Abstract: A nose assembly and method for controlling the rotation and stabilizing the orientation of a vehicle during landing maneuvers. The vehicle includes a nose assembly that is coupled to an airframe thereof and that has a frame and flap assembly. The flap assembly includes an actuating means and a flap coupled to the frame such that the actuating means moves the flap from and between a fully retracted position and a fully extended position in response to a guidance signal received from a flight control computer. In a preferred embodiment of the present invention, the flap assembly includes a plurality of flaps each coupled to the nose assembly frame and an actuating means that selectively positions the plurality of flaps in response to a signal.

Abstract: The invention provides a method for continuous acquisition, identification, and attack of helicopters operating with concealment, using a missile with an integrated target search head computer control. The visual field of the search head is adapted optimally in both the search phase and in the target tracking phase. During the search phase, the missile travels a flight path roughly parallel to the surface of the ground, and the axis of the line of sight is directed diagonally downward at a suitable angle. During a target tracking, the line of sight runs collinearly with the missile axis. The natural radiation of the helicopter modulated by the rotor blade movement is used for target recognition.

Abstract: The disclosure relates to a low cost and highly accurate precision guided system suitable for use in conventional aircraft launched bombs. The system includes a kit mounted upon the nose of the conventional bomb which replaces the conventional fuse disposed in a fuse well, the kit including guidance electronics controlling a self-contained jet reaction device and GPS P-code receiver electronics. The bombs are readied for discharge by signals broadcast from the aircraft into the bomb bay which transfer initial GPS data and commence operation of a gas generator which powers the jet reaction device.

Abstract: An artillery rocket including a motor for the launching thereof into a ballistic trajectory across a specified target area over which a payload is to be released. The rocket is equipped with a flight controller or autopilot for the control over a rudder or control surface-setting or control system which is actuatable from a navigational receiver with actual positional coordinates. The flight controller operates on a control or setting system which is disposed in front of the warhead in the forward region of the nose cone without noticeably restricting the usable volume for the warhead.

Abstract: An air-launchable gliding sonobuoy store includes a canister enclosing an flatable-membranous wing folded in a collapsed state with an electroacoustic system. After launching, the wing inflates and a steering mechanism controls the wing glide path by skewing the trailing edge thereof. Upon reaching the sea, the wing serves as a buoy with the electroacoustic system transducer depending therefrom.

Abstract: A munition including a submunition has a target detector and a core-generating charge with a firing axis .DELTA. for firing a projectile. The munition is designed to move relative to the ground and seek a target. The munition rotates about an axis A with a velocity translation v.sub.0. The target detector includes several detection axes .delta..sub.1 through .delta..sub.n and a device for selecting a detection axis .delta..sub.i from the detection axes .delta..sub.1 -.delta..sub.n for which the distance E between the point M.sub.i at which the axis .delta..sub.i intersects the ground and the point M' at which the projectile strikes the ground is minimal.

Abstract: A directed-effect submunition moves in a substantially vertical direction V with a displacement velocity v parallel to V and a rotation velocity r about an axis parallel to V. The submunition includes a shaped charge with axis D forming an acute angle t with axis V and a detection device with axis d forming an angle u with axis D, a target detecting device, and a triggering device. The submunition also includes a displacement velocity v determining device, and a calculation device for calculating as a function of v a value u.sub.i for angle u that minimizes deviation (e) between the position (M) of a target detected, and impact point (M') of the penetrator of the shaped charge if the latter were triggered upon detection, as well as a device for imparting the value u.sub.i to angle u.

Abstract: Submunition is transported by a carrier to a target area and launched there, whereupon it covers a preset distance at a constant altitude at an angle to the flight axis of the carrier. The submunition has a target sensor and a payload, and is equipped with an altimeter as well as a circuit to evaluate the altimeter readings, and with at least one altitude/roll rudder controllable by this circuit.

Abstract: A sub-combat unit to be separated from a flying body, comprises a warhead, a target detector and two diametrically disposed carrier surfaces designed and arranged to impart to the sub-combat unit a rotation for scanning of the target area in a helical pattern during the fall of the sub-combat unit down towards the target area. The two carrier surfaces are pivotable between a closed position and an opened position in which the two carrier surfaces form a retarding area for controlling the fall velocity of the sub-combat unit and a flow influencing means is provided at at least one of the two carrier surfaces for creating a turbulent area immediately above the carrier surface for completely relieving the carrier surfaces even for large differences in the direction of the impinging wind.

Abstract: The invention relates to a sub-combat unit which is disposed to be separated from a flying body, for example a carrier shell or the like, over a target area, the sub-combat unit comprising a warhead (4), a target detector (5) and two diametrically located carrier surfaces (1, 2) which impart to the sub-combat unit a rotation for scanning the target area in a helical pattern during the fall of the sub-combat unit down towards the target area, and both of the carrier surfaces (1, 2) being pivotally disposed from a collapsed position to an opened position where both of the carrier surfaces form a retarding area for the fall velocity of the sub-combat unit. The sub-combat unit is designed such that the relationship between the largest main inertia moment and the other main inertia moments of the sub-combat unit lies within the range of between 1.05 and 1.15.

Abstract: A submunition which is arranged to be separated from a missile or projectile for example, a shell canister or the like, over a target area including an active part, in the form of a warhead, a target detector and means for imparting to the submunition a controlled rotation for scanning of the target area in a helical pattern during the descent of the submunition towards the target area. The target detector is displaceable in order to allow a free view at the side of the warhead. The two diametrically situated aerofoils are pivotable from a folded position, in which the aerofoils connect with the outer surface of the submunition, to a 90.degree. unfolded position, in which the two aerofoils form a braking area for controlling the rate of descent of the submunition. The two aerofoils are pivotally arranged via a double joint.

Abstract: A device having pop-out wings and a guidance and control system is detachably mounted on a munition such as a bomb and is used to extend the range capability of the munition. Prior to launch, the wings are folded together. The control system is contained within a saddle portion of the device, and when the munition is released from the aircraft, the wings are caused to pop out to their flying position. The saddle is secured to the munition through a single bolt. Controllable flaps are installed along the trailing edges of the wings, such flaps being operated to control the pitch and roll angle of the munition. When the target area is reached, the device is jettisoned by detonating a charge which shears the securing bolt, thereby permitting the device to pivot rearwardly and separate from the munition.

Abstract: A flying body is provided with target detection capability. The flying body has an exterior wall and a target detection device for scanning a target area disposed within the body. The target detection device includes a combined laser transmitting/receiving system, having a laser and a laser radiation detector, stationarily mounted within the flying body. A holder is displaceably mounted for movement between a first position within the body and a second position where the holder extends outside of the exterior wall of the body. A first deflection mirror is disposed on the holder for reflecting radiation coming from the target area onto the laser radiation detector when the holder is in the second position. Additionally, a second deflection mirror is disposed on the holder for deflecting radiation coming from the laser toward the target area when the holder is in the second position.

Abstract: A low-altitude, retro-rocket, load landing apparatus for decelerating the rate of descent of a load and counteracting sideward wind drift. The apparatus includes a support assembly having a tilting mechanism for adjustably coupling a rigid support member to the load for pivotal movement about a horizontal axis offset from the center of gravity of the load, a retro-rocket rigidly coupled to the support member, a plurality of sensors for determining wind direction, wind speed and altitude of the load, and a control assembly coupled to the sensors, rocket and tilting mechanism for actuating the tilting mechanism in response to output signals from the sensors. Actuation of the tilting mechanism varies the rocket's thrust direction and counteracts sideward wind drift.

Abstract: A weapon deliver/target interceptor (DISK) comprising a spinning right circular cylinder maneuvered by thrusters located about the periphery of the cylinder's circumference. The cylinder is guided by means of a forward looking sensor mounted on the front face of the cylinder and a guidance system which senses the rotational acceleration and precessional acceleration.

Abstract: A vehicle steering device is disclosed that can be joined to any air-drop, free-falling component and steers that component directly down to a pre-determined location on the earth's surface. The device is comprised of an aerodynamically-shaped housing that is joined to the front of the component, and which carries orientation means in a nose portion, high-density gravity-reaction means, and steering fins rotatably joined thereto. After the combination is dropped, at a pre-determined altitude and airspeed, the orientation means causes it to assume the most efficient aerodynamic position and then the gravity-reaction means forces the nose, which is joined to and leads the component, to dive into the earth. The reaction means are connected to the fins and force a controlled and predictable descent.

Abstract: A mine, particularly a land mine, is equipped with at least one active (i.e. destructive) element which is accommodated in a housing of the mine and can be brought to the functional level by means of a rocket engine. For attaining a definite ascent of the active element, the rocket engine is mounted to this active element in such a way, and is designed in such a way, that its exhaust nozzles are located outside the mine housing and the propellant gases of the rocket engine effect extraction of the active element from the mine housing which is open at an upper end. The rocket engine furthermore exerts preferably a torque on the active element about the longitudinal axis of the element so that, in conjunction with an effective charge, the effective direction of which is inclined obliquely downwardly, the effective area on the ground continuously increases in a spiral fashion during ascent of the active element.

Abstract: Projectile steering apparatus and method employing the autogiro principle. Two rotatable blades are swung out from a longitudinal slot in a flying projectile. The blades are shaped to rotate as a result of the air stream rushing past the projectile. Steering is effected by altering the orientation of the blades with respect to the projectile in synchronism with rotation of the projectile. By varying the autogiro pattern produced by the pair of blades, it is possible to impart a force for correcting the projectile trajectory.

Abstract: Air carrying equipment particularly suited for ballistic type munitions, consisting of two parts that can be mutually coupled: a saddle that can be mounted to straddle the munition, provided with a pair of wings that are opposite and hinged close to the longitudinal edges of the saddle; and a cradle that can be mounted underneath the body of the munition, which can be coupled to saddle and contains fuel tanks, a motor device in the rear and an ogival part or torpedo nose in front with air intake and wind rotor.

Abstract: A command control and propulsion unit for ballistic munitions, including a wind-driven propeller, attached to a front end of the body of the munition for activation of an alternator. The electric power generated by the alternator activates a pump that feeds liquid fuel to a rocket motor oxidized by a liquid oxygen coming from a tank housed in a cradle. The cradle is coupled to a saddle, radially opposite from the cradle, which is provided with hinged and foldable sings. The body of the munition is coupled between the saddle and the cradle.

Abstract: The invention relates to a system for guiding of a projectile towards a target and a projectile for carrying out the system. The projectile has means for guiding the projectile towards a desired target, e.g. by means of control signal from a target seeker. In a given point of the projectile trajectory blades or wings are swung-out from the projectile body, which blades in swung-out position are shaped as a propeller so that they are driven by the stream of air passing the projectile. In order to guide the projectile towards the target in the final phase of the trajectory the said blades are then adjusted in dependence upon the control signal from the target seeker. In one embodiment, in which the blades are rotatably journalled on the projectile body, the rotational axis of the blades is set in a given angle relative to the length axis of the projectile. This oblique setting between the rotational axis and length axis then will produce a desired force in lateral direction on the projectile.

Abstract: A device for neutralizing military objects by means of sub-munitions released by a mother rocket onto mobile targets on the ground. Each sub-munition (1) is provided with a military charge (2) and a wide range sensor (3) and descends while suspended from a parachute and turns uniformly about a vertical axis of symmetry (10), the angle formed by the firing axis (5) and the vertical being constant. Superimposed upon this rotational movement of the sub-munition, the periodic oscillatory movement of an orientable mirror (14) permits varying the direction of the optical axis (8') with respect to the firing axis during the detection phases of a target and the guiding of the sub-munition towards the detected target. Thus at each oscillation period of the orientable mirror the complete image of the circular area on the ground is obtained. In the last phase of firing, when aimed at the target, the optical axis is maintained in the direction of the firing axis.

Abstract: A method of attacking aboveground armored objects, in particular those which are employed for sheltering aircraft; and moreover, to the utilization of steeply descending final flight phase-corrected submunition. The shelter is attacked in an orientation directed generally horizontally against its gate. Furthermore, in the utilization of steeply descending submunition of the type which is employed for implementing the foregoing method, this includes at least one projectile-forming covering oriented genrally transversely of the longitudinal axis thereof, and with a maneuvering sensor responsive to the center of a typical aircraft apron clutter signature in front of an aircraft shelter.

Abstract: A device for reducing the rotational speed of an ammunition unit, for instance a submunition unit, and at the same time imparting to the ammunition unit a lateral speed includes a body arranged to be swung out from the ammunition unit and be released in a specific outswung position. The body preferably consists of a band which is wrapped about the outer peripheral surface of the ammunition unit. One end of the band is fixed to the ammunition unit in such a way that the band is released in a specific outswung position.

Abstract: When a homing head or seeker is mounted on-board a missile, the inertial reference provided by the seeker may be contaminated to some extent by the motion of the missile body. To alleviate this, seekers are sometimes gimballed and use rate or position gyros or they may be momentum-stabilized--the seeker itself providing the inertial reference. However, gyros are both complex and expensive, and momentum-stabilized seekers tend to have large inertias making it difficult to achieve high scan rates. The guidance system described herein allows the establishment of inertial references via information derived from a seeker which need not be isolated from the missile body, the seeker having a range measuring function which, possibly in combination with one or more accelerometers, is used to control pitch, yaw, roll and stabilization of the missile.

Abstract: A guided missile is directed to railroad tracks, is buried a particular distance, such as five (5) feet, below the tracks upon reaching the tracks and is covered by rocks in the railroad bed as it moves the particular distance below the tracks. The guided missile detonates when the train approaches on the tracks within a particular distance from the guided missile on the tracks. The train then becomes derailed. The guided missile has a housing which is made from a strong metal and which is relatively thick. Preferably the metal is steel and has a thickness of about 0.2". A nose cone having a blunt configuration is disposed on the housing at the front end of the housing and is made from a material which passes signals into and out of the housing. The material is compressible (e.g. fiberglass, a ceramic or a glass) to become flattened when the missile strikes the ground.

Abstract: Ammunition incorporating a sensing fuse and a parachute, and which has the trajectory thereof correctable during its final flight phase, and a method for the combating of armored target objects with the utilization of such ammunition. The ammunition with the sensing fuse is equipped with a pulse transmitter for a course alignment or correction in the direction towards the lateral or sideways offset of a target object which has been detected by the sensing fuse, and with devices for suspending the action of a parachute during the approach to a target by the ammunition along a quasi-ballistic trajectory.

Abstract: An article of ammunition which is controllable during its final flight phase, which is equipped in its cross-sectional plane through the center of gravity with a radially oriented impulse system which is rotatable about the longitudinal axis of the article of ammunition; article, which is activatable through a control circuit located on board of the ammunition article, upon the detection of a target object which is located on the opposite side relative to the instantaneous orientation of the impulse system through the intermediary of a sensor device. Also disclosed is a method for navigating an article of ammunition which is controllable during its final flight phase towards the target object.

Abstract: An air dispensed assembly in the form of a submunition cannister is disclosed which has the capability to perform a lateral maneuver during the final 1500 ft. of descent before impact. Maneuvering is accomplished by deploying a samara blade shaped wing from the rear of the submunition cannister after ejection from the casing of the launching shell. The wing is sized and provided with an angle of attack which causes the cylindrical shaped cannister to spin as it descends downward at approximately a constant rate of descent. A passive infrared sensor in the nose of the cannister provides target information to a data processor which generates steering commands to appropriately alter the wing angle of attack so as to bring about a corrective lateral change in direction. When within lethal range of the sensed target, the warhead in the submunition is detonated.

Abstract: A missile on-board flight pitch, yaw and roll control drag actuator system. The system having a plurality of control panels operated by an actuator drive. The actuator drive accurately positioning the panels in a desired position in the airstream of the missile for controlling the flight, orientation and speed of the aircraft.

Abstract: A regulating system for guided ammunition flying at supersonic speed, such as missiles, rockets, or projectiles which includes an arrangement for effecting the guidance through a partially changeable flow pressure. Provided on the ammunition are one or more steering systems in the form of ring-shaped or quasi-annular guidance mechanisms which are divided into sectors, and wherein the sectors cause a medium which become effective within the sectors to selectively and controllably block the airflow.

Abstract: A control system for an ammunition having a longitudinal axis and adapted to move in a flight direction, particularly a wingless ammunition falling in ballistic flight, comprises a body having a rear curved surface with a gas generator in the body for producing gas under pressure. A nozzle is mounted to the body and oriented to direct a gas jet produced from the pressurized gas rearwardly and tangentially over the curved surface with respect to the flight direction of the ammunition. The gas jet produces reduced pressure on its side of the ammunition to alter the flight thereof.

Abstract: A guidance method is provided for the terminal portion of the trajectory of a guided missile having a sensor and comprising two sections coupled together by a central shaft and free to rotate with respect to one another about the longitudinal axis of the missile; one section comprises a drive means for controlling the roll attitude of this section and a gas generator which feeds a nozzle for providing a transverse throat force and the other section has a stabilizing tail unit formed by a set of fins able to be opened out.

Abstract: A submunition having an infrared detector disposed in a nose portion thereof, the detector having a narrow angularly-displaced field of view, and vanes for causing the submunition to rotate at an essentially constant rate while in flight, thus to cause the infrared detector to scan a target area and to detect the presence of a target having a selected higher temperature than the background infrared radiation. The submunition includes a small explosive charge sheet disposed on its outer surface and concentrated in one area, and firing pulse generation means for firing the charge. When the infrared detector scans past a detectable target within the target area, it produces a detection signal that triggers a firing pulse from the firing pulse generation means, thereby firing the explosive charge to create a lateral impulse or offset of the submunition.

Abstract: A delivery system for multiple sub-missiles including in the sub-missiles a marking system, a detection system, a diverter for elimination of targets identified by the detector system, a scanner for initial determination of multiple targets, a logic circuit utilizing input from both the diverter and the scanner to eliminate targets and a sub-missile guidance system.

Abstract: In a munitions system, a cylindrical canister is fired over a target. The canister carries a target sensing infrared device and, when a target is detected, a projectile is fired downward from the bottom of the overflying missile. A spinning motion is imparted to the missile to stabilize its flight, and a wobbling motion is imparted to the missile to provide a larger target area. The projectile forms a concave lower end to the missile and is fired by an explosive charge.

Abstract: A guided bomb for use in low level flying for pinpoint target combat, comprises a bomb having a braking device associated therewith to produce a slow-down which is effective against the trajectory and a picture-taking sensor connected to the bomb to guide the bomb for final phase guidance. The braking device advantageously comprises retrorockets or a parachute. The picture-taking sensor is advantageously a television camera or an infrared camera and a tracker is associated with it which may be mounted, for example, on the aircraft carrying the bomb. The picture taken by the picture-taking sensor is transmitted via either a radio or mechanical connection to the aircraft and is reproduced there for guidance by the pilot. The target may advantageously be illuminated by a laser illuminator carried on the aircraft and the bomb advantageously has a tracker with laser vectoring.

Abstract: In a munitions system, a cylindrical canister is fired over a target. The canister carries a target sensing infrared device and, when a target is detected, a projectile is fired downward from the bottom of the overflying missile. A spinning motion is imparted to the missile to stabilize its flight, and a wobbling motion is imparted to the missile to provide a larger target area. The projectile forms a concave lower end to the missile and is fired by an explosive charge.