Abstract: A nozzle assembly capable of controlling the hot exhaust gases which flow om the burning solid rocket propellant.

Abstract: A method of pulse-width modulation for operating oppositely aligned thrus valves of an integrated valve assembly in an aerospace post-boost control system in which zero average thrust during a modulation period is provided by commanding the thruster valves to be simultaneously on for a selected portion of the modulation period and simultaneously off for the rest of the modulation period. Non-zero average thrust is provided by varying the simultaneous operation of the thruster valves established for zero average thrust by commanding an increased on-time for one thruster valve while commanding a correspondingly decreased on-time for the other thruster valve, the excursions in on-time and in off-time occurring around the zero-thrust turn-on time or the zero-thrust turn-off time.

Abstract: A method for compensating for pre-reentry errors generated by the weapon ivery system to provide a reduced impact range error dispersion over that provided by a ballistic trajectory after reentry comprising maneuvering the reentry body after reentry so that the terminal flight direction is essentially in line with the line of means of the reentry body's position-error ellipse that exists just prior to reentry. The reentry body trajectory follows a sequence of a ballistic leg from reentry, a dive maneuver including an optional pullup leg and a pulldown leg to establish the required terminal direction, and a terminal ballistic leg to impact. The required maneuvering is accomplished by modulating the aerodynamic lift of the reentry body by controlling the reentry body's roll orientation.

Abstract: A method of providing an angular rate signal for attitude control in a mile flight control system by linearly mixing a derived rate signal generated from the measured attitude angle and a simulated rate signal generated from the measured nozzle angle. The derived rate is generated from the differentiation of missile attitude data and the simulated rate is generated by simulating the missile attitude dynamics based on the actual nozzle angle. The derived rate, which is filtered to remove the effects of quantization and noise is dominant at low frequencies. The simulated rate, which is filtered to block low frequencies, is dominant at higher frequencies.

Abstract: An antenna for providing a broadband omnidirectional circumferential radion pattern is formed by an array of arcuate waveguide radiators arranged to form a cylindrical antenna. Each waveguide radiator has a ridged waveguide cavity and a plurality of longitudinally-oriented slots communicating with the waveguide cavity. The slots are arranged in two parallel rows on either side of the longitudinal centerline in a staggered relationship along the outside surface of the radiator. Each radiator is fed from the interior of the cylindrical array at a feed point located at the center of the radiator.

Abstract: A method of bonding propellant to the insulation in a motor chamber by use f an adhesive and powder granule layer.

Abstract: A thrust nozzle of the hollow-cone type affixed to a stationary shell having external insulation on the nozzle and the shell and the nozzle having a liner extending beyond its edge and having insulation over the extended portion.

Abstract: An explosive separation system for making a clean cut in composite laminate aterials in which a flexible linear shaped charge is maintained in a molded holder of a low-density, energy-absorbing material. The flexible linear shaped charge is molded in the holder when the holder itself is molded to ensure correct alignment of the charge and a correct standoff distance from the surface to be cut. The holder has sufficient volume to dissipate reflected explosive forces to reduce secondary damage to the cut edges and to areas adjacent to target area.

Abstract: Explosive separation apparatus in which a LSC is supported by a plurality narrow preform supports which provide intermittent support at predetermined positions to maintain the LSC at the required standoff and perpendicularity to the target. The orientation of the supports themselves is maintained flat against the missile skin by a properly sized tunnel in the backup ring. The supports have a channel which maintains the LSC in the required orientation and standoff. A slot in each support below the liner walls of the LSC eliminates any obstruction from the support between the LSC and the target. The supports are maintained at the required spacing by a wire lanyard system which also allows the support system including the LSC to be installed in or removed fron a backup ring without applying any longitudinal forces to the LSC itself. A Venturi Plate provides a dual target to prevent delamination or splintering when cutting a target of composite material.

Abstract: A variable energy missile eject system in which the rate at which cooling ter is injected into the hot gas flow from a solid propellant rocket motor may be varied to optimize the eject energy according to launch depth. A first set of injection apertures through which water is always injected provides the necessary cooling and establishes the minimum rate of water injection (maximum launch energy). Additional sets of injection apertures having varying numbers of apertures are individually controlled to allow the water injection rate to be increased by increasing the number of injection apertures.

Abstract: A stowage rack unit consisting of a plurality of upright stanchions to prde a basic rack framework. The rack includes upper clamps and collars to restrict upward and horizontal motion of the projectiles. The collars have a two-piece threaded arrangement which allows adjustment to accommodate minor variations in projectile length. Lower clamps are provided for additional restraint against horizontal motion of the projectiles. Base plates are provided to support and restrict downward motion of the projectiles and side channels receive and secure the clamps and base plates. Additional special brackets are provided for attaching racks to bulkheads or for joining adjacent racks. To load the rack, side channels are attached to the stanchions and base plates are inserted into the lower pair of side channels and secured with pins. Individual upper and lower clamps are inserted into upper and middle side channels respectively and secured with pins.

Abstract: Electric power for a missile during flight is provided by a solid propell gas generator coupled through a magnetically-controlled gas flow diverter valve to drive an axial flow impulse turbine. The turbine is coupled to drive an alternator which produces ac power which is conditioned to supply all the electric power for the missile. The frequency or voltage of the alternator output is sensed and fed back to the speed control circuit where it is compared to the desired value of the chosen parameter. The speed control circuit modulates the glass flow valve to adjust the flow to the turbine to drive the turbine the required speed.

Abstract: A low burn rate motor propellant containing hydroxyl terminated polybutade, HMX and hexanedioldimerate polymer.

Abstract: A thermoelectric cooler control circuit for a laser diode that has its terature regulated by a thermoelectric cooler and its temperature sensed by a laser diode temperature sensor. The purpose of the control circuit is to regulate the thermoelectric cooler to maintain the laser diode at a constant temperature. The output of the laser diode temperature sensor is amplified and compared to a reference voltage in an integrator. The output of the integrator controls a pulse width modulator that controls a switching transistor that varies the pulse duration of power applied to a filter network. The power output of the filter network is applied to a mode controller that is controlled by the output of the integrator so that the mode controller switches the direction that power is applied to the thermoelectric cooler to maintain the temperature of the laser diode at a constant level.

Abstract: A system for reducing the shock and vibration transmitted to a missile dug transportation, stowage or launch. Rings of segmented shock-absorbing pads are disposed along the launch tube in the annular space between the missile and the tube. These pad segments are unitized by a circumferential tensile fiber hoop connecting the pad segments, and portions of this unitizing hoop are used to form control loops between these pad segments. The loop characteristics may be selectively varied to control the effective modulus and circumferential length of each unitizing hoop thus varying the force/deflection characteristics of the pad ring.

Abstract: A fuel cell operable by two gas generators which produce hydrogen and oxy by oxidation and reduction of hydrogen and oxygen containing salts respectively.

Abstract: A launching structure comprising a ram driven by a piston in a cylinder. A yrotechnic charge initiates a gas expansion underneath the piston and the expanding gases drive the ram. The ram has a helical groove engaged by a cam pin in the cylinder wall to impart a rotary motion to the ram as it is displaced linearly in the cylinder. A mass is engaged by the ram and is ejected from the cylinder with both a linear and rotational velocity.

Abstract: An apparatus and method for spraying molten metal that is light weight, requires low maintenance and is quick and simple to operate. A feed system is provided that uses an electric motor and control system to push the electrodes to the head and to prevent system failure, by temporarily stopping the feed, upon the occurrence of the feed wires becoming shorted or welded together. A portable head is provided that employs parallel lead guides that allows complete head manipulation without electrode mismatch. An atomizing gas nozzle is also provided that permits lower air pressure and compensates for arc wander. A lead system is provided that combines into one lead the feed wire guides, current leads and the atomizing gas. The atomizing gas also becomes a cooland allowing lighter current leads for arc metal spraying.

Abstract: A modular improved forward section and improved aft section containing an tive-control package are disclosed which can be retrofitted to existing sphere-cone geometry reentry bodies (RBs) and which will provide improved aerodynamic performance and deployment accuracy of the RBs independent of missile error sources and drop sequence. An aft section containing control electronics, a propulsion system and steering jets permits the improve RB to actively correct for attitude and velocity dispersions occurring throughout the flight profile.

Abstract: An optical alignment sensor capable of receiving radiation from a collima light source and subsequently providing orientation attitude and alignment data. Collimated light from the source impinges an aperture plate causing a shadow of the aperture plate pattern to fall across a two-dimensional photodetector array. Since the aperture pattern is larger than the active area of the array, only a portion of the light spots forming the aperture plate pattern will fall on the array. By varying the spacing of the apertures in the aperture plate in a known way, the light spots on the array can be associated with specific apertures in the aperture plate. From the location of specific light spots on the array, the angular orientation of the alignment sensor may be determined with respect to the incident beam.