Abstract: 1.

Abstract: A guidance system for automatically boresighting a small field-of-view, lresolution image, sensed by an infrared missile imaging sensor, to a large field-of-view, high-resolution image, sensed by an imaging sensor located within an airplane. The image sensed by each sensor is applied to a digital correlator which makes a bit-by-bit digital correlation of the images. The image sensed by the large field-of-view aircraft sensor is monitored on a CRT. Cross-hairs are placed at the centerpoint of the area in the monitored aircraft sensor image which has the highest correlation with the missile sensor image. Thus the boresight of the missile sensor is ostensibly located in the monitored, aircraft, sensor image.This system may be used to slave automatically one sensor boresight to another. Where a plurality of missiles are carried by one plane, the boresight of each missile may be located in the large field-of-view aircraft monitor.

Abstract: Sodium hexahydroxy antimonate is added to powder and acts as a flash-reducing agent.

Abstract: A guidance system for a missile or other vehicle utilizing a gyro stabilized seeker which is arranged in such a manner with respect to the missile as not to be servo controlled, but rather to follow the missile air-frame by means of passive coupling between seeker and airframe, as the airframe is steered to turn in response to seeker error signals. As a result of this arrangement the missile velocity vector is steered to point toward fixed targets or to lead moving targets. A further result of this arrangement is that the servo loop used to point the seeker toward the target in the conventional arrangement is not required and accordingly my missile guidance arrangement can achieve greater accuracy with less complexity than in the prior art.

Abstract: A pyrotechnic signal cartridge comprising a cartridge case, a projectile e detachably secured to the cartridge case, a charge in the cartridge case for launching the projectile case, rocket motor thrust means positioned within the projectile case, a rocket motor propellant charge and a pyrotechnic signal charge in the projectile case, ignition means for the pyrotechnic signal charge and the rocket motor propellant charge whereby ignition of the pyrotechnic signal charge and the rocket motor propellant charge after launching of the projectile case provides a self-levitating pyrotechnic display.

Abstract: An air intake pressure unit is attached to the exhaust section of a jet ene. The unit comprises several passages which extend out beyond the end of the jet engine and through which passages engine exhaust and cooling air is passed so that cooling air passes over and mingles with exhaust gases from the engine. Construction is such that the lower static pressure formed by the exhaust gases assists in drawing in the cooling air.

Abstract: An industrial process and system are described for forming finished parts from powder metal. Known steps of compacting the metal powder into a preliminary part having an intermediate shape, followed by heating and forming the preliminary powder into a finished part having a final shape and density are integrated into a single automated process and system by steps and equipment which provide for a rearranging of a continuous flow of preliminary parts into separate batches at a sintering station so that the separate batches of the preliminary parts can be uniformly heated to a selected sintering temperature level. After sintering, the separate batches are removed from the sintering station and rearranged back into a flow of parts which can be conveyed to a final forming station. This arrangement provides for advantages in starting up and stopping the system in a typical industrial application.

Abstract: An infrared suppressor for use with an engine to receive the engine exhaust gases from the engine exhaust flange. Individual panels, cooled by a combination of convection and film cooling techniques, make up the suppressor. The suppressor may be configured as an axisymmetrical plug, a single or double rectangular scoop, or any number of other geometrics.

Abstract: A method for operating a nuclear reactor or any other machine or industrial process where it is of importance to terminate operation when a given parameter deviates from a variable operating value by more than a given amount regardless of the rate at which the deviation occurs. A variable setpoint is continuously generated from the past history of the operating parameter by adding the current value to a predetermined excursion margin whenever this causes the variable setpoint to decrease. The setpoint remains constant whenever the operating parameter is increasing so that a system trip is initiated whenever the setpoint is exceeded. The variable setpoint is permitted to increase to within the excursion margin of the operating parameter only when independent authorization is given indicating that the increase is legitimate.

Abstract: A nuclear reactor internals arrangement is disclosed which facilitates reactor refueling. A reactor vessel and a nuclear core is utilized in conjunction with an upper core support arrangement having means for storing withdrawn control rods therein. The upper core support mounted to the underside of the reactor vessel closure head so that upon withdrawal of the control rods into the upper core support, the closure head, the upper core support and the control rods are removed as a single unit thereby directly exposing the core for purposes of refueling.

Abstract: An inherent shutdown assembly for a nuclear reactor is provided. A neutron absorber is held ready to be inserted into the reactor core by a magnetic latch. The latch includes a magnet whose lines of force are linked by a yoke of material whose Curie point is at the critical temperature of the reactor at which the neutron absorber is to be inserted into the reactor core. The yoke is in contact with the core coolant or fissionable material so that when the coolant or the fissionable material increase in temperature above the Curie point the yoke loses its magnetic susceptibility and the magnetic link is broken, thereby causing the absorber to be released into the reactor core.

Abstract: A dual, side-mounted inlet for air-launched ramjet missiles that require h angle-of-attack capability. The inlets are located symetrically on both sides of the vehicle pitch plane at an optimum angular displacement around the vehicle's lower surface from windward side meridian, lying in the pitch plane. The inlet pressure recovery and relative weight flow reach maximum values at angular displacements between 45.degree. and 60.degree. at positive angles of attack. The inlet is attached to the vehicle with a conventional boundary layer diverter of minimum height.

Abstract: 1. An igniter adapted to be positioned in the convergent portion of the nozzle of a rocket engine, said igniter comprising, a tapered combustible plastic casing having a small end and a large end, said casing having a stepped recess therein comprising a large cavity formed in the large end of said casing and a relatively small cavity opening into the inner end of said large cavity, a squib including a primer charge positioned in said small cavity, a body of pyrotechnic material positioned in said large cavity adjacent to said primer charge, a closure disc positioned in said large cavity to hold said pyrotechnic material therein, and squib-activating means for igniting said primer charge, said activating means extending from said squib through said casing and out the small end thereof, the inner end of said small cavity and the small end of said casing being substantially spaced from one another to provide a substantial body of combustible plastic therebetween.

Abstract: A variable-geometry ramjet engine, capable of operation over the Mach 3 to 12 speed range, is provided by disposing a movable cowl around a centerbody. The engine is axisymmetric and features a translatable cowl which slides relative to the centerbody on circumferentially spaced radially extending support struts. Forward translation of the cowl provides a variable inlet area resulting in higher compression at the high Mach numbers than is possible with a fixed-geometry configuration. Rearward cowl translation increases the combustor length and combustor area ratio at the low flight Mach numbers to improve low-speed combustion characteristics. Cowl translation changes the nozzle area ratio to provide a large expansion ratio at high flight speeds and a low expansion ratio at the low flight speeds.

Abstract: A method is disclosed for preventing segregation of particles within a finely divided powder having disparate particle size ranges, compositions or densities. The method includes working the powder with a minute amount, preferably less than about 1% by weight of the powder, of a finely divided fibrillatable polytetrafluoroethylene resin (hereinafter referred to as PTFE) to form a mixture with the powder. The PTFE resin may be added to the powder as a colloidal aqueous dispersion or as a fine powder obtained by coagulation of the colloidal dispersion. Whichever form is used, the PTFE is intimately mixed with the finely divided powder to form a dry mixture. Alternatively, the PTFE resin may be blended with the powder in a wet treatment to facilitate the homogenous dispersion of the resin. In any event, the mixture of resin and powder is worked either in the wet state, preferably as a paste, or as a dry blend, using a masticating or kneading action to fibrillate the PTFE.

Abstract: An exhaust duct for a turbofan aircraft engine includes a bulbous inner cone which blocks direct sight of the turbine through the duct. Ram air from the fan is caught by scoops and conveyed from a plenum into the double outer wall of the exhaust duct and through hollow struts to the inner cone. Circumferential outlets for film cooling air are distributed axially of the surface of the outer and inner walls. Also, film cooling air is discharged from the struts to cool the rear part of the struts which are visible from without the engine. Direct radiation from within the cone to the outside is blocked by ribs extending into the inside of the inner cone immediately upstream of the cooling air outlets.

Abstract: A system for guiding a missile to a target is disclosed which includes a signal processor for generating error signals in response to a signal being received from the target. The processor includes four channels for receiving a target signal. An arithmatic circuit compares the amplitude of the target signal on each channel with the average amplitude of the other three channels and generates an error signal for guiding the missile.

Abstract: 1. In combination with a vessel forming a rocket motor combustion chamber, a rubber-base liner having one surface firmly adhering to the chamber, the opposite surface of said rubber-base liner having a plurality of discrete powder grains partially embedded therein, each of said powder grains having a portion extending from said opposite surface of said rubber-base liner, and a propellant charge substantially filling the lined portion of said chamber, said propellant charge firmly adhering to said liner and enveloping each of said extending portions of said powder grains.

Abstract: A process for the rapid production of a substantial volume of non-toxic gas at a moderate temperature, comprises:A. effecting combustion of a pyrotechnic charge consisting of a composite solid propellant having a high content of inorganic oxidant, in excess of 80 percent and a low content of a carbonaceous, non-nitrogenous binder, not in excess of 17 percent in a combustion chamber to produce a substantial volume of combustion gases at an elevated temperatureB. a first cooling phase in which the hot combustion gases are diluted with oxygen obtained by the thermal decomposition of an oxygen-containing inorganic compound which has a low thermal stability and liberates, in gaseous form, only oxygen, whereby the combustion gases are cooled to a temperature of from 225.degree. to 700.degree.C, andC. a second cooling phase in which the gas mixture from the first cooling phase is cooled by contact with cooling means to the temperature of utilization.

Abstract: A process for dyeing and printing textile materials made of or containing fully synthetic hydrophobic linear polymers which are free from amino groups, wherein the material is padded with a dispersion dyestuff containing at least one carboxyl group, the padded textile material is dried and printed with an alkaline printing paste, the fabric is thermo-fixed and the salt of the dyestuff containing a carboxyl group is subsequently washed from the printed areas.