Abstract: A system and method for detecting breaklock for correlation trackers. The inventive system includes a first circuit (50) for computing energy EL in a residual image, a second circuit (52) for computing energy EI in an input image, and a third circuit (54) for computing a residual metric RL based on the residual image energy EL scaled by the input image energy EI. In the illustrative embodiment, the system further includes a fourth circuit (56) for comparing the residual metric RL to a threshold TR, and a fifth circuit (58) for setting a breaklock signal based on the output of the fourth circuit (56).

Abstract: Applicants' ATR system is weather-agile because it is comprised of a primary target sensing means that is capable of surveilling the target scene in foul or fair weather, and a secondary target sensing means that is also capable of sensing targets in various weather. The primary and secondary sensing means communicate through a control center so that ultimately, among several weapons available, the most strategically located and equipped weapon is activated for the destruction of a selected target, given the weather. The control center accomplishes the communication by receiving the sensed target signature from the primary sensing means, processing the signature using database already resident in the center and transmitting the processed target signature to the weapon possessing the greatest potential for successfully destroying the target.

Abstract: The present invention relates to a projectile seeker which comprises: (a) A hollow in the projectile for accommodating a light sensor; (b) A light sensor located within said hollow for sensing light which is emitted or reflected from a target, and for producing an electronic signal upon sensing such emitted light; and (c) A longitudinal shaped opening at the slanted front-side surface of the projectile for enabling a shaped field of view to said light sensor which is limited by the boundaries of said opening, the opening width varies in a direction from the front to the back of the projectile in order to cause said electronic signal to depend on the spinning of the projectile and to be proportional to the orientation of the projectile with respect to the object.

Abstract: A projectile navigation system operable within an extremely high G-shock loading environment during the launch phase may include a set of Kalman filters configured to repeatedly calculate a navigational solution by solving a set of non-linear equations of motions of the projectile utilizing a current parameter vector, position, velocity, and attitude of the projectile. The system may include a suite of solid state sensors to calibrate the Kalman filter equations. If desired, the system may also include a satellite based positioning-determining (SBPD) attitude determination system configured to update the state of the host projectile by making real time attitude measurements of the projectile, and a parameter estimator configured to estimate and update a parameter vector of the host projectile. An external guidance and control processor may be used to generate guidance and control signals, enabling real time navigation of the host projectile.

Abstract: A method of mapping a first array to a second array is useful where (1) each of the arrays has pixels in sequential columns and rows and the first array has sequential integers identifying each row of pixels, (2) sequential integers identify each column of pixels, and a numerical value is associated with each pixel, (3) the first and second arrays have (or can be made to have) a one to one pairing between columns of the first and second arrays, and (4) groups of four unique pixels in the same column of the first array are paired one to one with a pixel in the paired column of the second array.

Abstract: A plurality of sensor vehicles collect imaging data from an assigned location of a target region having targets and non-targets. The imaging data may be combined based on its location and the combined data is matched to a threat object map to identify the actual targets from the non-targets. In some embodiments, the sensor vehicles may be redirected to collect velocity and/or range information on the identified targets.

Abstract: An unmanned airborne reconnaissance system, the unmanned airborne reconnaissance system including a lightweight, portable, powered aircraft and a foldable launch rail, the aircraft, in a broken down condition and the launch rail in a broken down condition fitable inside a box, the box capable of being carried by one man. The launch system includes an elongated launch rail with the carriage assembly, and a propulsion means for accelerating the carriage assembly from one end of the launch rail to the other. The carriage assembly releasably engages the aircraft so as to propel the aircraft from one end of the launch rail to the other. The propulsion may be by a cartridge that explodes and releases a gas through a cylinder, or by elastic cords. The aircraft is guided through the air either by a programmed onboard computer which controls the control surfaces of the aircraft and/or by remote control. The aircraft typically contains a camera for recording and transmitting images received from the ground below.

Abstract: A method and apparatus for thrust vectoring a flight vehicle during homing are disclosed. The flight vehicle includes a body; a plurality of attitude control mechanisms on the body; a multi-pulse motor housed at least partially in the body; and a control unit housed in the body. The control unit generates signals controlling an actuation of the attitude control mechanisms and the multi-pulse motor to initiate a follow-on burn of the multi-pulse motor to effect a maneuver directed by the actuation of the attitude control mechanisms. The method includes conserving a second burn of a dual pulse motor until target acquisition; acquiring a target; actuating a attitude control mechanism for the flight vehicle to alter the flight vehicle's heading; and initiating the second burn.

Abstract: A device and method for guiding or steering projectiles (self-propelled or non-self-propelled), or missiles, and for steering a supersonic projectile, or a missile, having a nose, generally in the shape of a cone, having a more or less pointed end, and capable of creating a plasma discharge near the end of the projectile over a limited sector of the outer surface of nose.

Abstract: The present invention is a method of interception. When a missile is launched and detected by a satellite, an anti-missile rocket is launched to intercept it. When the anti-missile rocket nears the point of interception, it goes into a turn of about 180 degrees, to reverse its course, and comes in behind the enemy missile, at a speed almost equal to that of the ICBM. In this maneuver, coming in behind the ICBM, it reduces the relative speed of the two rockets from about 13,000 mph to about 50 mph, and allows the interceptor missile to approach the ICBM at a slow speed and easily destroy it.

Abstract: A method for enhancing an aerodynamic performance of an unmanned projectile. The method including at least one of the following: (a) morphing a cross-sectional shape of the projectile after launch thereof; (b) morphing a longitudinal shape of the projectile after launch thereof; (c) bleeding a fluid at a base of the projectile during flight thereof: (d) varying a base cone angle of the projectile as a function of speed thereof; (e) deploying at least one wing from a body of the projectile after launch thereof; and (f) deploying a fin from the body of the projectile after launch thereof.

Abstract: Applicants have invented a guidance system for guiding a projectile, the projectile having a body portion capable of being spun in a first direction and a nose portion connected to the body portion by a spin control coupling, the nose portion being capable of being spun in a second direction. The nose portion including first and second aerodynamic surfaces fixedly attached to the nose portion and configured and arranged to cause the nose portion to spin in a second direction during projectile flight. The nose portion including third and fourth aerodynamic surfaces fixedly attached to the nose portion, which are configured and arranged such that when the nose portion is spinning the third and fourth aerodynamic surfaces have no net effect on projectile flight, but when the nose portion is despun using the spin control coupling, the third and fourth aerodynamic surfaces induce both a moment and a lateral force to the nose, causing the projectile flight path to change.

Abstract: A system and method for performing in-orbit alignment calibration using on-board attitude sensors to improve reflector alignment after deployment to improve spacecraft pointing.

Abstract: A projectile comprises an imaging seeker at a front of the projectile; a front warhead behind the imaging seeker; a power supply; an electronics unit connected to the power supply and comprising a microprocessor circuit board, a voltage regulator circuit board, an inertial measurement circuit board and a fuze and safe and arm circuit board, all electrically connected to each other, the microprocessor circuit board also being connected to the imaging seeker; a rear warhead, the front and rear warheads being electrically connected to the safe and arm circuit board; a rocket motor electrically connected to the electronics unit; foldable fins mounted at the rear of the projectile; a shell that encases the front warhead, the power supply, the electronics unit, the rear warhead and the rocket motor; and a maneuver mechanism disposed in the shell and electrically connected to the microprocessor circuit board.

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: A system and method of providing situational awareness and weapon targeting is presented. The method includes determining the location of one or more enemy sites and one or more friendly sites. A “Do Not Engage” (DNE) zone is determined around each of the friendly sites and an “Allowable Engagement” (AE) zone is established around each of the enemy sites, wherein none of the AE zones overlap any of the DNE zones. An engagement plan is then determined based on the AE zones and integrity bounds on candidate munitions. The system includes a processing and communications network and a sensor element in communication with the processing and communications network. The system also includes a command control element in communication with the processing and communications network and an operating elements section in communication with the processing and communications network.

Abstract: A method for enhancing an aerodynamic performance of an unmanned projectile. The method including at least one of the following: (a) morphing a cross-sectional shape of the projectile after launch thereof; (b) morphing a longitudinal shape of the projectile after launch thereof; (c) bleeding a fluid at a base of the projectile during flight thereof: (d) varying a base cone angle of the projectile as a function of speed thereof; (e) deploying at least one wing from a body of the projectile after launch thereof; and (f) deploying a fin from the body of the projectile after launch thereof.

Abstract: The Multiple-Antenna Jamming System (MAJS) is useful for missile-borne jamming of active protection system radars that operate in close proximity to the frequency band of the missile's radio frequency seeker. The MAJS utilizes multiple receiving and transmitting antennas to reduce shadowing effects due to the transmissive radome. It also channelizes the jamming signals into in-seeker-band and out-of-seeker band signals to synchronize the transmission of jamming signals with the emit-listen pattern of the missile seeker and to eliminate the problem of de-sensitizing the RF seeker from the jammer energy. The in-seeker-band jamming signals are transmitted only concurrently with the missile seeker emissions and any signals emanating from an enemy radar are received only during the listen mode of the missile seeker.

Abstract: Pulse integration is utilized on board an optically guided missile or other ordinance device used as a part of a target designation system for extending the lock-on range of the missile by approximately 18%, when a double pulse laser is utilized to illuminate and designate the target. Pulse integration is accomplished with a recirculating delay unit which superimposes the first pulse on the second pulse, such that while the pulses add coherently, noise does not add in phase. The pulse integration technique therefore enhances the signal-to-noise ratio when the missile is at the outer limits of its operating range. When the missile is sufficiently close to the target, doublet decoding is actuated to offer countermeasure resistance. At this point, pulse integration may proceed in lieu of doublet decoding or may be dispensed with in view of the increased signal-to-noise ratio due to the close range of the missile to the target.

Abstract: A missile includes one or more arrays of barrel assemblies that are displaced from the centre of gravity of missile. Each barrel assembly includes a plurality of projectiles axially disposed within a barrel, and each projectile is associated with a discrete propellant charge for propelling the projectile sequentially from the barrel. Each array of barrel assemblies is capable of selectively firing the projectiles from selected barrels, whereby the missile is accelerated by the reactionary force generated by said firing of projectiles and the missile is deflected onto a new course or trajectory. This enables the missile to be steered to intercept its target, even if the target is undertaking evasive manoeuvres. Each barrel assembly may include multiple projectiles.

Abstract: A projectile guidance system without gyros in which the projectile has an orthogonal body coordinate system. The projectile has a triax of accelerometers providing x, y and z acceleration data measured along the x, y and z axes respectively. A GPS antenna and receiver means provides onboard GPS position and velocity data in earth referenced navigational coordinates. A computer and program means stores and accesses time indexed GPS position and GPS velocity data and transforms x, y and z axis acceleration data from body to navigation coordinates. The program means is responsive to corresponding time indexed acceleration data and to GPS velocity and position data for calculating and outputting an estimated projectile roll, pitch and yaw angle via optimal smoothing techniques with respect to local level for each time index iteration of present position to a flight control system, which actuates a divert propulsion system for guiding the projectile to a predetermined location.

Abstract: A covert tracer round has an infrared emitter of radiation mounted to its front, side or back. The radiation (which may be coherent or incoherent) is detected by a sensor that displays an image of the target and the beam. The sensor receives the beam directly if the emitter is on the back of the round and by reflection off the target or nearby objects if the emitter faces forward. The round may include a fixed or moveable collimating lens. The emitter may radiate radially from the round to signal troops or devices located along its path. The round may include sensors that gather significant information about chemicals or biological agents, about magnetic or gravitational anomalies or any other remotely detectable property and transmit that information to the sensor by modulating the emitted radiation.

Abstract: A technique is provided that uses a dual mode seeker (IR and LADAR) for precise target dynamics measurement, which extends stripping to a much higher altitude than ground based radar. Initial results show that this approach works to altitudes in excess of 100 km. Stripping becomes a reliable way to discriminate lighter weight decoys from reentry vehicles at altitudes and ranges consistent with planned divert capabilities for terminal phase missile defense. It is a finding of this invention that the LADAR will improve the spatial resolution by a factor of five over typical missile defense IR seekers using a common aperture. The LADAR provides a 3D angle, angle, range (AAR) image for each laser pulse which is used to extract the precise target state vectors.

Abstract: A system includes an optical system having a curved window with anamorphic symmetry about a first plane and a second plane perpendicular to the first plane. The window may be, for example, in a flight vehicle such as a missile. An optical corrector is adjacent to a curved inner surface of the window and has an optical corrector shape responsive to a shape of the window. The optical corrector has anamorphic symmetry about the first plane and the second plane. A sensor is disposed to receive an optical ray passing sequentially through the window and the optical corrector.

Abstract: A method for facilitating an optimization of a control space in n dimensions is provided. The control space includes a plurality of points, and the method includes removing at least one hyperplane of the control space, and perturbing the remaining points of the control space to lessen errors relative to the control space prior to the removal of at least one hyperplane.

Abstract: A missile, either a powered missile or an unpowered projectile, includes a freely-rolling tail assembly having an odd number of fins. Having an odd number of fins may reduce oscillations caused by the rotation of the freely-rotating tail. This may make a more stable platform for a seeker, such as an uncooled focal point array or other imaging infrared (IIR) or millimeter wave radio frequency (MMW) seeker, in the body of the missile. Also, minimizing oscillation by using an odd number of fins may facilitate control of the missile.

Abstract: The center of pressure of a projectile is caused to move upon the occurrence of an event that changes the static margin, such as the jettisoning of a body previously attached to the projectile, as noted above. In particular embodiments, this is achieved by a flare disposed toward the rear of the projectile. The flare has petals that deploy from a first, stowed position to a second, deployed position upon the occurrence of the event. In the stowed position, the petals are aligned with the air stream, in order to minimize drag. In the deployed position, the petals project into the air stream in such a way as to move the lift center rearward. A slide ring within the flare has sufficient inertia that it shifts aft in response to an acceleration that occurs when the attached body and the projectile are separated from one another. The slide ring is linked to the petals in such a way that the petals are deployed by the displacement of the slide ring. Detents lock the slide ring in its displaced position.

Abstract: A method for protecting a second location against a first projectile fired from a first location at the second location. The method includes: firing at least one second projectile toward the first projectile; and deploying one or more projections from the second projectile to increase its footprint and increase the probability of destroying or changing the trajectory of the first projectile.

Abstract: A system and method for controlling roll in a projectile. The novel system (56) includes first (52) and second (58) sections adapted to counter-rotate relative to each other and a mechanism (76) for inducing the counter-rotation to generate a roll torque on the projectile (50). In the preferred embodiment, the mechanism (76) is a motor comprised of a rotor (64) affixed to the first section (52), and the second section (58) which acts as a stator that rotates around the rotor (64) when a current is applied to the armature. In an alternative embodiment, the second section (58) is turned by a motor (80) attached to the first section (52) which drives a small gear engaging a full-diameter ring gear (82) on the second section (58). In the illustrative examples, the first (52) and second (58) sections are a missile forebody and a tail section of the projectile.

Abstract: A system and method that guides a device to an object using periodically adaptive guidance. The guidance and control system creates a reconstructed line-of-sight (LOS) vector to avoid system destabilization associated with small angle approximation during high bore sight engagements. The guidance system adaptively estimates the periodic maneuver of evasive objects with a set of harmonically balance Kalman filter banks. The Harmonically Balanced Kalman filter banks generate a set of probabilities that weight the effect of each individual Kalman filters on a resultant guidance command signal. The guidance command signal generated by the system acts perpendicular to the object LOS. The guidance and control system uses vectored proportional navigation guidance laws, optimal proportion navigation laws and periodically adaptive augmented guidance laws to generate a guidance command signal to supply to an autopilot.

Abstract: A target designation system for indicating a target to be destroyed by remotely guided ordnance comprising a receiver arranged to produce a receiver output signal in response to an incident electromagnetic signal from an attack aircraft. An auto-switch is connected to the receiver and arranged to produce a power signal in response to the receiver output signal. A transmitter is connected to the auto-switch to be activated by the power signal. When activated, the transmitter transmits a homing signal that indicates its location or the location of the target.

Abstract: A system and method of providing situational awareness and weapon targeting is presented. The method includes determining the location of one or more enemy sites and one or more friendly sites. A “Do Not Engage” (DNE) zone is determined around each of the friendly sites and an “Allowable Engagement” (AE) zone is established around each of the enemy sites, wherein none of the AE zones overlap any of the DNE zones. An engagement plan is then determined based on the AE zones and integrity bounds on candidate munitions. The system includes a processing and communications network and a sensor element in communication with the processing and communications network. The system also includes a command control element in communication with the processing and communications network and an operating elements section in communication with the processing and communications network.

Abstract: A multi-staged missile includes a booster and a submunition delivery vehicle that has one or more submunitions. The booster rapidly accelerates the submunition vehicle, and then separates from the submunition vehicle. The submunition delivery vehicle is then maneuvered to approach a target. Individual submunitions finally separate, and are individually guided to the target. By providing multiple, independently-targeted submunitions, the missile greatly increases the chances of hitting the target.

Abstract: Applicants' Passive Radar Detector for Dualizing Missile Seeker Capability incorporates passive RF detectors into a standard active MMW seeker missile with a minimum requirement for hardware modifications. Anti-radiation homing (ARH) antennas and down conversion elements are added to the missile and coupled to existing signal-processing hardware. The added antennas intercept the air defense radar emission signals and the conversion elements convert the intercepted signals to the intermediate frequency (IF) usable by the MMW radar. The IF can then be processed by signal processor that already exists as a part of the MMW seeker.

Abstract: The present invention relates to a towed/surrogate decoy transmitter connectable via the tow cable to a platform or host aircraft using a wireless communicator link, the link providing useful performance and status information of the decoy transmitter to the host aircraft and providing the decoy with control and optimization information from the platform. The tow cable provides a mechanical connection to the host aircraft as well as a prime power connection and in some cases, a fiber optic (FO) interface. In order to optimize the protection provided by the towed/surrogate decoy transmitter, the host aircraft will use the wireless communication link to transmit operational status and control adjustment data back to the towed/surrogate decoy transmitter. The towed/surrogate decoy transmitter utilizes a wireless communicator link that can transmit data to any cooperative host aircraft and any other cooperative towed/surrogate decoy transmitters.

Abstract: A projectile guidance system without gyros in which the projectile has an orthogonal body coordinate system. The projectile has a triax of accelerometers providing x, y and z acceleration data measured along the x, y and z axes respectively. A GPS antenna and receiver means provides onboard GPS position and velocity data in earth referenced navigational coordinates. A computer and program means stores and accesses time indexed GPS position and GPS velocity data and transforms x, y and z axis acceleration data from body to navigation coordinates. The program means is responsive to corresponding time indexed acceleration data and to GPS velocity and position data for calculating and outputting an estimated projectile roll, pitch and yaw angle via optimal smoothing techniques with respect to local level for each time index iteration of present position to a flight control system, which actuates a divert propulsion system for guiding the projectile to a predetermined location.

Abstract: A tracking system controls an aimed device (32) to keep it aimed at a target (34). A control system (10) determines when the tracker has lost its lock on the target (34) by comparing the target's instantaneous acceleration with its median acceleration. When the difference exceeds a predetermined threshold, the system searches backwards through a chronological buffer until it finds position data which antedate the receipt of inaccurate position data from the tracker. A second-order filter such as a Kalman filter is used to provide estimated target states. The difference between a time updated output from the second-order filter (16) and the present measured state from the tracking device is low pass filtered to provide a measurement of the instantaneous acceleration of the target. The buffer (20) stores position, velocity, and median acceleration values covering a span of time at least about twice as long as the time required to determine that a breaklock has occurred.

Abstract: A method for operating a short range, air-to-air missile carried by an aircraft flown by a pilot. The missile includes a seeker operative to track a target. The method comprises providing a first indication to the pilot when the seeker is tracking a target, providing a second indication to the pilot when a rate of angular motion of the seeker falls below a given value for a predefined period.

Abstract: A multi-staged missile includes a booster and a submunition delivery vehicle that has one or more submunitions. The booster rapidly accelerates the submunition vehicle, and then separates from the submunition vehicle. The submunition delivery vehicle is then maneuvered to approach a target. Individual submunitions finally separate, and are individually guided to the target. By providing multiple, independently-targeted submunitions, the missile greatly increases the chances of hitting the target.

Abstract: A device for detecting attacking guided missiles with optical seeker head and for generating a laser beam directed to such guided missile has an all-around seeker with a detector responding to thermal radiation from the guided missile, and a laser which points to the guided missile detected by the all-around seeker. A roll and pitch gimbal system is provided. A roll gimbal is rotatable relative to the structure about a roll axis. A pitch gimbal is rotatable relative to the roll gimbal about a pitch axis orthogonal to the roll axis. The detector is structure-fixed. An imaging optical system is mounted on the roll and pitch gimbal system. The optical system with its optical axis can point to an object scenario. With each position of the gimbal system, an image of this object scenario is generated on the detector. The laser is also structure-fixed.

Abstract: A projectile guidance system without gyros in which the projectile has an orthogonal body cordinate system. The projectile has a triax of accelerometers providing x, y and z acceleration data measured along the x, y and z axes respectively. A GPS antenna and receiver means provides onboard GPS position and velocity data in earth referenced navigational coordinates. A computer and program means stores and accesses time indexed GPS position and GPS velocity data and transforms x, y and z axis acceleration data from body to navigation coordinates. The program means is responsive to corresponding time indexed acceleration data and to GPS velocity and position data for calculating and outputing an estimated-projectile roll, pitch and yaw angle via optimal smoothing techniques with respect to local level for each time index iteration of present position to a flight control system for guiding the projectile to a predetermined location.

Abstract: A system and method that guides a device to an object using periodically adaptive guidance. The guidance and control system creates a reconstructed line-of-sight (LOS) vector to avoid system destabilization associated with small angle approximations during high bore sight engagements. The guidance system adaptively estimates the periodic maneuver of evasive objects with a set of harmonically balanced Kalman filter banks. The Harmonically Balanced Kalman filter banks generate a set of probabilities that weight the effect of each individual Kalman filters on a resultant guidance command signal. The guidance command signal generated by the system acts perpendicular to the object LOS. The guidance and control system uses vectored proportional navigation guidance laws, optimal proportion navigation laws and periodically adaptive augmented guidance laws to generate a guidance command signal to supply to an autopilot.

Abstract: The invention provides a system for passively controlling pressure oscillations of hydrodynamic origin in a solid propellant thruster comprising a body containing a charge of solid propellant, the system comprising at least one insert disposed in the thruster body transversely relative to the flow direction of the combustion gases of the solid propellant. The insert has an opening of non-axisymmetric shape so as to generate a three-dimensional effect on the flow and prevent axisymmetric turbulent modes from forming in the thruster. Thus, the control system of the invention serves to break the symmetry of the flow and thus prevents axisymmetric turbulence forming which is the source of instability that the present invention seeks to control. The present system is applicable to existing thrusters.

Abstract: An imaging fuse comprising a housing fixable within a receptacle at a fore end of a projectile, a coaxial support frame rotatably supported within the housing and fitted with an imaging assembly. The support frame is axially displaceable with respect to the housing. An axial shock absorbing system is provided intermediate the housing and the support frame, and a spin suppressing mechanism is associated with the support frame, for suppressing rotation of the support frame with respect to the housing.

Abstract: A target designation system for indicating a target to be destroyed by remotely guided ordnance comprising a receiver arranged to produce a receiver output signal in response to an incident electromagnetic signal from an attack aircraft. An auto-switch is connected to the receiver and arranged to produce a power signal in response to the receiver output signal. A transmitter is connected to the auto-switch to be activated by the power signal. When activated, the transmitter transmits a homing signal that indicates its location or the location of the target.

Abstract: A system for operating and releasing a store of a first predetermined type includes an aircraft adapted to control the operation of stores of a second predetermined type and a bypass apparatus. The store is releasably secured to the aircraft, and the aircraft is capable of releasing the store. The aircraft is capable of being configured such that a store of the first predetermined type is capable of operating independent of operating instructions. The bypass apparatus is carried by the aircraft and adapted to facilitate operation of the store. The bypass apparatus can store operating instructions and thereafter transmit the operating instructions into the store. As such, after the aircraft releases the store the store is capable of operating according to the operating instructions. Also, the system can include an umbilical cable disposed between the aircraft and the store. The bypass apparatus can, therefore, be disposed within the umbilical cable.

Abstract: A method and apparatus for thrust vectoring a flight vehicle during homing are disclosed. The flight vehicle includes a body; a plurality of attitude control mechanisms on the body; a multi-pulse motor housed at least partially in the body; and a control unit housed in the body. The control unit generates signals controlling an actuation of the attitude control mechanisms and the multi-pulse motor to initiate a follow-on burn of the multi-pulse motor to effect a maneuver directed by the actuation of the attitude control mechanisms. The method includes conserving a second burn of a dual pulse motor until target acquisition; acquiring a target; actuating a attitude control mechanism for the flight vehicle to alter the flight vehicle's heading; and initiating the second burn.

Abstract: A target designation system for indicating a target to be destroyed by remotely guided ordnance comprising a receiver arranged to produce a receiver output signal in response to an incident electromagnetic signal from an attack aircraft. An auto-switch is connected to the receiver and arranged to produce a power signal in response to the receiver output signal. A transmitter is connected to the auto-switch to be activated by the power signal. When activated, the transmitter transmits a homing signal that indicates its location or the location of the target.

Abstract: The present invention is directed towards a ballistic missile detection and defense system. The system of the present invention comprises a ship based interceptor or antiballistic missile, a missile launch detection system, a missile tracking system, and a ship based signal processing system capable of receiving said tracking signal calculating an intercept trajectory for an antiballistic missile to intercept a ballistic missile, and further capable of outputting an intercept trajectory program to an antiballistic missile.

Abstract: The present invention concerns a method and an arrangement for determining the angle of roll of a launchable body (4) which rotates in its path. The launchable body (4) can consist of a rotating projectile, shell, guided missile or the like, launchable from a launching device (1). According to the invention the transmitter antenna (3) and receiver antenna (5) are each designed with their sweeping beams (6, 9) directed essentially towards each other. By detecting the time the two beams (6, 9) coincide and the signal strength received in the receiver antenna, the angle of roll of the launchable body can be determined.