Abstract: Pulse integration is utilized on board an optically guided missile or other ordinance device used as a part of a target designation system for extending the lock-on range of the missile by approximately 18%, when a double pulse laser is utilized to illuminate and designate the target. Pulse integration is accomplished with a recirculating delay unit which superimposes the first pulse on the second pulse, such that while the pulses add coherently, noise does not add in phase. The pulse integration technique therefore enhances the signal-to-noise ratio when the missile is at the outer limits of its operating range. When the missile is sufficiently close to the target, doublet decoding is actuated to offer countermeasure resistance. At this point, pulse integration may proceed in lieu of doublet decoding or may be dispensed with in view of the increased signal-to-noise ratio due to the close range of the missile to the target.

Abstract: Circuitry for adjusting the resonant frequency of an Yttrium-Iron-Garnet (YIG) filter in the first local oscillator of a receiver carried on a guided missile is shown to include the combination of a crystal oscillator which produces a pilot signal for tuning the YIG filter to a corresponding resonant frequency and a frequency adjusting arrangement for offsetting the resonant frequency of the YIG filter by a predetermined amount.

Abstract: A cannon launched guided projectile having a gyro based electro-optical target finding and guidance system which includes an optical system carried by a gyro to provide target location information for an electronic system to produce gyro rotor torquing signals and for producing projectile guidance signals from gyro pickoff outputs is disclosed. The electronics system includes two difference channels for processing pitch and yaw signals responsive to the electrical output of a light detector and a sum channel for controlling the two difference channels responsive to target acquisition and master trigger signals.

Abstract: A motor brake control system for use on a motor having a motor brake retarder and a throttle fuel control is designed to respond to manual selection for sequentially retarding the selected cylinders in the motor. A transducer for sensing the speed of the motor is provided for generating a series of output pulses which access a high RPM detector and a low RPM detector. In the event that the motor exceeds a predetermined high RPM value, the brake control system activates all of the retarders to fully brake the motor. In the event that the brake retarders are on, either fully or partially, and the motor drops below a predetermined low RPM value, the brake retarders are released. Provision is made to prevent retardation of the motor as long as the throttle of the motor is being activated and retardation is further prevented after deactivation of the throttle until the fuel in the fuel delivery system has been consumed.

Abstract: A weapon system using a line of sight guidance system is provided with a missile containing two symmetrically located optical receivers. Information contained in a beam into which a missile is launched is used by the two receivers and associated processor means to derive roll position for the missile. Because the roll signal is derived electronically, mechanical means for determining roll position of the missile in the form of a conventional roll gyro, for example, may be eliminated. Elimination of the mechanical roll gyro from the missile permits much higher launch accelerations than are realistically feasible with missile control systems employing mechanically derived roll data. A processor located in the missile receives its signals from the pair of optical receivers. The processor uses the data from the first receiver to derive the position error of the missile relative to beam center.

Abstract: Diesel fuel injection system in which a standing high-pressure wave is maintained in the common rail and which utilizes injectors which function as gates or valves. Electronic controls sensitive to engine demands based on speed and load electronically control the injectors to vary both moment and duration of fuel injection time. Input signals, as determined by engine speed by way of the distributor, vary the injection timing according to an advance curve at the distributor correlated to piston position. Duration of the injection cycle (quantity of fuel injected) is controlled electronically and variably in relation to throttle position.

Abstract: In the art of motor fuel carburetion where conventional carburetors are employed to mix and prepare the fuel/air mixture for introduction into the combustion chamber of internal combustion engines, and particularly where gasoline is used as fuel, the liquid fuel is sucked, or aspirated out of the provided discharge opening by the current of intake air as it flows past this opening, thereby presumably mixing and preparing the fuel/air charge.In this invention the method of mixing liquid fuel with air employs a liquid fuel delivery spray valve which is so located as to spray liquid fuel upon an electrically heated metal plate which instantly converts the fuel from its liquid state into vapor form; a water delivery spray valve which is so located in similar fashion as the fuel delivery valve described above, to moderate the explosive violence of high octane fuel in the combustion chamber of internal combustion engines; and an electrically heated porous screen to atomize the fuel/air/steam mixture charge.

Abstract: Minesweep gear is suspended from an aircraft to be a selected height above the surface of the water for deployment and the sweep gear is selectively stowed within the container so that the sweep gear is selectively sequentially deployed with the sweep equipment which is to assume a position farthest from the towing aircraft being deployed first and the sweep equipment which is to assume a position closest to the towing aircraft being deployed last. The sweep lead wire is connected to the aircraft towing cable and, by remote control from the aircraft, the sweep gear can be so selectively deployed and thereafter towed by the aircraft, the container being jettisoned once the gear is deployed and the sweeping gear being jettisoned at the end of the sweeping operation.

Abstract: A method for guiding a flying vehicle having a light receiver by directing a spirally scanning beam at the light receiver. A repetition reference time of the scanning of the light beam is stored in the flying vehicle before it is launched. After the flying vehicle has been launched the radiation angle of the spirally scanning light beam is controlled according to the lapse of time after launching of the flying vehicle so as to maintain a scanning area of the scanning light beam on the light receiver constant. In flight, the flying vehicle is guided so as to be on the center of the light beam according to information on a displacement of the flying vehicle from the center of the light beam and information on a displacement angle from a reference axis of the light beam determined from a period of time during which the light receiver receives the light beam.

Abstract: A fuel supply system for engines having a carburetor which has a float chamber and a vapor bleed passage connected to the float chamber, wherein a part of a fuel supply passage means for supplying fuel from a fuel tank to the carburetor traverses through the float chamber so that the fuel flowing through the fuel supply passage means absorbs heat from the fuel contained in the float chamber. The fuel entering into the float chamber releases volatile light components as vapor towards the vapor bleed passage while the liquid fuel contained in the float chamber becomes a more stable liquid due to the release of volatile components and the cooling effected by heat exchange with the fuel flowing through the fuel supply passage means.

Abstract: A marine vessel whose hull consists of a single skin bottom plating comprising a plurality of large area membrane members supported by structural members about their outer periphery only and being of low areal density so as to deflect rapidly and substantially in response to the force of the shock wave of an underwater explosion without permanent deformation and whose personnel and machinery compartments are supported from hull structural members, such as bulkheads, solely by shock absorbing mounts.

Abstract: An acoustic homing torpedo which has an acoustic window and a nose section with the window-torpedo shell interface being positioned at a location aft of the acoustic transducers in the nose so as to minimize unwanted flow noise.

Abstract: A method of stopping out interfering radiators in a device for optically viewing the radiation produced by a missile through a lens aperture and for steering the missile as a result of the radiation viewed, comprising setting the opening of the lens aperture in a wide opening position during the launch of the missile and viewing the radiation through the opening set, determining the off position of the missile relative to the optical axis of the device by means of a modulator disc disposed in the image plane of the device and a radiation detector which is disposed behind the image plane on which the image of the entrance pupil of the device is formed and, after the off position is determined, reducing the image field of the lens of the device to an image area immediately surrounding the missile.

Abstract: A body is provided which consists of several discrete portions at least on one portion of which is spin stabilized. Mechanism is carried by the body for generating a signal having a frequency proportional to the spin frequency of the spin stabilized portion of the body, together with means responsive to the signal for precessing at least a portion of the body. The signal for precessing the portion of the body can apply cyclically phased impulses correlative to the spin of the body to precess the body.

Abstract: A free spinning gyroscope is provided which has a spin axis, together with precession means for precessing the gyroscope. In addition, means are provided for deflecting an electromagnetic field of energy and adapted to generate a signal indicative of misalignment of the gyroscope spin axis with the electromagnetic field of energy. Mechanism is further provided for utilizing an unresolved signal for directly controlling the precession means to maintain the gyroscope spin axis in alignment with the electromagnetic field of energy.

Abstract: A fiber optical transmission system for guiding and controlling a missile. he fiber optic link can provide for up and down link transmission that can provide target and reference position information not available to present wire guided missile systems. Fiber optics have an almost unlimited information transfer rate and does not have the electrical interference problems of the wire systems.

Abstract: An electronically-controlled fuel injection system includes electromagnetic fuel injection valves each of which is mounted in each cylinder of an internal combustion engine, and the injection of fuel during the starting period of the engine is also effected only by these fuel injection valves. During the starting period of the engine, the duration of the opening of the fuel injection valves is controlled at a constant value irrespective of the rotational speed of the engine until the rotational speed reaches a value corresponding to the initial combustion of fuel in the engine, after which the duration of the opening of the fuel injection valves is controlled in relation to the rotational speed of the engine.

Abstract: Various embodiments of optical apparatus incorporating a foraminous plate to define a field of view are disclosed. In a first embodiment, the foramina in a foraminous plate are cylindrical with the field of view defined by the ratio of the diameter of each foramen to the thickness of the foraminous plate. The presence, or absence, of a target within the field of view is determined by the electrical signal out of a photodetector actuated by light passing through the foramina. In particular, embodiments illustrating the use of the disclosed optical apparatus as a sensor in a guided missile, the foraminous plate and photodetector are movably mounted in such a missile to allow either bearing or range of a target to be determined.

Abstract: A device for guiding by night self-propelled missiles, comprising a daylight sighting telescope and an infrared goniometer which in association are called here daylight localizing apparatus, for spotting an infrared source carried by the missile, and a thermal telescope for night vision, to which are associated an infrared detector and a display member, further comprising a thermal reticle, optical means for forming outside the daylight localizing apparatus the image of the daylight telescope reticle, means for shifting the daylight telescope reticle image so that it coincides with the thermal reticle, optical means for forming the thermal reticle image on the thermal telescope detector, and an adequate frame mechanically attached to the daylight localizing apparatus for supporting said means, said thermal reticle, the thermal telescope and its associated detector and display member.

Abstract: An automatic takeoff control system for hydrofoil craft characterized in that the control surfaces of the craft are caused to automatically assume predetermined positions during takeoff, obviating the necessity for special levers, lever settings and special operator procedures which were involved in making a transition from hull-borne to foil-borne operation in accordance with prior art techniques.