Abstract: An airborne missile launcher for air launching of man-portable, tube-launched missiles includes a central support frame with attachment means for detachable attachment to an aircraft or other launching platform, with a central frame member having a launch tube saddle support assembly at each side of the frame member with quick detachable clamp means and an alignment guide for quickly positioning and securing launch tubes into position with auto connecting means for automatically connecting the electronics control system and coolant gas to the launch tube assembly upon clamping the assembly into position. An aerodynamic shell encloses the support structure and includes a quick release cover for providing access to the tube clamp assemblies for loading and unloading launch tubes.

Abstract: An electroforming process in which parts of complex configurations can be formed more effectively than with the processes available in the prior art. In particular, a heat shrinkable tube is positioned on a mandrel, the mandrel being of a shape different from the ultimate part to be formed but which will develop the desired shape for the part when shrink tubing is shrunk onto the mandrel. A layer of metal is then deposited over the tube and the mandrel is then removed. The tube is heated again, shrinking to a smaller size which enables it to be removed from the finished part.

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: An audible test device which provides a tone when a resistance being measured is less than a selected value, the selected value being variable to a few milli-ohms. A first or second source of voltage is applied to a constant current source. The constant current generated is divided between two paths, one path including test leads holding the resistance being measured therebetween, the other path through a voltage adjusting device. The output from the voltage adjusting device is applied to one input of a voltage comparator, the voltage appearing across the resistance under test being applied to the other input of the voltage comparator. The output of the comparator is applied to a voltage controlled oscillator (VCO), the output of the VCO being applied to a piezoelectric device and to a speaker operable only when the second voltage source is utilized, thereby generating an audible tone.

Abstract: A delivery system for multiple sub-missiles including in the sub-missiles a marking system, a detection system, a diverter for elimination of targets identified by the detector system, a scanner for initial determination of multiple targets, a logic circuit utilizing input from both the diverter and the scanner to eliminate targets and a sub-missile guidance system.

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: An improved work holder for use with a shearing or cutting machine is provided which includes a heavy tray stationary base, two or more spaced fixed upright supports secured to the base, cross-braced to each other and bearing aligned support brackets and a forwardly extending generally horizontal support arm slidably disposed in the brackets for reciprocating into and out of a workpiece supporting position within the machine between the machine's cutter and backstop. A forwardly extending handle is secured to the upper end of a vertical rod spaced laterally of the arm and secured thereto by a cross-bar. The lower end of the rod holds a rotatable ground traversing wheel, so that reciprocation of the handle reciprocates the arm into and away from the workpiece supporting position. A workman is able to manipulate the handle while a workpiece, such as a thin flat flexible sheet of metal, is in place in the machine for cutting.

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 low-loss fiber optic tap is fabricated by mounting a portion of an optical fiber with epoxy resin along the curved surface of a solid support form. After curing of the epoxy, a planar surface extending partially into and along the fiber is established by lapping and polishing the device to a carefully controlled depth. A prism having a preferred characteristic angle of 70.degree. is attached to the planar surface along the optical fiber and a photodiode is mounted adjacent thereto. The disclosure teaches how the parameters of the device may be tailored to the specific signal tap requirements of particular fiber optic transmission lines.

Abstract: A low-loss fiber optic tap coupler including an optical fiber mounted and adhered to a curved surface and having a clad single fiber core, a planar surface extending partially into and along the fiber through the cladding, a prism mounted on the surface having two reflective surfaces positioned to receive signals from the fiber travelling in opposite directions, and photodiodes mounted adjacent the prism to receive the reflected signals.

Abstract: Apparatus for holding an optical fiber, having both longitudinal and radial adjustment capabilities. The fiber is disposed in a tubular member having an end disc which secures one end of the fiber in an eccentric hole therein. The tubular member is disposed in an eccentric hole of a threaded collet. Relative rotation of the collet with respect to the end disc provides for radial adjustment of the end of the optical fiber. Axial motion of the tubular member within the collet provides for longitudinal adjustment of the fiber. A tapered nut provides for locking capability of the tubular member with respect to the collet. A particular embodiment of the present invention provides a means by which the optical fiber may be adjusted with respect to an optical system to allow optical energy to be focused on the end of the fiber.

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 delivery system for multiple sub-missiles including in the sub-missiles a marking system, a detection system, a diverter for elimination of targets identified by the detector system, a scanner for initial determination of multiple targets, a logic circuit utilizing input from both the diverter and the scanner to eliminate targets and a sub-missile guidance system.

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.