Abstract: A vehicle for launching from a gun such as a gas gun and having a housing; preferably incorporating a precessional attitude control system; and utilizing a flared base, fins, or active use of the attitude control system during passage through the atmosphere. Subtly canting the fins can produce desired spinning of the vehicle. The propulsion system can employ liquid, hybrid, or solid fuel. A removable aero-shell assists atmospheric flight with thermal protection being provided by anticipated ablation, an ablative aero-spike, or transpirational cooling. And a releasable sabot enhances the effectiveness of the launch.

Abstract: A system and method for guiding a projectile is presented. A nozzle system includes a boom assembly body that can be attached to a rear end of a projectile. A gas tank in the boom assembly contains pressurized gas. Fins are attached to the boom assembly body to guide the projectile. A valve lets a pulse of gas out of the gas tank. A nozzle expels the pulse of gas to control an angle of attack and lift of the projectile to guide the projectile to a target.

Abstract: An adjustable range munition has at least one gas vent that is selectively variable to affect the amount of force that is directed onto the projectile upon actuation of the propellant section, thereby to control the range of the munition.

Abstract: A vehicle for launching from a gun such as a gas gun and having a housing; preferably incorporating a precessional attitude control system; and utilizing a flared base, fins, or active use of the attitude control system during passage through the atmosphere. Subtly canting the fins can produce desired spinning of the vehicle. The propulsion system can employ liquid, hybrid, or solid fuel. A removable aero-shell assists atmospheric flight with thermal protection being provided by anticipated ablation, an ablative aero-spike, or transpirational cooling. And a releasable sabot enhances the effectiveness of the launch.

Abstract: The present invention relates to a missile or munition with a hierarchical, modular, closed-loop flow control system, more particularly to aircraft or munition with flow control system for enhanced aerodynamic control, maneuverability and stabilization. The present invention further relates to a method of operating the flow control system. Various embodiments of the flow control system involve elements including flow sensors, active flow control devices or activatable flow effectors, and logic devices with closed loop control architecture. The sensors are used to estimate or determine flow conditions on the surfaces of a missile or munition. The active flow control device or activatable flow effectors create on-demand flow disturbances, preferably micro-disturbances, at different points along the various aerodynamic surfaces of the missile or aircraft to achieve a desired stabilization or maneuverability effect.

Abstract: A vehicle for launching from a gas gun having a housing; preferably incorporating a precessional attitude control system; and utilizing a flared base, fins, or active use of the attitude control system during passage through the atmosphere. Subtly canting the fins can produce desired spinning of the vehicle. The propulsion system can employ liquid, hybrid, or solid fuel. A removable aero-shell assists atmospheric flight with thermal protection being provided by anticipated ablation, an ablative aero-spike, or transpirational cooling. And a releasable sabot enhances the effectiveness of the launch.

Abstract: Systems and methods of controlling solid propellant gas pressure and vehicle thrust are provided. Propellant gas pressure and a vehicle inertial characteristic are sensed. Propellant gas pressure commands and vehicle thrust commands are generated. A propellant gas pressure error is determined based on the propellant gas pressure commands and the sensed propellant gas pressure, and vehicle thrust error is determined based on the vehicle thrust commands and the sensed vehicle inertial characteristic. Reaction control valves are moved between closed and full-open positions based on the determined propellant gas pressure error and on the determined vehicle thrust error. The system and method allow the reaction control valves to operate at variable frequencies or at fixed frequencies. The system and method also allows propellant pressure to be commanded to follow a predetermined pressure profile or commanded to vary “on-the-fly.

Abstract: The 6-axis position and attitude of an imaging vehicle's detector assembly is measured by mounting the detector assembly on a compliant isolator and separating the main 6-axis IMU on the vehicle from a secondary IMU comprising at least inertial rate sensors for pitch and yaw on the detector assembly. The compliant isolator couples low-frequency rigid body motion of the vehicle below a resonant frequency to the isolated detector assembly while isolating the detector assembly from high-frequency attitude noise above the resonant frequency. A computer processes measurements of the 6-axis rigid body motion and the angular rate of change in yaw and pitch of the isolated detector assembly to mitigate the drift and noise error effects of the secondary inertial rate sensors and estimate the 6-axis position and attitude of the detector assembly.

Abstract: Some embodiments relate to a method of controlling a flight of a flight vehicle according to a first mode of operation and changing the mode of operation to a second mode of operation having a different bandwidth than the first mode of operation. Other embodiments relate to a flight-control system for a flight vehicle configured to control a flight of a flight vehicle according to a first mode of operation and to control the flight of the flight vehicle according to a second mode of operation to use less energy than the first mode of operation. Other embodiments relate to a control actuation system configured to control positions of aerodynamic elements in a flight vehicle in response to commands from a guidance system according to a first mode of operation and to change the mode of operation to a second mode of operation having a different bandwidth than the first mode of operation.

Abstract: Higher Order Sliding Mode (HOSM) control techniques are applied to the Guidance Control (G&C) of interceptor missile in which velocity may be steered by combination of main thrust, aerodynamic lift and lateral on-off divert thrusters, and attitude may be steered by continuous or on-off actuators. Methods include the pointing of the seeker, its associated estimation processes, a guidance law that uses concurrent divert mechanisms, and an attitude autopilot. The insensitivity of the controller to matched disturbances allows the concurrent usage of the divert mechanisms without adverse effect on the accuracy. The controller also allows the de-coupling of the control of roll, pitch and yaw channels, and usage quaternions to represent body attitude and it provides control perfect robustness. While it conceivable to design separately the components of the G&C method, it is widely accepted that designing them in an integrated fashion usually produces a better result.

Abstract: The present invention relates to a missile or aircraft with a hierarchical, modular, closed-loop flow control system and more particularly to aircraft or missile with a flow control system for enhanced aerodynamic control, maneuverability and stabilization. The present invention further relates to a method of operating the flow control system. Various embodiments of the flow control system of the present invention involve different elements including flow sensors, active flow control device or activatable flow effectors and logic devices with closed loop control architecture. The sensors of these various embodiments are used to estimate or determine flow conditions on the various surfaces of a missile or aircraft.

Abstract: The present invention relates to a method and a shell (1) for achieving variable firing range and effect when firing from a launcher, which shell (1) contains a firing charge (10), a rocket motor charge (6) with gas outlet (8), a rocket motor nozzle (9) and an active part (5). According to the invention, this is achieved by virtue of the fact that the shell (1) also contains a release mechanism (15) for releasing the rocket motor nozzle (9) from the rocket motor charge (6) after a time delay determined with regard to firing range and effect, and that the rocket motor charge (6) comprises a propellant which is detonable.

Abstract: An apparatus for vectoring the thrust of a motor that produces thrust along a longitudinal axis by expelling combustion gases through a nozzle may include a plurality of linearly-positionable non-rotatable thrust deflectors. The thrust deflectors may be disposed at around a perimeter of the nozzle. Each thrust deflector may be independently extended to simultaneously generate both a force transverse to the longitudinal axis and a torque about the longitudinal axis.

Abstract: A steerable projectile comprises a pressure chamber to hold gas in a pressurized state; and a body section coupled to the pressure chamber, the body section having a flight system to use the pressurized gas for adjusting a trajectory of the projectile. The pressure chamber comprises an orifice in a wall of the pressure chamber; and a check valve corresponding to the orifice, the check valve configured to allow gas that results from ignition of a propellant to enter the pressure chamber via the corresponding orifice and to prevent the gas, once inside the pressure chamber, from exiting the pressure chamber via the corresponding orifice.

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: An actuation assembly is provided. The actuation assembly includes a casing, a plurality of linear actuators coupled to the casing, each of the linear actuators having first and second components and being configured to move the second component thereof relative to the first component thereof along a respective first axis, and a plurality of translational member sets, each being coupled to the second component of a respective one of the linear actuators and the casing and being configured such that when the second component of the respective linear actuator moves along the respective first axis, a selected portion of the translational member set moves substantially along a respective second axis.

Abstract: A method for correcting a trajectory of a projectile is provided, in that a laser beam is guide or rotated around a center of the instantaneous target course of a projectile in such a way that the projectile itself detects a divergence thereof and subsequently carries our a selfcorrection. A first laser beam is emitted over a certain region around the target course of the projectile that can at about the same time initiate a start of a timing process. A further rotating laser beam having a fixed rotational frequency ? can be simultaneously positioned around the region. Via the second laser beam, the projectile recognizes a divergence thereof from the target course and initiates a correction based on the determined divergence, whereby a magnitude thereof is then used to effect the timed initiation of the correction. Thus, delays in the release are implemented in the projectile.

Abstract: A method for correcting a trajectory of terminally guided ammunition is provided. In order to achieve a high probability of hits, in particular when firing in bursts (continuous fire, rapid single shot fire), it is provided that every individual ammunition is addressed separately. The “imprinting” is performed based on the beam rider guidance principle of terminally guided ammunition. Every individual ammunition reads only the guidance beam identified for this ammunition and can, using additional information, determine its absolute roll attitude in space in order to achieve the proper triggering of the correcting propulsion unit.

Abstract: This invention relates to the construction of a rocket motor and fuel system thereof and, in particular to a new and useful Viscous Liquid Monopropellant (VLM) rocket motor containing a liquid propellant that is pumped into the combustion chamber, atomised and then ignited. The atomisation step significantly increases the surface area of the propellant, delivering faster burn rates and smoother combustion. VLM is a non-Newtonian fluid containing both oxidisers and fuels. These monopropellants are comprised of a variety of liquid and solid components, mixed together to form a homogenous fluid, although heterogeneous in composition. The solid constituents are retained within the liquid phase by dispersion, suspension, bonding or chemical emulsification techniques, so as when a motive force is applied to the propellant, all the constituents are also transported, and held in correct proportion whilst doing so.

Abstract: A projectile is guided by employing heat, generated from the aerodynamic heating of a surface of the projectile while the projectile is in flight, to vaporize a material stored within the projectile. The resulting gas is used to guide the projectile.

Abstract: A spin rate tracking system comprising a guidance system suitable for adjusting a flight path of a vehicle based on a spin rate of the vehicle, a signal reception system configured for receiving signal information from a global navigation system wherein a spin rate of the vehicle is derived from a substantially harmonic pattern produced amongst a global navigation signal.

Abstract: A weapon interceptor projectile has a deployable frame for maintaining a deployable net in shape. The deployable frame may be an inflatable structure, including a flexible material inflated by a gas generator. The inflatable structure has a perimeter that supports an outside shape of the net, and a series of spokes or arms that couple the perimeter to a body of the projectile. The perimeter may have an airfoil cross-section shape, reducing drag of the frame and aiding in deployment. The perimeter may be have a circular shape, giving the net a circular area. The deployable frame allows the net to maintain its shape during flight, increasing its area and its ability to come into contact with an incoming weapon, such as a rocket propelled grenade (RPG).

Abstract: Embodiments of a propulsion and maneuvering system that may be suitable for use during a terminal phase in an interceptor are generally described herein. The propulsion and maneuvering system may include one or more axial thrusters to provide thrust along axial thrust lines that run through a center-of-gravity of the interceptor and a plurality of divert thrusters to provide thrust in radial directions. The combination of divert and axial thrusters may allow the interceptor to respond to a maneuvering target and may allow the interceptor to increase its velocity along a line-of-sight (LOS) to a target to change target impact/engagement time.

Abstract: There is disclosed a vehicle and methods for maneuvering the vehicle. The vehicle may include a plurality of multiple-impulse rocket motors, each of which comprises a plurality of independently ignitable solid fuel propellant charges, and a processor that generates at least one command to ignite at least one solid fuel propellant charge of at least one of the plurality of multiple-impulse rocket motors.

Abstract: In one embodiment, a projectile is guided by employing heat, generated from the aerodynamic heating of a surface of the projectile while the projectile is in flight, to vaporize a material stored within the projectile. The resulting gas is used guide the projectile.

Abstract: A modular artillery projectile and method of engaging a target. A modular artillery projectile may include a payload module, a guidance module coupled to the payload module and a rear module coupled to the guidance module. The payload module may be selected from a plurality of interchangeable payload modules containing different payloads. The guidance module may include a transverse propulsion system to propel the modular artillery projectile transversely to a longitudinal axis of the modular artillery projectile, a global positioning system receiver, and a control system to control the transverse propulsion system responsive to the global positioning system receiver to guide the modular artillery projectile to a predetermined target position.

Abstract: An adjustable range munition has at least one gas vent that is selectively variable to affect the amount of force that is directed onto the projectile upon actuation of the propellant section, thereby to control the range of the munition.

Abstract: A vehicle for launching from a gas gun having a housing; preferably incorporating a precessional attitude control system; and utilizing a flared base, fins, or active use of the attitude control system during passage through the atmosphere. Subtly canting the fins can produce desired spinning of the vehicle. The propulsion system can employ liquid, hybrid, or solid fuel. A removable aero-shell assists atmospheric flight with thermal protection being provided by anticipated ablation, an ablative aero-spike, or transpirational cooling. And a releasable sabot enhances the effectiveness of the launch.

Abstract: The present invention relates to a missile or aircraft with a hierarchical, modular, closed-loop flow control system and more particularly to aircraft or missile with a flow control system for enhanced aerodynamic control, maneuverability and stabilization. The present invention further relates to a method of operating the flow control system. Various embodiments of the flow control system of the present invention involve different elements including flow sensors, active flow control device or activatable flow effectors and logic devices with closed loop control architecture. The sensors of these various embodiments are used to estimate or determine flow conditions on the various surfaces of a missile or aircraft.

Abstract: An actuator stack is provided and having a tubular body and two or more individual actuators stacked in a longitudinal direction in the tubular body. Where each of the two or more actuators have a solid propellant; a primer for igniting the propellant; and detonation wiring for powering the primer. The actuator stack further having a separation layer formed between adjacent individual actuators in the stack.

Abstract: An active vortex control system (AVOCS) includes a set of primary injectors that inject gas into a cavity to generate a vortex in front of and possibly around components inside the cavity. The vortex interferes with an external flow field in an opening to the cavity to protect the components from the external environment. Sets of secondary injectors may inject gas at a reduced mass flow into the cavity to compensate for energy losses to maintain the coherence of the vortex. The AVOCS is well suited for use in windowless endo- and exo-atmospheric interceptors to protect the electro-optical imagers and optical components from Earth atmosphere.

Abstract: A missile in which a nose portion is rotatably mounted on a main body portion of the missile and is subjected to thrust to bring it to a demanded roll attitude and to apply to it a demanded lateral steering force. The thrust is produced by a propellant gas and supplied to discharge ducts in the nose portion which provide for the discharge of the propellant gas tangentially with respect to the nose portion. The discharge ducts are selectively opened and closed by relative axial displacement of the nose portion and a valve spool which controls the flow of propellant gas. An actuator responsive to guidance control signals causes a predetermined roll torque to bring the nose portion to a demanded roll attitude and a predetermined lateral steering force on the missile.

Abstract: A matrix of explosive cells can include plural explosive cells formed in an array in a common substrate. Each cell can be formed as a recess filled with explosive material. An ignition device has an addressable ignition source for each cell. This matrix can be used in combination with a projectile guidance system. The projectile guidance system includes an antenna, a transceiver and a control processor. A method of guiding a projectile can include firing a projectile at a target, tracking the projectile and the target, determining a desired change in a flight path of the projectile, transmitting guidance commands to effect the desired change in the projectile's flight path to the projectile, receiving the guidance commands onboard the projectile and selectively igniting an explosive cell in a matrix of addressable explosive cells contained in a common substrate using the guidance commands.

Abstract: A control system for a maneuverable kill vehicle is provided. The control system includes a pressurized fluid source configured to provide a pressurized fluid, a valve in fluid communication with the pressurized fluid source, and a voice coil actuator comprising a magnet and a conductive coil oriented relative to the magnet such that when current flows through the coil, the coil moves relative to the magnet. The voice coil actuator is coupled to the valve such that the relative movement of the coil causes an adjustment in a flow rate of the pressurized fluid through the valve.

Abstract: Methods and apparatus for a fast action impulse thruster according to various aspects of the present invention may comprise a projectile comprising an impulse thruster system. The impulse thruster system may comprise a guidance system and a fast action impulse thruster system. The guidance system may control the trajectory of the projectile, for example by activating the fast action impulse thruster system to adjust the projectile's trajectory. The fast action impulse thruster system may be configured such that it may provide an impulse force to guide the projectile with a reaction time that is not affected by the rotational velocity of the projectile. The impulse force may be achieved by ejecting at least one mass from the projectile at high velocity such that a resulting momentum exchange may alter the trajectory of the projectile.

Abstract: Methods and apparatus for a fast action impulse thruster according to various aspects of the present invention may comprise a projectile comprising an impulse thruster system. The impulse thruster system may comprise a guidance system and a fast action impulse thruster system. The guidance system may control the trajectory of the projectile, for example by activating the fast action impulse thruster system to adjust the projectile's trajectory. The fast action impulse thruster system may be configured such that it may provide an impulse force to guide the projectile with a reaction time that is not affected by the rotational velocity of the projectile. The impulse force may be achieved by ejecting at least one mass from the projectile at high velocity such that a resulting momentum exchange may alter the trajectory of the projectile.

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 method of controlling flight of a missile includes using gyroscopes, such as pitch rate gyroscopes, to sense when a factor based on the angular rate of change of the missile exceeds a threshold value. One the threshold value is exceeded, a decision may be made to use one or more compensation thrusters to reduce the angular rate of change. The use of the compensation thrusters may correct residual angular velocities from a pitch over maneuver used to put the missile on an intended course. In addition, the compensation thrusters may be used to compensate for errors in missile heading induced after the pitch over maneuver, such as induced by misalignment of thrust provided by a main rocket motor of the missile. Multiple compensation thrusters may be used to compensate for angular changes in the pitch and yaw directions.

Abstract: A guided fuse is provided for installation on a projectile at its nose. The fuse includes a conical frustrum housing, a pair of control panels rotatably connected to pivotable knuckles, and a pair of drag panels disposed on hinges. Each of the control panels releases on command from stowage to deployment. Stowage configuration disposes each control and drag panel to conform against the housing, whereas deployment configuration separately splays the control and drag panels radially outward from the housing. In response to maneuver commands, each control panel turns on one of the knuckles along a radial control axis substantially perpendicular to the longitudinal axis. The control panels turn together either the same angular direction or the opposite angular direction. The control and drag panels form a cruciform pattern along the exterior.

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. Although this approach is applicable to provide attitude control for any flight vehicle including all types of missiles, kill-vehicles and space craft, it is particularly applicable for smaller highly maneuverable cost-constrained missile systems. One such system is an “Active Protection System” or APS in which a missile system is integrated with a vehicle such as a HumVee or armored personnel carrier to provide defensive counter-measures against possible attack.

Abstract: Methods and apparatus for a missile having an external system operate in conjunction with an airframe and a fluid transfer system. The airframe includes an interior surface defining a substantially enclosed internal chamber. The fluid transfer system selectively connects the internal chamber to the external system, for example to provide pressurant or coolant to the external system.

Abstract: A ring portion including: a ring body; and one or more actuators formed therein for providing thrust to a projectile and configured for fastening to a shell of an airborne device to form a portion of the shell. The airborne device can be a projectile.

Abstract: A multiple-stage solid rocket motor is operated in a manner designed to control its mass discharge profile. This is accomplished by providing means for igniting one stage and then igniting a subsequent stage while the first continues to burn.

Abstract: A steerable projectile comprises a pressure chamber to hold gas in a pressurized state; and a body section coupled to the pressure chamber, the body section having a flight system to use the pressurized gas for adjusting a trajectory of the projectile. The pressure chamber comprises an orifice in a wall of the pressure chamber; and a check valve corresponding to the orifice, the check valve configured to allow gas that results from ignition of a propellant to enter the pressure chamber via the corresponding orifice and to prevent the gas, once inside the pressure chamber, from exiting the pressure chamber via the corresponding orifice.

Abstract: A method of controlling flight of a missile includes using gyroscopes, such as pitch rate gyroscopes, to sense when a factor based on the angular rate of change of the missile exceeds a threshold value. One the threshold value is exceeded, a decision may be made to use one or more compensation thrusters to reduce the angular rate of change. The use of the compensation thrusters may correct residual angular velocities from a pitch over maneuver used to put the missile on an intended course. In addition, the compensation thrusters may be used to compensate for errors in missile heading induced after the pitch over maneuver, such as induced by misalignment of thrust provided by a main rocket motor of the missile. Multiple compensation thrusters may be used to compensate for angular changes in the pitch and yaw directions.

Abstract: A non-propulsive projectile and method of maneuvering the non-propulsive projectile. The non-propulsive projectile includes a divert system with a multiple of valves to maneuver the projectile in response to a control system.

Abstract: An aeronautical vehicle includes at least one set of tandem divert thrusters incorporated into the body. Each set of tandem divert thrusters includes a first divert thruster and a second divert thruster, each configured to provide substantially equal thrust forces at substantially the same time and in substantially opposite directions such that the moment reference point lies between the first and second divert thrusters.

Abstract: A tubular distributor in a missile having a right-angled hollow tubular first section, the right-angled hollow tubular first section having a first leg and a second leg, a straight hollow tubular second section, an end of the first leg of the right-angled hollow tubular first section perpendicularly connected to a first end of the hollow tubular second section, a straight hollow tubular third section, a first end of the hollow tubular third section perpendicularly connected to the first end of the straight hollow tubular second section, and a close/open valve positioned within the straight hollow tubular third section, the close/open valve positioned between a gas generator and the straight hollow tubular second section.

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: There is disclosed a vehicle and methods for maneuvering the vehicle. The vehicle may include a plurality of multiple-impulse rocket motors, each of which comprises a plurality of independently ignitable solid fuel propellant charges, and a processor that generates at least one command to ignite at least one solid fuel propellant charge of at least one of the plurality of multiple-impulse rocket motors.