Abstract: An interceptor-based sensor clusters tracks of objects to generate track clusters based on an uncertainty associated with each track, and generates feature vectors for a cluster under test using the relative placement and the population of other track clusters. The feature vectors may include one or more of a cluster count feature vector (N), a cluster population density feature vector (P), a cluster proximity feature vector (r), a cluster-weighted centroid feature vector (L) and a cluster scattering feature vector (?). The interceptor-based sensor generates belief functions (?) from corresponding feature vectors of clusters of tracks generated from a ground-based sensor and the interceptor-based sensor. The interceptor-based sensor may also associate the tracks with a cluster having a track of interest identified by a ground-based sensor based on the belief functions and may select one of the tracks for intercept of a corresponding object within the threat object cloud.

Abstract: A target identification and tracking system includes a carrier vehicle and one or more tracking vehicles. The carrier vehicle may determine an aimpoint of a target from a high resolution image of the target and may generate an offset from a tracking point to the aimpoint. The offset may be conveyed to an assigned tracking vehicle for tracking the tracking point of the target while navigating toward the aimpoint of the target. The tracking point may be the target's centroid. The carrier vehicle may employ a high-resolution LIDAR imaging system to identify the aimpoint from a target's features; while the tracking vehicle may employ a lower resolution optical imaging system for tracking the target's tracking point. The carrier vehicle may correct the offset for parallax and the offset may be revised as the tracking vehicle approaches the target.

Abstract: A munition is presented which includes an integrity verification system that measures the integrity of the munition. When an integrity threshold is not met, engagement of the munition with a predetermined target is aborted. Also presented is a methodology for gating the engagement of the munition with the target. The methodology includes performing an integrity check of the munition after it is deployed. The method further includes aborting the engagement of the target when the integrity check of the munition fails.

Abstract: A system for measuring a position and orientation of an object in flight relative to a reference coordinate system is provided.

Abstract: The centroid of the discrete components forming the overall radar return from a target onto which a homing weapon is being guided may not coincide with a desired aimpoint on the target. Herein proposed is the discrimination and comparison of returns from different portions of the weapon sensor's field-of-view, i.e. different portions of the target and guidance of the weapon in dependence upon the relative values of the differences between those returns. As a result, the weapon can hit say the centre of a tank turret roof rather than the probably heavily armoured area forward of the turret roof.

Abstract: Systems and methods for guiding an object may comprise improved guidance laws that improve the effectiveness of the PRONAV guidance law. The improved guidance laws may utilize the same parameters as the PRONAV law and may be algorithmically simpler than conventional guidance laws because they may not be based on information about an intercept point or time-to-go. The improved guidance laws may be developed based on the Lyapunov method. The improved guidance laws may augment the PRONAV law and may provide additional components based on the negative definiteness of the derivative of the Lyapunov function. The additional components may be determined based on the partial stability of the guidance system dynamics under consideration with respect to the line of sight derivative. A comparative analysis of the improved guidance laws with the PRONAV laws, for example, may show that the improved guidance laws guarantee shorter homing time requirements and larger capture areas.

Abstract: A wide field-of-view optical system that may be used in determining a direction to a source of light, or for determine steering corrections to direct a vehicle toward a target, is disclosed. The optical system, which may be used as a seeker in a missile or other weapon, comprises a spherical ball lens truncated to provide one or more facets on which detectors may be mounted to measure relative intensities as a blur spot image of a source of light, which may be a reflection from a laser designated target, moves across the detectors, which may be individual elements in a quadrant detector. Narrow band filters may be used to suppress undesired wavelengths and enhance performance. The innovative design enables implementation of a wide field-of-view seeker with no moving parts. The spherical ball lens may be used directly as an aerodynamic surface without a need for a separate optical dome.

Abstract: A dual-mode target seeking apparatus having a seeker dome defining an aperture and transmissive to microwave frequency energy of a first frequency and to light wave energy at a second frequency and at a third frequency. An optics system within the seeker dome is transmissive to the microwave frequency energy reflective to the light wave energy received via the aperture. A first detector receives the microwave frequency energy via the aperture, and a second detector images a target by the light wave energy of the second and third frequencies via the optics system.

Abstract: A virtual sensor mast for a ground vehicle and a method for operating a ground vehicle using a virtual sensor mast are disclosed. The virtual sensor mast includes an unmanned airborne vehicle capable of lifting itself from the ground vehicle upon deployment therefrom; a sensor suite mounted to the unmanned airborne vehicle; and a tether between the unmanned airborne vehicle and the ground vehicle over which the sensor suite is capable of communicating sensed data upon deployment. The method includes elevating a tethered unmanned airborne vehicle from the ground vehicle to a predetermined height; sensing environmental conditions surrounding the ground vehicle; and terminating the deployment.

Abstract: Systems and methods for contiguously and accurately updating target object information during an entire target engagement period are provided. The target tracking system includes a database for storing starfield information, an optical beam source configured to illuminate one or more optical beam pulses, first and second camera systems, and a processor. The processor instructs the first camera system to track the object based on recordation of the tracked object, instructs the second camera system to stabilize the tracking image based on the instructions sent to the first camera system, and determines inertial reference information of the tracked object based on the stabilized image and starfield information associated with the stabilized image.

Abstract: A method for ballistic target defense including identifying a launched ballistic target having a target launch point, a target launch direction, a target speed, and a target trajectory; launching a target interceptor in a launch direction that is generally the same as the target launch direction and with a speed that is less than the target speed; providing the interceptor with an approximate target intercept trajectory; and accelerating the interceptor at an approximate point of intercept to substantially match the target trajectory. During a relatively long target engagement time, the interceptor has approximately a zero net relative velocity with respect to the target.

Abstract: An airborne vehicle (1, 2, 10) which is equipped with an extinguishant container (12) for mist extinguishing is specified for efficient firefighting. A detonator (18) which is located on the extinguishant container (12) can be detonated via a fuze (19). The detonator (18) is attached to the airborne vehicle (1, 2, 10) such that, on firing the extinguishant which is contained in the extinguishant container (12) produces an extinguishant mist.

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: A process to control the trajectory of a spinning projectile. The projectile's accelerations are measured by means of an inertial unit in three axes within a reference linked to the projectile so as to prepare the piloting commands for the projectile's trajectory. The velocity vector V components (VX, VY, VZ) of the projectile are measured using a global positioning system (GPS) along three axes and within a land reference (GX, GY, GZ). Based on these measurements, the components (?X,?Y,?Z) of the acceleration vector ? are evaluated in the same land reference (GX, GY, GZ). At each of these measurements and periodical evaluations by the GPS, the Euler angles of the projectile are recalculated by combining the resultants of the velocity (V) and acceleration (?) measurements given by the GPS and those of the acceleration given by the inertial unit.

Abstract: An interceptor device for protecting a platform against an incoming threat is provided. The interceptor device comprises a housing and a countermeasure device. At least one detonating charge is capable of deploying the countermeasure device. A controller device housed by the housing is capable of directing the detonating charge(s) to deploy the countermeasure device at least partially radially outward of the housing, corresponding to the threat trajectory. A sensor device is in communication with the controller device, and comprises a range-finding apparatus including one of a LADAR, a RADAR, and a LIDAR device, capable of sensing the threat and/or a range thereof, at least partially radially outward of the housing, and notifying the controller device if the threat is sensed, to cause the controller device to direct the detonating charge(s) to deploy the countermeasure device to impact the threat in the intercept zone. Associated systems, and methods are also provided.

Abstract: A weapons system is disclosed that provides hot-start navigational information to the Global-Positioning-System receivers on missiles prior to flight. The system comprises a Global-Positioning-System receiver that uses a classified red cryptographic key to decode the P(Y) signal from one or more of the Global-Positioning-System constellation of satellites. Once the P(Y) signal is decoded, one or more characteristics of the P(Y) signal is derived. These characteristics of the signal—and some other information including a black cryptographic key that comprises the red cryptographic key—are then provided to the Global-Positioning-System receivers on missiles prior to flight. By giving the missiles this information, the missiles are able to acquire the P(Y) signals, which enables them to determine their position more quickly than they otherwise could.

Abstract: Disclosed is an autonomous radar guidance of an otherwise radar-directed projectile (RDP). The preferred embodiment uses an inexpensive radar receiver with an inexpensive slow wave antenna, placed internally in a gun projectile, and on the surface of the projectile, respectively. The receiver detects the angle and range of the target relative to the body coordinates of the projectile. The radar receiver operates as a bistatic radar apparatus with the primary illumination emanating from the fire control radar directing the fire of the gun. When integrated with an on-board trajectory correcting system, such as divert thrusters of miniature proportions, the projectile autonomously refines its otherwise ballistic trajectory to the target. The trajectory refinements produce improved kills per round, with the potential for reducing the ammunition expended and time-loading on the fire control system and its guns.

Abstract: An attitude sensing apparatus for determining the attitude of a mobile unit is provided that can reliably estimate an alignment angle between a GPS antenna coordinate system and an IMU coordinate system with good accuracy regardless of the magnitude of the alignment angle. Based on observation of the difference between a GPS angular velocity and an IMU angular velocity, an alignment angle estimating section estimates an alignment angle and sensor errors. An alignment angle adder and a sensor error adder cumulatively add and update the estimated alignment angle and sensor errors, respectively. The estimated alignment angle is fed back to an inertia data converter while the estimated sensor errors are fed back to an inertia data correcting section. The apparatus repeatedly performs estimation until the estimated alignment angle gradually approaches a true alignment angle by successively feeding back estimated values to a flow of alignment angle estimation process.

Abstract: An interceptor device adapted to protect a platform associated therewith against an incoming threat having a trajectory by intercepting the threat in an intercept zone is provided. Such an interceptor device comprises a housing defining an axis and a countermeasure device operably engaged with the housing. At least one detonating charge is housed by the housing and is operably engaged with the countermeasure device. A controller device is in communication with the at least one detonating charge, wherein the controller device is housed by the housing and is configured to direct the at least one detonating charge to deploy the countermeasure device at least partially radially outward with respect to the axis of the housing and in correspondence with the trajectory of the threat to thereby cause the countermeasure to impact the threat in the intercept zone. Associated apparatuses, systems, and methods are also provided.

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: A method for testing the performance of a Missile Time-Space-Position Information Unit. The method is utilized for Functional, Acceptance and Qualification test of the Missile Time-Space-Position Information Unit. The method has the capability of testing the Missile Time-Space-Position Information Unit to verify and document functionality of the Missile Time-Space-Position Information Unit prior to use of the Missile Time-Space-Position Information Unit in an operational environment.

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 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: 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 method for the automatic collection of surveillance information by an unmanned air vehicle comprises the steps of receiving an automatic collection requirements message, determining a route for gathering requested information about a target in accordance with a collection policy, and controlling operation of an air vehicle to follow the route and gather the requested information. An automatic collection management system for an unmanned air vehicle that performs the method is also provided.

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: Systems and methods for contiguously and accurately updating target object information during an entire target engagement period are provided. The target tracking system includes a database for storing starfield information, an optical beam source configured to illuminate one or more optical beam pulses, first and second camera systems, and a processor. The processor instructs the first camera system to track the object based on recordation of the tracked object, instructs the second camera system to stabilize the tracking image based on the instructions sent to the first camera system, and determines inertial reference information of the tracked object based on the stabilized image and starfield information associated with the stabilized image.

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 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 dual mode radar seeker comprising a wide-band passive anti-radar antenna system (3) at the rear of a radome (1), operating at relatively low radar frequencies in an amplitude comparison tracking mode, and a high-frequency (W-band) active amplitude-comparison antenna system (5) in the nose of the radome (1) and having a common boresight with the anti-radar system. The active system employs coarse phase shift steering (31, 41) of the antenna ‘beam’ for the transmit and, optionally, also, the receive ‘beam’. The high frequency and the use of phase shift steering both help to keep down the size of the active radar thus enabling it (5, 7, 9) to be positioned far forward in the nose of the radome (1) so as not to obscure the field of the anti-radar system (3).

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: A proximity sensor for use with a guidance system of a smart bomb including a ranging radar proximity sensor configured for mounting on a smart bomb and a radome connected to the ranging radar proximity sensor. A laser radiation sensor system is attached to the proximity sensor, which is configured and arranged to detect laser radiation reflected from a target which passes through the radome and output the azimuth and elevation angles to the target to the guidance system.

Abstract: A vehicle guidance system. The system includes a first mechanism for tracking a vehicle based on time-of-arrival information associated with energy emanating from the vehicle and providing vehicle position information in response thereto. A second mechanism steers the vehicle based on the vehicle position information. In a specific embodiment, the system of further includes a third mechanism for locating the target based on time-of-arrival information associated with energy radiating from the target and providing target location information in response thereto. The second the second mechanism steers the vehicle based on the target location information and the vehicle position information.

Abstract: A munition is presented which includes an integrity verification system that measures the integrity of the munition. When an integrity threshold is not met, engagement of the munition with a predetermined target is aborted. Also presented is a methodology for gating the engagement of the munition with the target. The methodology includes performing an integrity check of the munition after it is deployed. The method further includes aborting the engagement of the target when the integrity check of the munition fails.

Abstract: A method of guiding a munition to a target transmitting one or more signals is described. The method includes configuring the munition with a radio frequency receiver, an antenna for the receiver mounted such that a main beam of the antenna pattern for the antenna is offset from a line of flight axis of the munition by an angle and configuring the munition to rotate along an axis substantially similar to the line of flight axis of the munition. The method also includes configuring the munition to process signals received at the antenna, wherein heading changes of the munition, the angle of the main beam of the antenna from the line of flight axis, and the rotation of the munition result in the received signals having amplitude variations. Directional corrections are generated for the munition to direct the munition towards the target based on amplitude variations in the received signals.

Abstract: A method of projectile control provides a control order for an organ allowing the yaw piloting of a spinning projectile. The control order causes a modification of a yaw piloting parameter of the projectile, the parameter that needs to be controlled being fin deflection. The angular rate of roll of the projectile is measured. At least one corrective coupling term is introduced into the evaluation of the control order modifying the yaw piloting parameter. The corrective coupling term is proportional to the angular rate of roll and also to the drift over time of the pitch piloting parameter to provide projectile piloting orders control fin motors.

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 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 for automatically correcting flight path of an aircraft onto a predetermined trajectory is provided. A sensor is configured to sense speed and direction of air relative to the aircraft at a predetermined distance in front of the aircraft. A navigation system is configured to determine displacement of a flight path of the aircraft from a predetermined trajectory. A processor is coupled to receive the sensed speed and direction of air from the sensor and the displacement of the flight path from the navigation system. The processor includes a first component that is configured to determine whether the speed of the air at the predetermined distance is indicative of turbulence, and a second component that is configured to automatically generate control signals to correct the flight path of the aircraft from the displacement onto the predetermined trajectory by a time when the aircraft enters the turbulence.

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, apparatus, article of manufacture, and a memory structure for compensating for optical sensor data corrupted by angular acceleration is disclosed. The method comprises the steps of determining an angular acceleration of the optical sensor and modifying the optical sensor data according to the determined angular acceleration of the optical sensor. The apparatus comprises a sensor for determining an angular acceleration of the optical sensor and a navigation system for modifying the optical sensor data according to the determined angular acceleration of the optical sensor.

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 method and apparatus for finding a relative direction of received radiation is described. The received radiation is incident upon a window system at an angle and is transmitted therethrough. The magnitude of the transmitted radiation decreases as a continuous function of increasing angle of incidence, known as Fresnel transmittance. Opposing radiation detectors then detect this transmitted radiation, thereby creating a pair of detection signals, By dividing the difference of the detection signals by the sum of the detection signals, a processor generates a beta angle error curve and finds the relative direction of the radiation. Based upon this beta angle error curve, the processor generates an appropriate error correction signal for guiding an object based upon the relative direction of the received radiation. The method and apparatus are readily applicable to guiding munitions using a laser monopulse to designate a target.

Abstract: A method and apparatus for conducting proximity operations is disclosed. The method called inverser proximity operations includes maneuvering an active vehicle into general proximity to a target vehicle, transmitting from the target vehicle to the active vehicle data representing relative position and velocity between the target vehicle and the active vehicle, and maneuvering the active vehicle in accordance with the data to effect a desired proximity operation. Another method called distributed proximity operations includes maneuvering a carrier vehicle into general proximity to a target vehicle, releasing one or more active vehicles from the carrier vehicle, transmitting from the carrier vehicle to the active vehicle(s) data representing relative position and velocity between the target vehicle and the active vehicle, and maneuvering the active vehicle(s) in accordance with the data to effect a desired proximity operation.

Abstract: A missile system and a method of missile guidance in which a bus missile is launched from a launch station remote from a target with the bus missile carrying a plurality of sub-missiles. The sub-missiles are then launched from the bus missile during flight of the bus missile. The sub-missiles are arranged to deploy ahead of the bus missile and are guided to the target under the control of a guidance beam generated in and transmitted from the bus missile.

Abstract: A wireless means of guidance for a device in accordance with the present invention includes receiving signals from at least one wireless base station indicating at least a respective position thereof, determining the current position of the device using at least the information contained in the received signals, calculating a vector between the determined current position and a predetermined desired destination for the device, and making trajectory corrections to the device's current trajectory so as to guide the device to the desired destination. In addition to the information contained in the received signals, the guidance system may also use stored information regarding parameters, such as the location, communication protocols and operating frequencies of the wireless base stations, as well as previous position information, for determining a current position for the device.

Abstract: A munition is presented which includes an integrity verification system that measures the integrity of the munition. When an integrity threshold is not met, engagement of the munition with a predetermined target is aborted. Also presented is a methodology for gating the engagement of the munition with the target. The methodology includes performing an integrity check of the munition after it is deployed. The method further includes aborting the engagement of the target when the integrity check of the munition fails.