Abstract: A projectile having a plurality of micro electromechanical (MEMS) devices disposed about the axis of flight for active control of the trajectory of the projectile. The MEMS devices each form an integral control surface/actuator. Control circuitry installed within the projectile housing includes both rotation and lateral acceleration sensors. Flap portions of the MEMS devices are extended into the air stream flowing over the projectile in response to the rate of rotation of the projectile, thereby forming a standing wave of flaps operable to impart a lateral force on the projectile. MEMS devices utilizing an electrostatically controllable rolling flap portion provide a large range of motion while consuming a small amount of power. The MEMS devices may be arranged in longitudinal strips along an ogive portion of the projectile. Packaging concepts for projectiles as small as a 30 caliber bullet are described.

Abstract: A device for the unambiguous measurement of the angle of roll of a projectile, comprises at least a radar equipped with means of processing and sending a signal to the casing of the projectile in at least one direction of incident polarization; a set of parallel grooves made on the casing, the depth of which is modulated dissymmetrically with respect to the axis of symmetry of the projectile; the axis of symmetry of the projectile not passing through the point of the antenna of the radar where the antenna beam is generated, the processing means analyzing, in reception, a signal back-scattered by the casing of the projectile, the signal being modulated as a function of the angle of roll of the projectile, the modulation having two maximum local values corresponding to two angular roll positions of the projectile such that the polarization {overscore (E)} is parallel to the grooves, the processing means removing the 180° ambiguity by comparing the levels of the local maximum values.

Abstract: A submunition for delivery in a carrier, the submunition including a satellite aided global location system guidance system mounted on the submunition for guiding the submunition towards a pre-selected target after delivery to a target area by the carrier, and a method for guiding a submunition after delivery from a carrier, the method including mounting a satellite aided global location system guidance system on the submunition and utilizing the satellite aided global location guidance system to guide the submunition towards a pre-selected target.

Abstract: A projectile having a plurality of micro electromechanical (MEMS) devices disposed about the axis of flight for active control of the trajectory of the projectile. The MEMS devices each form an integral control surface/actuator. Control circuitry installed within the projectile housing includes both rotation and lateral acceleration sensors. Flap portions of the MEMS devices are extended into the air stream flowing over the projectile in response to the rate of rotation of the projectile, thereby forming a standing wave of flaps operable to impart a lateral force on the projectile. MEMS devices utilizing an electrostatically controllable rolling flap portion provide a large range of motion while consuming a small amount of power. The MEMS devices may be arranged in longitudinal strips along an ogive portion of the projectile. Packaging concepts for projectiles as small as a 30 caliber bullet are described.

Abstract: The Magnetostrictive Missile Guidance System pivots the missile nosecone about a multi-directional joint on the missile axis to produce aerodynamic control forces for missile flight path control. The nosecone is driven by magnetostrictive materials in conjunction with displacement amplification devices. The determination of the nosecone deflection angle necessary to achieve any change in the flight path is made by a sensing device that produces position signals and a guidance computer that produces the desired flight path command signals. The sensing device senses the current position of the nosecone and this position signal is compared with the command signal by the computer to yield an error signal, which is indicative of the difference between the two input signals. Then appropriate magnetic field is applied to the magnetostrictive materials to cause them to grow in length and deflect the nosecone until the error signal is eliminated and flight path is changed.

Abstract: An apparatus, method and computer program product useful for supplying the pilot of an aircraft with aircraft attitude information. During bank angles exceeding a predefined limit, the roll gyro is slaved to a roll angle estimator for improved system accuracy.

Abstract: A tracking device includes a motor, top and bottom propellers of opposite sense attached to the stator and rotor of the motor for rotation in opposite directions. Target sensors are provided on the propellers and signals from the target sensors are supplied to a controller that controls the rotation of the motor and the propellers. The tracking device also includes a power supply for the motor and the controller.

Abstract: A guidance device for projectiles has stationary canards (40) and thrusters (50) positioned on the nose (20) of the projectile (10). The thrusters (50) are initiated from remote or local sensor to provide flight maneuverability to a target.

Abstract: A method to determine the direction in which a spinning projectile is traveling. A solar sensor array on the projectile is used to calculate the orientation of the axis of rotation of the projectile with respect to a known solar field and a magnetometer sensor array is used to calculate the orientation of the axis of rotation of the projectile with respect to a known magnetic field, both fields being represented by respective vectors having magnitude and direction. With the known and calculated orientations, the pointing direction may be obtained by vector combination.

Abstract: The present invention provides a fast, low-cost, small diverter capable of generating a relatively high impulse (1-5 N-sec) over a short time period. The diverter is adapted for installation in a projectile for steering the projectile in flight by ejecting an end cap in response to control signals from a guidance system. In one embodiment, multiple diverters are arranged in one or more bands about a flying projectile such as a rocket. Each diverter includes a header assembly providing a mounting surface and support for a plurality of electrical leads, a reactive semiconductor bridge mounted on the mounting surface of the header assembly and providing an electrical path for the electrical leads at a certain voltage across the bridge, a diverter body supporting the header assembly and containing a prime, wherein the reactive semiconductor bridge and the prime define a gap, and an end cap attached to the diverter body and containing a propellant.

Abstract: The present invention relates to a process and a device for guiding a flying craft onto a target, the device (1) comprising a detector (D) pointed at the target in such a way that a projection of the latter is situated on a field of measurement of the detector (D), a computation unit (UC) for determining guidance commands, and members (6) carrying out the guidance. According to the invention, the said device (1) furthermore comprises computation means (C3, C4) for determining commands for varying attitudes of the said flying craft making it possible to center the said projection with respect to a first direction of the measurement field, and the line of sight of the detector (D) is moveable and is controlled in such a way as to center the said projection with respect to a second direction of the measurement field, which is different from the said first direction.

Abstract: Apparatuses and methods for controlling an object spinning at a first rate in a first direction. The apparatus includes a swash plate, a rotor, a spin actuator, a roll actuator, and a pitch actuator. The rotor is coupled to the swash plate. The spin actuator is coupled to the rotor and is configured to spin the rotor in a second direction opposite the first direction at a second rate. The roll actuator is coupled to the rotor and is configured to displace the swash plate along a longitudinal axis. The pitch actuator is coupled to the rotor and is configured to tilt the swash plate in a tilt direction about the longitudinal axis, the tilt direction being adjustable by adjusting the second rate relative to the first rate. The roll actuator may be coupled to the pitch actuator so that the pitch actuator keeps a substantially identical orientation with the swash plate as the swash plate is displaced along the longitudinal axis by the roll actuator.

Abstract: A locking and unlocking mechanism for moveable control fins extending from the surface of a missile. The locking mechanism includes a pin extending thru the outer surface of the missile into an opening provided in the movable fin. A link is pivotally connected between each of the pins and a slide member disposed internally of the missile and carried by a guide. The links are in a close to dead center position when the pins are extended into the openings in each of the fins. A striker assembly is disposed within the slide member and includes a rod carrying a hammer which is spring loaded spaced from the slide member when the pins are in their extend position.

Abstract: An active damping method and a self-contained active damping system that can be retrofitted to existing rockets are provided which for reducing the dispersion of rockets by using lateral thrusters to oppose any initial yawing motion. The self-contained system of the present invention can be installed in a cylindrical section of a rocket body by insertion between other flight body parts.

Abstract: In a projectile launched by a gun, the projectile including a fuze with a longitudinal axis of symmetry and a braking device, an apparatus disposed in the fuze for determining a time of deployment of the braking device, the apparatus including a first accelerometer having a sense axis and mounted with its sense axis coincident with the longitudinal axis of symmetry of the fuze; a second accelerometer having a sense axis and mounted a known axial distance from the first accelerometer and with its sense axis coincident with the longitudinal axis of symmetry of the fuze; a magnetometer having a sense axis and mounted with its sense axis orthogonal to the longitudinal axis of symmetry of the fuze; a field-programmable memory unit loaded with aiming data of the gun, magnetic field direction at the gun, a nominal path length table, and a braking device maneuver authority table; and a microprocessor connected to the first and second accelerometers, the magnetometer, the field-programmable memory unit and the braking

Abstract: A winged bomb is launched from a launch aircraft and glides to a target. During the glide the winged bomb follows a calculated guide path stored in a on board computer, with correction generated by the computer using data from an altimeter and global positioning receiver. Near the termination of the glide a television camera is activated and transmits signals to a remote location from which final correction are manually generated and transmitted by radio to the bomb. The bomb is designed with low radar cross section.

Abstract: In a first aspect, the invention uses the thrust and axial aerodynamic forces of and on the missile system as the primary mechanism for altering the missile system's flight path as opposed to the missile system's aerodynamic normal force. In accordance with this first aspect, a first embodiment is a method for changing the direction of travel of a vehicle moving through a fluid medium to a desired direction of travel measured in the vehicle's inertial frame of reference, the vehicle comprising a body including a nose, a moment generating control device, and an axial propulsive device. The method comprises actuating the moment generating control device to align the nose substantially with the desired direction of travel, and applying the axial propulsive device as the primary mechanism to redirect the vehicle's velocity to the desired direction of travel. In a second aspect, the invention provides a missile control system implementing the first aspect of the invention.

Abstract: In an adjusting apparatus for control surfaces of a missile the control surfaces 2, 3 are displaceable by adjusting motors 5, 6 by way of thrust spindles 15. To afford a compact structure and a low weight the stators 7 of the adjusting motors 5, 6 are arranged directly in a carrier housing 4 and the thrust spindle 15 engages into a female thread 14 of the motor shaft 9.

Abstract: A control system for aerodynamic vehicles has a fuselage nose segment and at least one strake. The fuselage nose segment is rotationally adjustable with respect to the aircraft fuselage. The at least one strake is mounted on the fuselage nose segment so that the strake can swing out.

Abstract: A universal driver circuit is provided for actuating both valves and ordnances, such as the valves and ordnances carried by a missile or other unmanned air vehicle. The universal driver circuit includes at least one valve driver circuit for controllably opening and closing a valve and at least one ordnance driver circuit for controllably activating an ordnance. In addition, the universal driver circuit includes a controller capable of independently directing each valve driver circuit and each ordnance driver circuit to open the valve and to activate the ordnance, respectively.

Abstract: A method for the automated generation of ballistic constants for use in a trajectory control system. The potential trajectory of a pursuing vehicle is divided into a plurality of multiple sequential phases wherein each phase is characterized by a plurality of ballistic parameters. Known simulated data from a number of runs concerning the pursuing vehicle is analyzed. Ballistic parameter values for each run are obtained and statistically analyzed to produce generic constants for a particular set of operating conditions. Resulting matrices are stored as part of a two-dimensional, kinematic vehicle model to facilitate the propagation of projected trajectories during firing control solutions.

Abstract: Method and apparatus are described for improving the impact angle between a missile and stationary or moving target in the presence of stationary or adverse wind conditions. A triggered bias detector provides an enabling signal to a bias resolver when the pitch line of sight rate of a missile exceeds a predetermined level. The bias resolver supplies first and second bias signals to the pitch forward guidance loop and yaw forward guidance loop in response to the detected pitch line of sight rate. The missile is given a lofting trajectory in response to the applied bias signal as it closes on the target. Impact angles of a more nearly vertical condition over a wide range of missile/target acquisition geometric conditions are obtained using this triggered bias technique over conventional constant gravity bias proportional guidance techniques.

Abstract: A locking mechanism for moveable control fins extending from the surface of a missile. The locking mechanism includes a pin extending thru the outer surface of the missile into an opening provided in the movable fin. A link is pivotally connected between each of the pins and a slide member disposed internally of the missile and carried by a guide. The links are in a close to dead center position when the pins are extended into the openings in each of the fins. Upon a command signal from a controller, preparatory to missile launch, a restraining device holding the slide is removed and a spring commences movement of the slide toward a position which will take the links past their dead center position upon which additional springs which are loaded around each of the pins are activated to positively move the slide and extract the pins from the openings in the fins.

Abstract: The invention, in one embodiment, is an apparatus for controlling the roll, pitch, and yaw attitudes of an air or sea vehicle. The apparatus includes an actuator including an actuation plane and an actuation mechanism, capable of displacing the actuation plane at three points; at least three non-propulsive fins; and a linkage between the actuator and each one of the fins, the linkage communicating the actuation plane's displacement to the respective one of the fins.

Abstract: An attitude control system and method operative with a thruster controls the attitude of a vehicle carrying the thruster, wherein the thruster has a valve enabling the formation of pulses of expelled gas from a source of compressed gas. Data of the attitude of the vehicle is gathered, wherein the vehicle is located within a force field tending to orient the vehicle in a first attitude different from a desired attitude. The attitude data is evaluated to determine a pattern of values of attitude of the vehicle in response to the gas pulses of the thruster and in response to the force field. The system and the method maintain the attitude within a predetermined band of values of attitude which includes the desired attitude. Computation circuitry establishes an optimal duration of each of the gas pulses based on the pattern of values of attitude, the optimal duration providing for a minimal number of opening and closure operations of the valve.

Abstract: A comparative dual-control strategy actuates forward and aft control devices simultaneously to significantly improve a missile's maneuverability/dynamic capability. A substantial, and measurable, operational effect of the inventive control strategy is a dramatic improvement in a missile's divert capability. To effect a maneuver in accordance with the inventive strategy, a missile's aft fins are initially deflected to generate a force OPPOSITE that conventionally used (pushing the missile's tail in the direction of the commanded maneuver) which simultaneously actuating forward thrusters to also push the missile's nose in the direction of the commanded maneuver but at a faster rate than the tail section. This causes the missile body to simultaneously rotate and translate in the direction of the commanded maneuver.