assemblies, pivot the sensor in the pitch and yaw planes and provide signals representative of the angular rate of motion and angular position of the sensor. These signals, along with the sensor output, are utilized in a gimbal track loop for pivoting the sensor so that it tracks the target. The outputs of the body rate gyros are utilized to remove or decouple the airframe body motion from the gimbal track loop signal. The system eliminates the need for a costly and complex space stabilized gimballed sensor while offering improved performance over a system utilizing a pure body fixed sensor.

Abstract: A gimbal assembly includes an outer arcuate yoke gimbal member mounted on rollers to rotate about its axis and an inner gimbal member includes a platform pivotally mounted in the yoke to rotate about a second axis. Two drive motors are separately and independently connected through independent cable drive assemblies to separate ones of the inner and outer gimbal members and functions either individually or together to rotate the gimbal members selectively or both together in a combination of motion. In one form, the two drive motors are co-axially mounted in the base of the gimbal assembly. In another form the gimbal drive motors are co-axially mounted with the outer housing of one motor forming the drive pulley for the other drive assembly. In another arrangement the motors are disposed on adjacent parallel axes with one drive motor for the inner gimbal having co-axially disposed drive pulleys for the drive cable.

Abstract: A circuit which performs regulator or limiter functions at current and voltage levels below the operating ranges of conventional zener diodes. The output of an op amp is connected through a diode to a main input terminal which may be connected between a power source and one end of a load resistor. A first current limiting resistor connects the main input terminal to the inverting input of the op amp. A second current limiting resistor connects the non-inverting input of the op amp to the wiper terminal of a potentiometer which permits adjustment of a simulated zener voltage V.sub.z. A pair of supply voltage terminals of the op amp are connected to voltages V.sub.cc and V.sub.ee, respectively. A pair of fixed terminals of the potentiometer are also connected to voltages V.sub.cc and V.sub.ee, respectively. The simulated zener voltage V.sub.z may be positive or negative, and may be adjusted to any value within limits determined by voltages V.sub.cc and V.sub.

Abstract: A sealing liner of flexible material such as Teflon has a downwardly tapering side wall which is positioned over a header. A case is positioned over the liner, and the top of the case is moved into engagement with the top of the liner to capture the tapered side wall of the liner between the side walls of the header and the case to provide a tight cold flow seal so that small particles working loose from the case cannot reach the header.

Abstract: A bistatic passive radar system and method for airborne use in a first aircraft in conjunction with a host transmitter located in a second aircraft that may be at a different altitude than the first aircraft, characterized by a system and method for determining the distance between the aircraft. The system for determining the distance between the aircraft includes a system for receiving radar signals from the host transmitter directly and via reflection from a selected ground target located between the two aircraft; a system coupled to the receiver for determining the apparent range R.sub.a from the host transmitter on the second aircraft to the receiver on the first aircraft in response to receipt of the radar signals; a device on the first aircraft for determining the altitude H of the first aircraft; a device on the first aircraft for determining the angle .theta.

Abstract: A receiver for locating a source of RF radiation received by a four-arm spiral antenna having an angular measurement frame normal to the antenna axis, including a detection circuit for detecting signals received from each of the spiral arms in response to receipt of RF radiation by the antenna; a first comparison circuit for comparing signals detected from a first opposite pair of the spiral arms to produce a first signal that is proportional to a first function of the frequency of the received RF radiation and the angular displacement of the radiation source in the measurement frame; a second comparison circuit for comparing signals detected from the remaining opposite pair of the spiral arms to produce a second signal that is proportional to a second function of the frequency of the received RF radiation and the angular displacement of the radiation source in the measurement frame; and a processing circuit for processing the first and second signals to produce third and fourth signals that are proportional

Abstract: A platinum-cadmium sulfide Schottky barrier photovoltaic detector which is capable of sensing near ultraviolet and short wavelength visible radiation with extremely small response to wavelengths longer than about 5200 angstroms. The detector is fabricated with both the ohmic and barrier contacts located on the same side of the cadmium sulfide substrate to facilitate wire attachment by high-speed bonding techniques. A titanium-gold-titanium infrared shield structure is deposited directly on the substrate and is utilized to provide a connection between the ohmic contact and the substrate. An insulating layer of silicon dioxide covers the shield structure. A thin layer of platinum is deposited directly on the substrate in a small central optically active area surrounded by the insulated shield structure. A metal boundary layer overlies the periphery of the platinum layer and prevents the barrier contact metalization from affecting the properties of the Schottky barrier.

Abstract: An optical floating deck modulator to modulate a control element of an electron device, such as the grid of a Klystron tube or traveling wave tube, having two high power MOSFET switching devices connected in series between a high positive and a high negative voltage source (which also supply the high voltage to the electron device) with the control element coupled between the MOSFET devices. This arrangement provides a low resistance path between the two voltage potentials and the control element being modulated, as the two MOSFET devices are switched alternately ON and OFF and thus achieves fast rise and fall times over a very high voltage swing. Each MOSFET device has a separate drive circuit (deck) and each deck comprises a photo diode information receiver coupled to a transimpedance amplifier, the output of which is amplified by a bipolar transistor amplifier and a FET amplifier. Total isolation between the decks and the information source is achieved by an optic link therebetween.