Abstract: A monitor connected to an automotive engine, suitably monitoring pulses in the ignition system thereof electronically, and a flyball-type governor connected to the final drive train of an automotive engine transmission driven thereby, respectively operate switches for independently causing an engine-throttle-closing fixed-rate drive to run in throttle-closing direction to override the manual throttle control whenever the engine exceeds a predetermined engine speed or the vehicle approaches or exceeds a predetermined vehicle speed. Whenever both engine and vehicle are below their respective predetermined speeds and the vehicle speed is neither constant nor accelerating in the aforementioned approach range, the unoperated switches cause the throttle drive to run in throttle-opening direction to allow, but not to cause, full-throttle operation, which may be achieved by operating the manual throttle control to open the throttle to obtain full power.

Abstract: A method for eliminating boresight error in a beamrider missile guidance tem wherein moving parts may disrupt alignment of a nutated beam. Periodic strobing of a light emitting source directs beams of light to form an optical reticle which may function as either the boresight alignment check source or as the telescope aiming reticle.

Abstract: A system for enabling homing by a missile onto a target which is marked by beacon at some other location. A radio frequency beacon is located remotely from the intended target. Target coordinates relative to the beacon are obtained and relayed by conventional means to the launch site and are stored in missile memory. During flight the missile seeker acquires, interrogates and tracks the beacon. The missile borne equipment generates guidance signals which alter the trajectory to the target location.

Abstract: A control system for hydrofoil craft is one in which control surfaces are moved automatically in response to signals derived from the motion of the craft to stabilize and control the craft. In such systems, a potentially dangerous condition can occur in case of a failure or malfunction in the roll control system. In order to prevent such conditions, two redundant roll sensing devices are provided which normally generate identical signals to actuate the control surfaces to stabilize the rolling motion. In case of a failure or malfunction, the signals provided by the two sensing devices become different. When this occurs, all normal control signals to the control surfaces are terminated; and secondary feedback loops act to position all control surfaces to smoothly land the craft.

Abstract: This invention relates to a valve for use in the automatic control of a vehicle and which may conveniently be powered from a vehicle speed monitoring electronic system. It is essentially a solenoid operated valve for vehicle control comprising a hollow body of non-magnetic material having an inlet and an outlet axially aligned with each other, valve seats at the inlet and outlet, a piston of magnetic material slidable in said body between positions closing the opening through either one or other valve seat, and a bore through the piston and in communication with a normally open outlet from the body. A considerable constriction is provided between the piston controlled inlet and the outlet from the body. The normally open outlet is suitable for connection to a vacuum operated servo-mechanism, the piston controlled outlet is suitable for connection to the vehicle engine vacuum line and the inlet is open to ambient atmosphere.

Abstract: An apparatus for correcting the terminal portion of the ballistic trajectory of a projectile. The projectile is initially fired at a target in a manner to cause the projectile to rotate in flight. At least one detector is mounted on a front surface of the rotating projectile to rotate with the projectile and scan the target area in a spiral pattern. A laser beam is directed to hit the target and a reflected portion of the beam energizes the scanning detector. The energized detector transmits an ignition signal to activate a trajectory correction motor and an associated nozzle having a plug that is weakened in response to the signal. The activated motor operates during the terminal portion of the trajectory to generate a thrust pulse that is passed through the nozzle having the weakened plug. The thrust pulse is directed by the nozzle to correct the trajectory of the projectile.

Abstract: A missile is guided onto a target by means of a laser beam, so that the missile can determine and correct its displacement from the boresight of the laser beam. This leads to greater accuracy of guidance, and avoids the need for very narrow beams which could be lost by the missile.

Abstract: A mixture-compressing internal combustion engine with a combustion space arranged either in the piston or in the cylinder head and with an ignition source located in the cylinder head; the main volume of the combustion space is thereby delimited by circular arcs, as viewed in plan view, of which the circular arc located closest to the ignition source is arranged at least approximately concentrically about the ignition source; a part of the piston which is matched within this area of the cylinder head adjoins the ignition source so closely that at first a smaller portion of the charge is ignited in the gap which is formed between the cylinder head and this piston part shortly prior to the end of the compression stroke while the main portion of the charge is combusted, at the earliest, beginning with the upper dead-center position of the piston.

Abstract: An electronic ignition timing system for an internal combustion engine which rotates a crankshaft is disclosed. The ignition system comprises a plurality of variable engine condition sensors which produce corresponding analog output signals and a crankshaft position sensor. A timing control logic circuit periodically multiplexes each of the variable engine condition sensors such that they are sequentially connected as inputs to an analog to digital (A/D) converter which produces an output signal comprising a pulse train for each of the multiplexed engine conditions. The total number of pulses in each pulse train is related to the magnitude of the variable engine condition currently being connected to the A/D converter. In addition, high resolution crankshaft position pulses are produced, preferably by an electronic angle divider which receives coarse crankshaft position pulses and produces high resolution crankshaft position pulses.

Abstract: A missile guidance system is provided in which a sensor is pivotally mounted on the missile in a gimbal system having two degrees of freedom. The sensor is controlled during flight in such a manner that the axis of the sensor is aligned in a direction determined by the acceleration of the missile, and the sensor locates the target and determines the angle between the direction of the sensor axis and the direction of the target. Guidance information is derived from this angle for directing the missile toward the target. Compensation for gravity may be provided by means of a spring suitably arranged in the gimbal system. The sensor system may be either active or passive and may be responsive to any desired type of signal from the target.

Abstract: A pilot fuel injection system for a diesel engine. One embodiment of the system includes a high pressure fuel pump, an accumulator, a mechanical fuel distributor, a pair of fuel metering valves for each cylinder of the engine, a fuel injection nozzle for each cylinder, and an electronic logic for controlling actuation of the metering valves; in a second system embodiment a pair of the metering valves supply fuel to all of the engine cylinders. Several embodiments of the metering valve are disclosed, some of which allows exclusion of the mechanical fuel distributor from the system. All of the disclosed metering valves meter fuel from the pump to the nozzles by traversing a passage in a valving member across another passage. Motion is imparted to the valving member by electromagnetic means which are energized by the electronic logic. The logic is responsive to engine speed and throttle position.

Abstract: An ignition system for an internal combustion engine is described, including an ignition timing control apparatus which is useful for cleaning the exhaust gas and saving fuel, which ignition timing control apparatus is controlled by first, second and third control signals in which the first control signal represents the rotating speed of a crank shaft, the second control signal represents the value of the negative pressure in an intake manifold and the third control signal indicates that the internal combustion engine is idle.

Abstract: A fuel injection pump for internal combustion engines includes a reciprocating and rotating pump piston. Fuel delivery to the pressure line connected to an injection valve can be interrupted by the opening of a main control orifice in the wall of the cylinder which permits fuel to return to a low pressure volume of the pump. In order to provide for pressure relief of the pressure line when no injection takes place, there are provided a pressure control valve and a pressure relief conduit which bypasses this valve. The pressure relief conduit terminates in an auxiliary control orifice in the wall of the cylinder and is also obturated by the piston during its motion. The two control orifices are so located as to be opened in a predetermined sequence. The piston surface includes portions which block the auxiliary control orifice during engine starting.

Abstract: A method of improving the guiding of reaction driven flying bodies for ground-to-ground utilization and a device for practicing the method in which the distance between a target point and a launching point is determined, as by observation, and a flying body such as a rocket is launched from the launching point while the flight thereof is controlled in conformity with the position of the flying body which latter is determined by detecting radiation given off by the reaction drive of the body. The path of the flying body is controlled so that, upon launching the body from the launching point, the path of the body diverges upwardly from a line joining the launching point and target point and then converges with the line and then follows the line to the target point.

Abstract: An inductance fuze for armor defeating shells and missiles that utilizes ped neutralization, i.e., cancellation of an AC voltage, induced by a primary coil in a sensing coil under free-space conditions, by an equal and opposite voltage. The lumped neutralizing voltage is obtained from a neutralizing coil that is also coupled to the primary. Adjustment of neutralization is made by translating axially either the sensing coil, the neutralizing coil or both relative to the primary coil. The physical configurations of the coils can be adjusted to be accommodated within the fuze ogive as long as a certain relationship involving the number of turns and the flux amplitudes is maintained.

Abstract: The present invention relates to fuel injection device characterized by comprising a main body having an axial cylindrical bore, a fuel supply port, a plurality of fuel metering ports, and a plurality of fuel distributing ports communicating with said fuel metering ports; a rotor having an inlet port communicating with said fuel supply port in said main body, a single metering port associated with said metering ports in said main body, and a hole communicating with said two ports; means for driving said rotor for rotation in synchronism with the rotation of an engine; control means for axially sliding said rotor in unique association with the amount of suction air; and fuel supply means for supplying fuel to the fuel supply port in the main body through a pressure regulating valve, the arrangement being such that the length of time for communication between each metering port of the main body and the metering port of the rotor is controlled in connection with the r.p.m.

Abstract: A flood valve is adapted to be mounted in an opening provided through a wall to normally separate a fluid on one side thereof from a relatively unpressurized space on the other side thereof. The valve includes an integrally-formed plastic body member having a forward portion mounted in the opening, an intermediate thin-walled section, and a rearward portion arranged in the unpressurized space. A piston is slidably mounted in a bore provided in the forward portion to engage the rearward portion, and forms a sealed chamber within the bore adjacent the thin-walled section. A heating element encircles the thin-walled section and may be selectively energized to melt the same, and to allow the rearward portion and the piston to separate from the forward portion. After such separation, fluid may pass through the forward portion bore to enter the unpressurized space.

Abstract: The invention relates to a system for tracking and/or guidance of a vehicle or projectile using a correlation arrangement for comparing representations from a sensor mounted on the vehicle or projectile with a reference representation, the correlation being carried out by comparing portions of the representations and like portions of the reference representation to derive position coordinates for each of said portions and to evaluate from said position coordinates compensation signals for rotational misalignment and/or changes of scale as between the reference and subsequent representations.

Abstract: A method for masking on the display device associated with a thermal telescope for the night guidance of self-propelled missiles carrying an infrared source, the image of a source of relatively intense stray radiations, wherein, on the one hand, the radiations transmitted in the field of vision of the thermal telescope are simultaneously detected in two different spectral bands, of which the one, called the useful band, corresponds to the maximum radiations from the target and the surrounding landscape, and the other one, called stray band, corresponds to the maximum radiations from the intense infrared sources carried or not by the missile, and on the other hand the signal detected in the first band is corrected by the signal detected in the second band in a manner to leave out the stray portions of the useful signal.

Abstract: The system of the present invention basically consists of a detector unit unted in each bomb or airborne weapon and operable upon interception of a signal emitted by an aircraft-mounted source. The required signal for arming is present only in a well defined zone below the aircraft and only in response to pilot command during weapon release. The signal consists of an unmodulated beam of high-energy photons (gamma rays) emitted by a radioisotope source on the aircraft. The weapon must fall well below the aircraft to see the signal. Geiger-Mueller tubes are used for radiation detectors and the resulting signal is processed to initiate the arming or fusing sequence. Power for the operation of the detector and associated electronics is transferred through the metallic covering of the weapon by means of a split-core transformer at the time of release.