Abstract: A reliable and inexpensive attitude control system uses a plurality of pitch-over thrusters to perform rapid and precise attitude maneuvers for a flight vehicle. The pitch-over thrusters create rotational moments that directly pitch and yaw the flight vehicle. The use of very simple thrusters and control techniques provides for a reliable and cost effective solution. The ability to perform overlapping pitch and yaw maneuvers with single-shot fixed-impulse thrusters provides for high-speed maneuverability.

Abstract: Methods and apparatus for delivering a missile may operate in conjunction with a missile comprising an outer skin. The missile may be configured in a closed position and an open position. In the open position, an aperture is opened in the outer skin, for example to supply air to an air-breathing engine. In the closed position, the aperture is closed.

Abstract: Methods and apparatus for guiding a projectile according to various aspects of the present comprise a force source disposed on the projectile and a control system operably connected to the force source. The control system is configured to initially activate the force source when the force source is substantially in a selected rotational position, and subsequently activate the force source when the force source rotates to substantially the selected rotational position a second time.

Abstract: An aircraft in the form of multi-stage missile 1 with a spiral inducing assembly 2 which is capable of inducing the missile to travel in a continuous spiraling motion without the missile rolling. A ramjet 6b is attached to a tube 3 that is able to rotate around the encircled part of the fuselage. The ramjet 6b is able to rotate in a pivoting manner on the rotate-able tube 3 with respect to the rotate-able tube 3, thereby changing their pitch relative to the longitudinal axis of the rotate-able tube 3. Ramjet 6b is rotated to a greater than another ramjet on the right side of the tube 3. The difference in degree of rotation between the ramjets makes the ramjet 6b exert a greater force on the rotate-able tube 3 than the ramjet on the right side when the ramjets are rotated in the same direction. The imbalance between the rotational forces thus causes the rotate-able tube 3 to rotate. When rotated, the ramjets would exert a lateral force on the rotate-able tube 3.

Abstract: An aircraft in the form of multi-stage missile 1 with a spiral inducing assembly 2 which is capable of inducing the missile to travel in a continuous spiraling motion without the missile rolling. A ramjet 6b is attached to a tube 3 that is able to rotate around the encircled part of the fuselage. The ramjet 6b is able to rotate in a pivoting manner on the rotate-able tube 3 with respect to the rotate-able tube 3, thereby changing their pitch relative to the longitudinal axis of the rotate-able tube 3. Ramjet 6b is rotated to a greater than another ramjet on the right side of the tube 3. The difference in degree of rotation between the ramjets makes the ramjet 6b exert a greater force on the rotate-able tube 3 than the ramjet on the right side when the ramjets are rotated in the same direction. The imbalance between the rotational forces thus causes the rotate-able tube 3 to rotate. When rotated, the ramjets would exert a lateral force on the rotate-able tube 3.

Abstract: A spin-stabilized projectile is steered by taking air from an air intake at the front of the projectile, and expelling the air along an outer surface of the projectile to alter its trajectory toward the desired impact location. Air taken in through the air intake is directed toward a rotor that is able to rotate relative to the rest of the projectile. The rotor has an outlet that may direct the air taken in at the air inlet out in a direction having both radial and circumferential components. The force produced in the radial direction provides a steering force substantially normal to the projectile axis, used to steer the projectile. The force produced in the circumferential direction is used to provide impetus to spin the rotor. A brake is used to control the rotational speed of the rotor, to control the direction that the air is expelled from the projectile.

Abstract: Projectiles are provided having a shell and; one or more actuators for providing thrust disposed inside of a wall of the shell; one or more ring portions forming at least a portion of the shell, the one or more ring portions having one or more actuators formed therein for providing thrust and/or one or more actuator stacks for providing thrust, the one or more actuator stacks each having two or more individual actuators for providing thrust.

Abstract: A flying object includes a lift and displacement motor which has a combustible propelling charge and direct thrust flight control and can ensure the lift and displacement of the flying object in an observation position for which the flying object is at least approximately vertical with the rear part thereof oriented downwards; an attitude motor with a combustible propelling charge and conventional thrust vector control; and an observation unit which is arranged in the rear part of the flying object.

Abstract: Rolling airframe projectile guidance and stability systems are disclosed. Flight control surfaces, such as canards and/or tail fins are attached to a projectile airframe that is designed to roll during flight. Stepper motors are attached to the flight control surfaces and move the flight control surfaces in discrete increments. A control system generates signals that control the flight control surfaces. The control system may include a neural network that is trained to generate control signals in response to received inputs.

Abstract: A method for varying the flight path of a missile, in particular of a spin-stabilized projectile, which has an outer wall and which is provided with at least one impulse device. The impulse device can be activated deliberately at a defined time during the flight of the missile. The impulse device is arranged with respect to the longitudinal axis of the missile such that, when it is activated, it generates an impulse that initiates a tumbling movement which causes the flight-path of the missile to be shortened or varied. A spin-stabilized projectile is provided with such an impulse device and it is configured so that the impulse device may be triggered during flight so as to initiate the flight-altering tumbling movement.

Abstract: A control surface actuation system has the ability to move aerodynamic control surfaces using a rotational motion of a motor. In an arrangement, rotational motion of the motor enables the aerodynamic control surfaces of a rotating projectile to oscillate and thus vary the angle of the control surfaces as the projectile spins. The rotation of a motor in one direction in combination with a gear and a link and a crank arm attached to a shaft of the aerodynamic control surfaces allows the control surfaces to move in fluttering motion to induce the maneuvering of a projectile in the desired direction. A controller takes information regarding the current condition of the projectile and drives the motor to move the aerodynamic devices to maneuver the projectile.

Abstract: An aircraft in the form of multi-stage missile 1 with a spiral inducing assembly 2 which is capable of inducing the missile to travel in a continuous spiraling motion without the missile rolling. A ramjet 6b is attached to a tube 3 that is able to rotate around the encircled part of the fuselage. The ramjet 6b is able to rotate in a pivoting manner on the rotate-able tube 3 with respect to the rotate-able tube 3, thereby changing their pitch relative to the longitudinal axis of the rotate-able tube 3. Ramjet 6b is rotated to a greater than another ramjet on the right side of the tube 3. The difference in degree of rotation between the ramjets makes the ramjet 6b exert a greater force on the rotate-able tube 3 than the ramjet on the right side when the ramjets are rotated in the same direction. The imbalance between the rotational forces thus causes the rotate-able tube 3 to rotate. When rotated, the ramjets would exert a lateral force on the rotate-able tube 3.

Abstract: An aircraft 1 with a spiral inducing assembly 2 which is capable of inducing the aircraft to travel in a continuous spiraling motion without the aircraft rolling. A ramjet 6b is attached to a tube 3 that is able to rotate around the encircled part of the fuselage. The ramjet 6b is able to rotate in a pivoting manner on the rotate-able tube 3 with respect to the rotate-able tube 3, thereby changing their pitch relative to the longitudinal axis of the rotate-able tube 3. Ramjet 6b is smaller than another ramjet on the right side of the tube 3. The difference in size between the ramjets makes the ramjet 6b exert a weaker force on the rotate-able tube 3 than the ramjet on the right side when the ramjets are rotated in the same direction. The imbalance between the rotational forces thus causes the rotate-able tube 3 to rotate. A fin 6c is also able to cause the rotate-able tube 3 to rotate during flight. When rotated, the ramjets would exert a lateral force on the rotate-able tube 3.

Abstract: An aircraft 1 with a spiral inducing assembly 2 which is capable of inducing the aircraft to travel in a continuous spiraling motion without the aircraft rolling. A ramjet 6b is attached to a tube 3 that is able to rotate around the encircled part of the fuselage. The ramjet 6b is able to rotate in a pivoting manner on the rotate-able tube 3 with respect to the rotate-able tube 3, thereby changing their pitch relative to the longitudinal axis of the rotate-able tube 3. Ramjet 6b is rotated to a greater than another ramjet on the right side of the tube 3. The difference in degree of rotation between the ramjets makes the ramjet 6b exert a greater force on the rotate-able tube 3 than the ramjet on the right side when the ramjets are rotated in the same direction. The imbalance between the rotational forces thus causes the rotate-able tube 3 to rotate. When rotated, the ramjets would exert a lateral force on the rotate-able tube 3.

Abstract: An aircraft 1 with a spiral inducing assembly 2 which is capable of inducing the aircraft to travel in a continuous spiraling motion without the aircraft rolling. A ramjet 6b is attached to a tube 3a that is able to rotate around the encircled part of the fuselage. The ramjet 6b is able to rotate in a pivoting manner on the rotate-able tube 3a with respect to the rotate-able tube 3a, thereby changing their pitch relative to the longitudinal axis of the rotate-able tube 3a. Ramjet 6b is rotated as is another ramjet on the right side of the tube 3a. The rotate-able tube 3a is rotated by means of an electric motor 3b rotating a wheel 3c. The difference in degree of rotation between the ramjets makes the ramjet 6b exert a greater force on the rotate-able tube 3a than the ramjet on the right side when the ramjets are rotated in the same direction. The imbalance between the rotational forces thus causes the rotate-able tube 3a to rotate.

Abstract: The present invention relates to a method of controlling an aircraft, missile, munition or ground vehicle with plasma actuators, and more particularly to controlling fluid flow across their surfaces or other surfaces, which would benefit from such a method. The method includes the design of an aerodynamic plasma actuator for the purpose of controlling airflow separation over a control surface of a aircraft, missile, or a ground vehicle, and more particularly to the method of determining a modulation frequency for the plasma actuator for the purpose of fluid flow control over these vehicles. The various embodiments provide the steps to increase the efficiency of aircraft, missiles, munitions and ground vehicles. The method of flow control provides a means for reducing aircraft, missile's, munition's and ground vehicle's power requirements. These methods also provide alternate means for aerodynamic control using low-power hingeless plasma actuator devices.

Abstract: A yaw control system is provided for use in a hypersonic airborne mobile platform, for example a re-entry vehicle. The system includes an active movable yaw control flap positioned between passive/fixed yaw ear surfaces that border or frame the active yaw flaps. The yaw control system includes an active yaw control flap embedded between passive/fixed yaw ear surfaces. The retracted active yaw control flap and passive/fixed yaw ear surfaces provide passive yaw damping during atmosphere reentry, bank-to-turn steering and midcourse fly-out/glide steering. The active yaw control flaps are preferably arranged on opposing sides of a re-entry vehicle, and may be independently extended to provide for steering the vehicle. The active yaw control flaps provide for active yaw control skid-to-turn terminal guidance to achieve a desired level of accuracy, such as needed when using the vehicle as a missile to strike a target.

Abstract: A side thruster module, comprises: a cavity-type body skin extending in a longitudinal direction; a first thruster arranged in the body skin and extending in a longitudinal direction; and a conversion nozzle arranged in the body skin and extending in a radial direction perpendicular to the longitudinal direction, for converting a direction of a thrust generated from the first thruster in the longitudinal direction into the radial direction. A large number of thrusters can be mounted at the side thruster module thus to generate a high thrust, and the side thruster module can be slim in the radial direction perpendicular to the longitudinal direction.

Abstract: A method for varying the flight path of a missile, in particular of a spin-stabilized projectile, which has an outer wall and which is provided with at least one impulse device. The impulse device can be activated deliberately at a defined time during the flight of the missile. The impulse device is arranged with respect to the longitudinal axis of the missile such that, when it is activated, it generates an impulse that initiates a tumbling movement which causes the flight-path of the missile to be shortened or varied. A spin-stabilized projectile is provided with such an impulse device and it is configured so that the impulse device may be triggered during flight so as to initiate the flight-altering tumbling movement.

Abstract: A steering system for use in a traveling guided flying apparatus (10) and method for driving the steering system are provided. The system includes an outer housing (111), an inner housing (113) and a support fins (112) extending inwardly from the outer housing (111) and holding the inner housing (113) thereon. The outer housing (111) and the inner housing (113) define a ram air inlet (114) at a nose of the forward portion (11), an annular inlet air passage (115), an annular pressure chamber (116), and an outlet air passage (125). The steering system further includes exhaust outlets (120) arranged in the outer housing and separately controlled valves (124) mounted at the exhaust outlets (120) configured to vary the flow of escaping air through the exhaust outlets (120). The steering system also includes a target seeker (121), one or more pressure sensors (119) mounted in the pressure chamber (116) and a control unit (122) for controlling flight of the guided projectile (10).

Abstract: A reliable and inexpensive attitude control system uses a plurality of pitch-over thrusters to perform rapid and precise attitude maneuvers for a flight vehicle. The pitch-over thrusters create rotational moments that directly pitch and yaw the flight vehicle. The use of very simple thrusters and control techniques provides for a reliable and cost effective solution. The ability to perform overlapping pitch and yaw maneuvers with single-shot fixed-impulse thrusters provides for high-speed maneuverability.

Abstract: The present invention provides a MKV interceptor including multiple kill vehicles with autonomous management capability and kinematic reach to prosecute a large threat extent. Each KV can self-manage its own KV deployment and target engagement for a determined target volume assigned by a designated master KV. At least one KV is master capable of managing the post-separation of all of the KVs without requiring updates to the mission plan post-separation. The autonomous capability and increased kinematic reach provides for a more efficient use of boosters and more effective engagement of the threat.

Abstract: A spin-stabilized correctible-trajectory artillery shell has a generator in the rotation-decoupled engagement region between a canard guidance unit and its munition body. The generator can be switched over to avoid load fluctuations between an adjusting motor and a substitute load. In order to avoid an additional heat source in the interior of the guidance unit the substitute load is in the form of an electrical resistance on, at or in canard surfaces behind the afflux flow edges. The canard surfaces are preferably formed on anti-spin canards which are not adjustably mounted.

Abstract: According to an embodiment of the present invention there is provided a kill-vehicle to be used in an exo-atmospheric anti-missile interceptor aimed at hitting a target, the kill-vehicle having a main body and comprising: an electronic box; a sensor unit coupled to the electronic box and including at least one sensor for tracking the target at a certain field of view; an inertial measurement unit coupled to the sensor unit; and a divert system controlled by the electronic box for providing the kill-vehicle with thrust at a desired direction; said divert system and electronic box constituting said main body, wherein the kill-vehicle further comprises at least one gimbals unit coupled to the main body and to the sensor unit for controllably changing an angle between the sensor unit and the main body, and wherein said electronic box is configured to synchronically operate said divert system and gimbals unit such that the target remains in the field of view of said at least one sensor and the thrust is provided i

Abstract: An apparatus for changing the angle of attack of a cavitator on a supercavitating underwater research model. The apparatus has a nose assembly that has a pivotable cavitator tilt plate, an actuator member and a drive system engaged with the actuator member to drive the actuator member so as to tilt the cavitator tilt plate to a desired angle. Power components are remotely located and accessible to an operator so as to enable an operator to vary the angle of the cavitator tilt plate while the supercavitating underwater research model is underwater and in motion.

Abstract: Methods and apparatus for projectile systems according to various aspects of the present invention comprise a projectile attached to an auxiliary control system. The auxiliary control system may include a control system and a transverse propulsion system. The control system controls the trajectory of the projectile system, for example by activating the transverse propulsion system to adjust the trajectory.

Abstract: The Trajectory Correction Kit (TCK) is a completely self-contained retrofit kit that is externally and fixedly mounted as an add-on to the rear (aft of the tailfins) of an existing, unguided rocket. The TCK continuously measures the pitch and yaw of the rocket as it is released from the launch tube and during the initial seconds of the flight and calculates the trajectory correction that is necessary to eliminate the measured pitch and yaw. Then it activates selected thrusters among the thrusters that are positioned around the circumference of the rocket body so as to steer the rocket in a direction until the measured pitch and yaw are eliminated. This results in significant reductions in both the rocket flight path dispersion and collateral damage.

Abstract: A missile includes a control system having divert and attitude control system thrusters with control valves. Each of the control valves has a nozzle plate having a plurality of small nozzles therein. The nozzle plate includes a pair of portions, one of which is rotatable relative to the other. Control of flow through the nozzle plate may be effected by relative positioning of the portions of the nozzle plate. An upstream convergent portion of the nozzle plate may be fixed relative to the missile, with a downstream throat and/or divergent portion of the nozzle plate moveable. Movement of the movable portion of the nozzle plate may be accomplished by use of an actuator that is external to the missile body. The control valve provides a simple, lightweight and compact way of controlling flow from a divert thruster.

Abstract: A lateral thrust control is provided for influencing the flight trajectory of a projectile. The control has a main control unit; a central, axially extending main recess in the main control unit; a plurality of thruster recesses in the main control unit for accepting correction thrusters; an ignition element for one of the correction thrusters disposed in each of the thruster recesses; and at least one tubular conductor support of an electrically insulating material arranged inside the main recess of main control unit. At least some of the electrical conductors are in the form of conductive tracks fixedly arranged on the at least one tubular conductor support such that a particular contact element for a particular ignition element contacts the conductive track assigned to the particular contact element.

Abstract: A missile includes a tail section having a multi-nozzle grid with both fixed nozzlettes, and movable, thrust vector nozzlettes. The movable nozzlettes may be configured in a number of discrete array bars, each containing multiple of the movable nozzlettes. Movement of one or more array bars may be used to vector the thrust of the missile, providing roll, yaw, or spinning of the missile, for example.

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 or hot burning gases 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.

Abstract: A diverter valve includes a valve bore having a set of valve seats associated with each fluid outlet port. Each set of valve seats is at least partially separated from one another by a flow channel. The valve seat configuration increases the impact area for the valve element. As a result, the impact force upon seating against the valve seats is reduced. Moreover, by including flow channels between the sets of valve seats, the switching force and performance of the valve element is not adversely affected.

Abstract: A vehicle, such as a missile, with a pilot valve system controls the vehicle's thrust valves despite a hostile propellant gas environment. The pilot valve system can have one or more pilot valves. Using refractory elements, the pilot valve ball reciprocates between a supply seat and a vent seat which is subject to the filtered inflow of propellant thrust gases. When open, the pilot valve allows the stray thrust gas to communicate to a control chamber which closes a poppet against a valve seat in the nozzle. When an associated solenoid closes the pilot valve by pushing the pilot valve ball against the supply seat, the control chamber is vented to ambient. The poppet may then travel into the cylinder bore and the nozzle is opened to exhaust propellant gases and exert lateral thrust on the vehicle. Certain nozzle thrust geometries provide useful vehicle guidance.

Abstract: An ordnance system of the present invention may include or feature any one or more of: a control unit, one or more effectors (detonators, initiators, shaped charges and the like), and a two-, three- or four-wire communication bus between the control unit and the effectors; an addressable system in which all the effectors can be connected to the same communication bus and the control unit can issue coded signals on the bus addressed to a specific effector; inductive coupling between the effectors and the communication bus; and a multi-voltage level communication system in which communication signals are carried at a first voltage and arming signals are provided at a second, higher voltage. Other features may include two-way communication between effectors and the control unit and the de-centralization of firing control so that the control unit does not have exclusive control over whether the effectors function.

Abstract: A three-axis attitude control propulsion device and a flying object like a rocket comprising the same are provided in which combustion gas for attitude control can be efficiently used. A three-axis attitude control propulsion device 4, having six nozzles, comprises a motor case 6 and three-way discharge changeover valves 10, 10′ of a valve plug rotation type enabling a changeover of flow passage by rotation of the valve plug. Combustion gas 18 is generated by combustion of propellant 8 in the motor case 6. The three-axis attitude control propulsion device is operated so that one or two of the nozzles are opened to thereby discharge the combustion gas 18 and the remaining 5 or 4 nozzles are fully closed. Thereby, a three-axis attitude control of pitch control, roll control and yaw control and a control of neutral state are selected.

Abstract: A guidance seeker system for a projectile includes a plurality of photoconductive sensing elements symmetrically disposed about a central axis of the projectile. When a target is illuminated with a light source, a lens transmits light reflected from the target to one or more of the photoconductive sensing elements. Dependent on which photoconductive sensing element is irradiated, a variance between the line of flight of the projectile and the target is determined. A voltage impulse resulting from irradiation of the photoconductive sensing element triggers actuation of a course corrector, such as a diverter, to nudge the line of flight of the projectile to increase the likelihood of the projectile reaching the desired target. This guidance seeking system is particularly effective when the target is designated with a pulsed laser.

Abstract: A fuzing system for non-spinning or substantially non-spinning weapons is implemented by means of wide angle optics providing at least forward-hemisphere coverage, an array of infrared detectors and a microprocessor for image and data processing, aim-point selection, directional-warhead aiming and skewed-cone fuzing. The skewed-cone fuzing has a generatrix which is the vector sum of missile velocity, warhead velocity and the negative of target velocity.

Abstract: A nacelle comprised of a rigid shroud and a support truss. The shroud encloses the truss and a rocket engine. The shroud is comprised of three sections, including a top section and two side sections. The top section has openings to permit the communication of lines for liquid propellant, electrical current, and hydraulic fluid between the engine and an attached flight vehicle. The two side sections are connected to each other by longitudinal field joints, and to the top section by a circumferential field joint. The rocket engine is attached to the flight vehicle by a gimbal allowing the engine to rotate relative to the flight vehicle about orthogonal pitch and yaw axes. A pair of actuators is located in the flight vehicle, one to control the rotation of the rocket engine about the pitch axis, and the other to control its rotation about the yaw axis. The truss is attached to the body of the rocket engine.

Abstract: A control system for a flying vehicle in an atmospheric environment, the vehicle having an aerodynamic shape including a front end and a rear end including a plurality of attitude control jet nozzles spaced outward from the vehicle near the rear end of the vehicle or a trailing edge of a vehicle part; and a generator for providing a low mass flow of a fluid through the attitude control jet nozzles to create an area of high pressure immediately forward of the nozzles and adjacent the flying vehicle, wherein the location of the attitude control jet nozzles is so close to the rear end of the vehicle that any area of low pressure created by the low mass flow of fluid through the attitude control jet nozzles does not contact the vehicle.

Abstract: A control system for a flying vehicle in an atmospheric environment, the vehicle having an aerodynamic shape including a front end and a rear end including a plurality of attitude control jet nozzles spaced outward from the vehicle near the rear end of the vehicle or a trailing edge of a vehicle part; and a generator for providing a low mass flow of a fluid through the attitude control jet nozzles to create an area of high pressure immediately forward of the nozzles and adjacent the flying vehicle, wherein the location of the attitude control jet nozzles is so close to the rear end of the vehicle that any area of low pressure created by the low mass flow of fluid through the attitude control jet nozzles does not contact the vehicle.

Abstract: An device for correcting the in-flight trajectory of a munition consists of an impulse motor assembly body. The slug or multiple slugs and propellant(s) are located within the impulse motor assembly body. When a trajectory correction is desired and required, the individual impulse motor propellants are activated and fired, and the slug or multiple slugs are propelled out of the in-flight munition at a specific time and a specific angle on or near the gravimetric center of gravity of the in-flight munition. The reactive forces created by the explosion of the(se) heavy metal slugs does, by equal and opposite reaction, create a corrective vector and thereby does cause a correction in the trajectory of the in-flight munition.

Abstract: A high torque nozzle system for a tube launched rocket has a fixed position nozzle on the rocket and a set of internally positioned erodible vanes inside of the nozzle. The vanes erode as the rocket exits the launcher. The high torque nozzle system has a first section of a rocket nozzle body, a second section of the rocket nozzle body and a torque ring that contains erodible vanes. The torque ring is fitted into a groove formed by the first and second sections of the rocket nozzle body, which are threaded together.

Abstract: The MLRS1 artillery rockets (11) which are stored in the depots of the consumer can enjoy in a technologically non-critical fashion an increase in performance in the sense of a substantially improved degree of delivery precision, insofar as the ogival head (13) is temporarily cut off so that it is possible to fit into same and thus into the foremost region of the original payload space (15), which is behind the fuse (12), in a position of surrounding the pyrotechnic delivery ejection system, an annular assembly frame (21) for a transverse thrust unit (23) with reaction elements (25), which blow out radially around the rocket, which, in dependence on position, can be individually triggered by a navigation satellite-supported course correction unit (20) which is also fitted there.

Abstract: A rocket spin control system for a tube launched rocket has a fixed position nozzle on the rocket and a set of internally positioned torque ring inside of the nozzle that is anchored with erodible tabs. The tabs erode as the rocket exits the launcher. With the erosion of the tabs, the torque ring is free to rotationally move, which eliminates any torque imparted onto the rocket while retaining the torque ring with the rocket. This increases the reliability of rocket precision.

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: A system for controlling the trajectory of a launched projectile. More particularly, a method for correcting the projectile jump displacement of a launched projectile after it is released from a vessel using on-board G-hardened accelerometers orthogonally mounted along the longitudinal axis of the projectile. Deviation from an intended flight path is corrected by firing selected trajectory diverting thrusters mounted around the periphery of the projectile. Eliminating or reducing projectile jump, or the angular deviation of the flight path of a projectile relative to its intended trajectory, will greatly increase the accuracy of gun fired projectiles.

Abstract: A system for guiding projectiles to a target. More particularly, a system for the guidance of projectiles toward a target using a photo detector array (18) and an arrangement of single use thrusters (22). The system is capable of guiding projectile to targets after firing from extended distances.

Abstract: A dissolvable jet vane (22/30) is a composite structure, having a support frame (38), a plug leading edge (40) connected to the forward edge (42) of the frame (38), and an insulation layer (44) on the side walls of the support frame (38). The dissolvable jet vane materials withstand the pressure and thermal loads associated with missile steering during the first few seconds of rocket boost until the missile attains sufficient speed to use conventional external aerodynamic control fins for steering control. Once control passes to the external fins, the jet vanes rapidly and uniformly dissolve in the exhaust stream. The dissolvable jet vane provides a lightweight, reliable means of removing steering jet vanes from the exhaust stream of a solid rocket motor nozzle.

Abstract: The thrust device comprises a valve body (20) having a chamber (24) surrounding part of the needle, at least one gas admission opening (27) opening out into the chamber, and a gas outlet opening (25) opening out into the chamber and defined by a wall portion which co-operates with a nose portion (14) of a moving needle (10) to define an outlet section for gas leaving the chamber. Actuator means (40, 41, 43) control the position of the needle in the valve body by acting on a rear end portion of the needle. The nose (14) of the moving needle (10) has an aerodynamic concave profile (15) and the wall portion (29) which defines the outlet (25) from the chamber is shaped in such a manner as to be capable of directing the exiting gases essentially against the concave side of the nose of the needle, which needle acts as the main member for taking up thrust.

Abstract: A fin disengagement device for limiting the range of a projectile uses an electronic safe and arm circuit to sense launch and spin levels. Once armed, the stored energy from the electronic safe and arm circuit is dumped into an initiator or directly to explosive bolts. The initiator ignites an energetic material to separate the fin from the projectile in-flight at a predetermined time. Alternatively, the explosive bolts separate the fin from the projectile in-flight at a predetermined time. In the embodiments using an initiator and energetic material, an opening or cavity in the rear portion of the projectile body or rod adapter acts as a pressure chamber. When enough pressure has built up from the burning of the energetic material, the front hub of the fin section expands enough to disengage the threads and separates the fin section from the projectile body.