Abstract: A lateral thrust assembly for missile maneuvering comprises an annular array of outwardly directed nozzles, each nozzle having a releasable plug normally blocking flow of propellant gases out of the nozzle. A plug release mechanism associated with each plug allows that plug to be released to open the respective nozzle. A combustion chamber containing propellant is connected to the inner ends of all the nozzles. The propellant is ignited when one or more selected plugs are released to allow opening of the associated nozzle or nozzles, controlling the direction of the lateral thrust applied to the vehicle.

Abstract: A helium purification system for use with lighter-that-air airships has a catalytic purification stage for removing oxygen from the lift gas, and if desired, a nitrogen removal stage. Impure lift gas is passed through the catalytic purification stage which includes catalytic means for reacting hydrogen and contaminating oxygen entrained in the lift gas to form water and liberate heat energy. The catalytic reaction of oxygen and hydrogen increases the lift capacity of the airship both by removing oxygen from the lift gas which can then be replaced with additional lift gas and by heating the lift gas. The lifht weight catalytic purifier requiring no external power makes practical an on-board lift gas purifier to scavenge oxygen from the lift gas as soon as it enters the aerostat whose only cost of operation is that of the hydrogen consumed.

Abstract: A drumlike canister onto which a filament is wound is rotatably mounted to an airborne vehicle, the axis of rotation being generally parallel to the vehicle longitudinal axis. At launch, as the filament unwinds and is payed out the canister is rotated to remove the twist from the filament produced on winding.

Abstract: A device for ignition of a pyrotechnic material, comprising:(a) piezoelectric means for providing a high voltage electrical pulse in response to mechanical energy;(b) means for emitting a flash of light in response to the high voltage pulse; and(c) a solid state laser capable of emitting a light beam sufficient to ignite a pyrotechnic material in response to said flash of light;and a process of igniting a pyrotechnic device using the same, are disclosed.

Abstract: A filament (20) for use as a data link is wound on the tapered aft fairing (22) of a missile (10) in a manner so as to form a tapered wound pack (24) conforming generally to the aft fairing. An outer length of the filament is enclosed within a protective covering forming a leader (26). When the missile is launched from a moving mother vehicle (36), a further length of the filament is wound onto a dispenser aboard the mother vehicle (36) and a drogue (30) connected to the leader (26) is released with the leader and filament during dispensing.

Abstract: A mechanism for upgrading a missile to be effective against reactive armor. The invention includes an adaptor (11) for mounting a probe module (10) with a warhead (13). The probe module has a charge in its extensible tip. A faring (12) over the five inch warhead reestablishes the aerodynamics of the missile.

Abstract: Improved apparatus for providing control signals to a warhead in a guided missile is shown to comprise a plurality of optical radars that produce overlapping beams to form a conical coverage pattern and logic circuitry responsive to the signals processed in the receivers of the optical radars to produce control signals indicative of the sector of the conical coverage pattern in which echo signals have originated.

Abstract: A high speed aircraft fitted with a unitary, rotatable wing coupled to the craft's fuselage at a hollow turret or solid pivot pin, enabling it to operate with the wing in either of two ninety degree opposed positions.

Abstract: One-dimensional sun sensing and angle measurement assemblies are deployed with substantially totally overlapping fields of view on a plane of a spacecraft body to protect sensors within a protected angular area of the plane, each of the analog sun sensors generating a signal indicative of incident sun along one axis and the presence of sunlight along an orthogonal axis thereto in the common plane. The sensors together generate an indication of the orientation of the sun relative to a target field of view which is a protected area. In an alternative embodiment, a digital sun sensor assembly is provided consisting of two or more independent digital channels and employing a slit aperture cooperating with a plurality of photocells laid out in a gray coded pattern. The digital device produces digital signals indicating relative position relative to axes in a plane.

Abstract: A multi stage high-altitude data acquisition system comprising a first stage manned lighter-than-air, engine propelled aircraft and a second stage air-buoyant vehicle of stratospheric altitude attaining capability statically sustainable aloft by a sufficient quantity of lighter-than-air gas contained within an expandable envelope balloon to carry the vehicle to a stratospheric float altitude and transportable from ground level to a tropospheric launching altitude by the first stage aircraft from which the air buoyant vehicle and its partially expanded gas containing envelope is releasable at the launching level while the first stage aircraft is established in a flight condition of substantially zero airspeed.

Abstract: A hybrid laminar flow nacelle for housing an engine of an aircraft includes an outer annular cowl having a leading lip and radially spaced and axially extending annular outer and inner forward surface portions which merge at the leading lip. The nacelle incorporates a suction bleed system between the surfaces and a tailored outer surface geometry shape for producing reduced friction drag laminar flow over the outer cowl at cruise operation of the aircraft and producing separation-free flow over the inner surface of the cowl at off-cruise operation of the aircraft.

Abstract: A proximity fuzing system includes a passive proximity detection section including an electrostatic probe for detecting initial missile entry into the electric field inherently associated with an airborne target. Probe signals are processed to determine that the intercepted electric field is characteristic of a valid target, and, if so, an active proximity detection section, such as a radar proximity detector, is rendered operational to trigger a warhead detonator at the optimum point in the missile's engaging trajectory to inflict maximum possible damage on the target.

Abstract: A drive system is provided between a ram air turbine (10) and at least a pair of accessory power units (38,40) of an aircraft, the ram air turbine being movable between stowed and deployed positions relative to the fuselage of the aircraft. The problems of providing a compact lightweight design which eliminates extraneous components in the airstream and a system which operates at optimum speeds are solved by the use of a drive shaft (28) extending between the ram air turbine and a first accessory power unit (38), such as a hydraulic pump, within the aircraft fuselage. First gears (30, 34) rotatably couple an outer end of the main drive shaft to the ram air turbine. Second gears (36,48) rotatably couple an inner end of the main drive shaft to the first accessory power unit. Third gears, in the form of a gear train (54), rotatably couple the first accessory power unit to a second accessory power unit (40), such as an electrical generator, within the aircraft fuselage.

Abstract: A radar seeker transient suppressor for an anti-radar homing missile in which glint effects upset the smooth tracking of a target by apparently changing the target position spasmodically. A seeker output signal is derived which is at least substantially independent of body movement e.g. the target sightline angle signal rather than the look angle signal (i.e. relative to a space reference rather than a body reference). This signal is used to control the steering either filtered or unfiltered according to whether the difference exceeds a threshold value or not. Both azimuth and elevation channels are treated similarly and in unison. An excessive filtered/unfiltered difference in either channel causes use of the filtered signal in both. A double integrating filter may be employed to avoid the relative displacement of output and input signals when the input is, or contains, a ramp component.

Abstract: A backdrive system is provided for aircraft flight control surfaces, including a motor for driving a control surface. A fluid pressure responsive engaging/disengaging device is operatively associated between the motor and the control surface. The device may be a clutch normally engaged in the absence of to supply pressure or a brake normally disengaged in response to supply pressure. A supply of fluid pressure is connected to the device. An accumulator is connected in-line between the fluid pressure supply and the engaging/disengaging device for storing hydraulic energy during normal operation of the system and for releasing the stored hydraulic energy for at least a given period of time in the event of loss of supply pressure to allow the control surface to backdrive to a neutral position. A check-valve is provided between the fluid pressure supply and the accumulator to prevent return of hydraulic energy from the accumulator supply of fluid pressure when the supply pressure is lost.

Abstract: An adapter brace device (10) for removably fitting onto one end of a policeman's side handle baton (12) for bracing a handgun while the baton itself is used as a shoulder stock. The adapter device includes a round, plastic body portion (14) with an inner end (16) and an outer end (18). The inner end (16) of the body (14) includes a recessed opening (20) and the outer end has a cradle portion (28) which angles upwardly and outwardly and which cradle portion has a concave depression (26) for receiving the back edge of the grip of a handgun (G). The adapter brace fits on to the end of the baton as shown.

Abstract: A fixed wing aircraft that can be converted to an automotive vehicle, comprising a generally rectangular planform fuselage having four wheels as in conventional automobile practice, and a telescopic wing which retracts into a housing in the roof of the fuselage. Telescopic horizontal and vertical stabilizers are provided at the rear end of the fuselage, as well as a retractable pusher propeller that is driven by an engine mounted on the front end of the fuselage. Both the propeller and the rear wheels are connected by a transmission box to the engine, so that either can be driven to operate the vehicle as an aircraft or as an automobile. On take-off, the rear wheels are partially retracted so as to place the aircraft at a proper angle of attack at the same time that the elevators are raised by pulling back on the control wheel. The control wheel is also connected to both the front wheels and the ailerons, and when turned 90.degree.

Abstract: In the field of blasting, it is often desirable to ignite explosives at various relative times. Such delayed ignition can have advantages in better break up of rock and reduced ground vibration. A principle problem in using the time delay technique is the accuracy rate of a local oscillator which measures the delay time for each of the delay circuits. In the described system, a calibration interval, independent of any delay time, is transmitted from a control unit concurrently to each of the delay circuits wherein each delay circuit counts the output of its local oscillator during the calibration interval. This local oscillator output is then compared to a predetermined reference count, either at the delay circuit or at the control unit, and a correction factor is established. This correction factor is then applied to a delay count for the individual delay circuit.

Abstract: An ejector seat device for aircraft includes a support structure which is adapted to be mounted in an aircraft and which can be ejected in an emergency, a seat connected to the support structure, a harness system which is capable of keeping a person in the seat and which comprises a recall device to immobilize the person in a suitable position at the moment of ejection, at least one pyrotechnical catapult capable of ejecting the support structure and the seat, together with a person sitting on the seat, out of the aircraft, a device for at least weakening the aircraft canopy by shock wave, a control handle, and an initiator connector to the handle for transforming a pull on the handle into a pyrotechnical signal. The pyrotechnical signal from the handle is transmitted in the form of a shock wave to the harness recall device and to the catapult.

Abstract: A subcaliber, spin stabilized, discarding sabot projectile of the type including a projectile body, with a conically tapered tip, and a discardable sabot which completely encloses said projectile body and includes a base portion and a plastic hood portion connected to the base portion, and with the hood portion having an inner conical surface which contacts at least a portion of the conically tapered tip of the projectile body and being provided, on its circumferential surface, with a plurality of symmetrically disposed grooves which extend in the longitudinal direction of said projectile and form desired break locations along which the hood portion tears open into a plurality of segments after firing from a weapon and after the projectile has left the weapon muzzle.