Abstract: A missile has a flight termination system that includes deployable lift surfaces that deploy forward of a center of gravity of the missile. When deployed, the lift surfaces cause the missile to rotate about its longitudinal axis. This rotation eventually increases in rate until the missile nears a natural roll frequency of the missile. As the missile nears or reaches its natural roll frequency, the missile's nose pitches up, angle of attack diverges and the missile tumbles, resulting in rapid termination of flight by loss of aerodynamic lift, vertical plunging and crashing. The lift surfaces may be curved surfaces that conform to the shape of a fuselage of the missile, prior to the deployment of the lift surfaces. The lift surfaces may be canted slightly relative to a missile longitudinal axis when the lift surfaces are deployed, so as to provide a sufficient rolling moment to overcome aerodynamic damping or resistance (roll drag) of the missile.

Abstract: A guidance system according to various aspects of the present invention operates in conjunction with a suite of different ordnance delivery devices. In one embodiment, the guidance system comprises an interface configured to attach to the ordnance delivery devices in the suite, such as via the fuze well. The guidance system may further include a control system adapted to attempt to establish communications with a subsystem of the ordnance delivery device and operate the guidance system as a standalone guidance system if the attempt fails. The guidance system may further include a control surface interchangeably attachable, for example via an interchangeable control surface module.

Abstract: A submunition is formulated for destroying a target in a target area. Accommodated in a casing are a signal processing unit connected to a radar antenna and/or an infrared sensor and/or another target-detecting sensor. The submunition further has target recognition software and a charge provided with a covering. To increase the versatility of use and to simultaneously improve detection and decision certainty and reliability, the target recognition software has a software interface for the transfer of at least one parameter specific to the target area.

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 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 multi-stage hyper-velocity kinetic energy missile (HVKEM) uses a ‘missile in a missile’ architecture in which the HVKEM includes a 1st stage flight missile and a 2nd stage kill missile that includes a KE-rod penetrator. The flight missile cruises at a relatively low velocity (less than Mach 1.5, typically less than Mach 1) to conserve propellant (weight) and to allow for effective guidance and maneuvering until the missile is in close proximity to the target. When the missile is within the lethal range of the KE-rod penetrator, the kill missile separates and boosts to a much higher velocity (greater than Mach 3, typically greater than Mach 5) and flies unguided to impact the target in less than a second. Waiting to boost the KE-rod until “the last second” reduces the total propellant (weight) needed to deliver the KE-rod on target and simplifies the guidance.

Abstract: A Hybrid Projectile is provided for delivering an explosive payload to a target wherein the Hybrid Projectile may be steered in flight using relatively inexpensive means. The Hybrid Projectile is exteriorly configured in the same physical exterior configuration of conventional ammunition of various standard types so it can be launched in conventional manner from the same weapon systems. However, internal features allow the Hybrid Projectile to be transformed in flight from a command signal to deploy wings and fins, and in some projectiles to telescope open to deploy such wings and fins. An inexpensive televisual means is activated in the fore region of the round which through RF uplink command can be used to select a path, while motors on the wings can then be used to more precisely glide the projectile to a target, or otherwise to abort the target run.

Abstract: Current targeting approaches involve guiding to a spatially derived guidepoint of a group of objects likely to be the preferred object. This method may not allow the intercepting missile to contain the preferred, or other probable object(s), within its divert capability. The guidepoint is shifted closer to the preferred object using specific energy and angular momentum, constants of orbital motion, which describe properties of an object's trajectory. Guiding to the specific energy derived guidepoint does not offer significant benefit over guiding to the spatially derived guidance point. However, computing the spatial rate of change of specific energy within the plane formed by the guidance objects establishes a vector pointing close to the preferred object. This is the direction to shift the guidepoint in order to contain the preferred object within the interceptor's divert capability.

Abstract: A projectile including: a casing; first and second windows provided on the casing for at least one of transmitting a first optical signal into an interior of the casing and transmitting a second optical signal from the interior of the casing; a receiving element disposed on the interior of the casing and in optical communication with one or more of the first and second windows for at least one of converting the first optical signal into electrical energy and storing data provided in the first optical signal; and a transmitting element disposed on the interior of the casing and in optical communication with one or more of the first and second windows for transmitting data provided in the second optical signal to outside the casing.

Abstract: An air-based vertical launch system is described by means of which ballistic missile defense can be achieved effectively from a large aircraft. A method for ensuring safe missile egress is proposed. A method for ensuring that the missile strikes the ballistic missile payload section is also proposed. Together, the air basing method employing vertical (or near-vertical) launch and semi-active laser guidance yield an affordable and operationally effective missile defense against both tactical and long-range ballistic missiles. The affordability of missile defense is enhanced by the ability of an aircraft equipped with a vertical launcher to simultaneously carry out several defensive and offensive missions and to provide other capabilities such as satellite launch at other times.

Abstract: A multi-stage missile with plural stages adapted to be physically coupled to and decoupled from adjacent stages and a processor disposed on a single stage for controlling each stage thereof. In the illustrative embodiment, the processor includes a field programmable gate array. In the illustrative embodiment, the processor is disposed on stage 4 of a four-stage missile and performs guidance and navigation functions for each stage and control functions for stages 2, 3 and 4. In a specific embodiment, a serial bus interface is included for coupling the processor to electronic circuitry on each of the stages of the missile. In the best mode, the interface is an IEEE 1394b interface with a physical layer interface and a link layer interface.

Abstract: A method for guiding a multistage interceptor missile toward a target missile that may transition from a boost mode to a ballistic mode during the engagement. The method comprises the steps of tracking the position of the target missile with a sensor, generating a predicted intercept point and time, and loading the predicted intercept point and time into the interceptor missile guidance system. The interceptor missile is launched and transition is made to the second stage of propulsion of the interceptor missile. Second-stage midcourse guidance acceleration commands are generated in response to an elevated predicted intercept point generated using the Runge-Kutta integration method working on predicted target missile position, velocity, and acceleration. During third stage propulsion said interceptor missile is guided toward an updated predicted intercept point of the target missile. During fourth stage, the kinetic warhead effects a hit-to-kill intercept of the target missile.

Abstract: An intercept system for destroying a falling bomb includes a packable structure including a compressed expandable net of break resistant cords, a radio altimeter and a deployment mechanism for expanding and deploying the net below a falling bomb. The system also includes an explosive charge and a detonator for detonating the explosive charge when the detonator comes into contact with a bomb. A shoulder fired missile launcher propels the packable structure into the air below a falling bomb. The structure also includes a timer, responsive to the radio altimeter to detonate the explosive charge if a bomb is not encountered within a pre-selected amount of time.

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: An apparatus and method for protecting against incoming projectiles comprising transmitting two radar waveforms, the first waveform comprising a pulsed continuous wave waveform, and the second waveform comprising a pulsed linear chirp waveform over a bandwidth, and based on returned radar data, causing deployment of a defense mechanism to intercept a detected incoming projectile.

Abstract: A method for guidance of a moving object towards a target. The method including: providing reference signals from RF reference sources to illuminate RF sensors on the moving object; positioning the RF reference sources to form a reference coordinate system; determining position information designating a position of the target in the reference coordinate system by a forward observer; fixing at least one of the RF reference sources at the forward observer in the reference coordinate system; determining a position and orientation of the moving object in the reference coordinate system on board the moving object based on signals received at the RF sensors from the RF reference sources and based on the positions of the RF reference sources; and guiding the moving object to the target at least based on the determined position and orientation of the moving object and the determined position information of the designated target.

Abstract: A method and apparatus for attacking a plurality of dispersed targets are herein presented. In particular, the method and apparatus herein presented allow the user to upload target data onto a pod mounted on a host aircraft. Upon reaching the pre loaded target location, the pod releases a plurality of individually targeted Micro Air Vehicles (MAVs), thereby allowing the user to attack a plurality of dispersed targets from a single aircraft standing off at a significant distance from the target area.

Abstract: A method of determining a deviation of a path of a projectile from a predetermined path. The method uses an image of a target area in which the desired path or direction is pointed out. Subsequently, the real direction or path is determined and the deviation determined.

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 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: By sharing tasks between the CV and the KVs, the MKV interceptor provides a cost-effective missile defense system capable of intercepting and killing multiple targets. The placement of the acquisition and discrimination sensor and control sensor on the CV to provide target acquisition and discrimination and mid-course guidance for all the KVs avoids the weight and complexity issues associated with trying to “miniaturize” unitary interceptors. The placement of either a short-band imaging sensor and headlamp or a MWIR sensor on each KV overcomes the latency, resolution and bandwidth problems associated with command guidance systems and allows each KV to precisely select a desirable aimpoint and maintain track on that aimpoint to impact. An implicit divert and attitude control system (DACS) using tow or more divert thrusters performs KV divert and attitude maneuvers to respond to the command guidance pre-handover and to maintain track on the aimpoint to terminal intercept post-handover.

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 modular electromechanical actuation system assembly is provided that includes an electronic control unit housing having a plurality of motor receptacles and a plurality of battery receptacles formed in an outer surface thereof. Each of the motor receptacles has an associated motor electrical interface, and each of the battery receptacles has an associated battery electrical interface. An electronic control unit is disposed within the electronic control unit housing and is electrically coupled to each of the motor electrical interfaces and each of the battery electrical interfaces. A plurality of motors are supported, one each, within one of the motor receptacles, and a plurality of batteries are supported, one each, within one of the battery receptacles.

Abstract: The present invention is a device which includes an antenna and circuitry. The antenna may receive a circularly-polarized signal as first and second linearly-polarized signals. The circuitry is connected to the antenna and is configured for combining the first and second linearly-polarized signals to produce at least two reception patterns. The reception patterns are created by summing the first and second linearly-polarized signals via phase shifting. The reception patterns are optimized for at least two substantially different directional orientations. Further, the antenna may simultaneously allow/provide spec-compliant Global Positioning System operation and spec compliant Height of Burst operation.

Abstract: A method for guiding a moving object to a target. The method comprising: transmitting a signal from one or more illuminating sources defined in a reference coordinate system; receiving the signal at three or more cavity waveguides disposed on the moving object; using one or more forward observers to determine the position of the target; fixing the one or more illuminating sources to the one or more forward observers; determining a position and/or orientation of the object in the reference coordinate system based on a strength of the signal received in the three or more cavity waveguides; and guiding the moving object to the target based on the determined position and/or orientation.

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

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

Abstract: Methods and systems for a wave guide according to various aspects of the present invention may be implemented in conjunction with a radiation collection device comprising a light pipe, a first plate and a second plate. The first plate and the second plate may be inserted into the interior of the light pipe to divide the light pipe into sections. In one embodiment, a first section plate and at least a second section plate are inserted into a light pipe. The inserted first section plate and the at least second section plate may be secured to the light pipe.

Abstract: In a method for removing moisture from an optical system at high altitude, the improvement comprises using the difference in flow resistance between the desiccant path and the optical cavity path to enable airflow through the desiccant unit and not through the optical path.

Abstract: One example embodiment relates to a method of navigating an object. The method includes detecting when the object accelerates through the speed of sound and maneuvering the object based on when the object accelerates through the speed of sound. Another example embodiment relates to a system for navigating an object. The system includes a detector within the object. The detector determines when the object accelerates through mach one. The system further includes a guidance system within the object. The guidance system adjusts the flight of the object based on data received from the detector.

Abstract: A method for engaging a target uses sensors to generate target track(s). The tracks are projected forward in time and associated with a track quality measure. The maximum seeker look angle and beamwidth, acceleration, and net radar sensitivity characteristics are listed for each type of interceptor. A plurality of target intercept times are generated for each interceptor type. The probability that the interceptor can acquire the target is determined from the projected target tracks, the quality measure, and the characteristics. The probability of hitting the target is determined from the probability of acquisition and acceleration of the interceptor type. The probabilities of acquisition and of hitting the target are aggregated, and the type of interceptor to use is the type having (a) an extreme value of the aggregation or (b) the earliest intercept time from among the interceptors having an aggregation value above a threshold value.

Abstract: Systems and methods are provided for projecting a virtual image of an object. A projector mounted on the object for projecting a light beam. A photographic plate is provided that includes an interference pattern imprinted onto at least one surface, wherein the interference pattern manipulates the light to form a hologram beam such that a detector detecting the hologram beam detects a virtual image of the object that has a light signature at a greater intensity than a light signature of the object.

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 nose cone formed from a shape memory alloy (SMA) having a recoverable strain of at least 2% collapses about the dome for storage, deploys at launch to protect the sensor dome and reduce drag during atmospheric flight and is shed to allow sensing for terminal maneuvers. The SMA is shape-set at elevated temperatures in its Austenite phase with a memorized shape having a radius of curvature greater than that of the sensor dome to reduce aerodynamic drag. The temperature is reduced and the SMA collapsed to conform to the curvature of the sensor dome within the recoverable strain for storage. A first mechanism is configured to return the collapsed SMA to its memorized shape at launch or prior to going supersonic. In one embodiment, the SMA is stored below its Martensite finish temperature in a temperature-induced Martensite phase in which case the mechanism heats the SMA above the Austenite finish temperature to return the material to its memorized shape.

Abstract: A flechette has a forward section or body (12) containing its center of gravity. A quill (10) is connected to the forward section and is integrally connected to a pair of fins (15A, 15B) each having a longitudinal angle and a radial angle. When the two fins are viewed from the aft of the flechette, the pair of fins demonstrate an S-shaped orientation. The size, shape and orientation of the fins provide aerodynamic stability to the flechette while allowing the flechette to be stacked with like-shaped flechettes in rows and columns or in a radial, circular arrangement. When stacked in rows and columns or in a circular arrangement, each flechette has its nose oriented in the same forward direction.

Abstract: Embodiments of a missile, an airframe and a structure comprising piezoelectric fibers and a method for active structural response control are generally described herein. In some embodiments, a housing structure includes a composite material containing a plurality of piezoelectric fibers adapted to generate an electrical signal in response to a deformation in the structure and to deform the structure to provide low frequency stiffness and strength performance while attenuating high frequency vibrations.

Abstract: Methods and apparatus for an air brake system for a projectile according to various aspects of the present invention comprises a pivot and a protrusion mounted on the pivot. The protrusion is adapted to selectively translate outward from the projectile around a translation axis that is parallel to the longitudinal axis of the projectile. The methods and apparatus may further operate in conjunction with an actuation system engaging the protrusion, wherein the actuation system is configured to selectively facilitate the translation of the protrusion.

Abstract: A system and method of providing aerial navigation. Techniques are described for receiving global positioning system data, receiving local positioning system data such as instrument landing system data, generating a virtual target flight path using the global positioning system data and the local positioning system data, and presenting a virtual target flight path indicator corresponding to the virtual target flight path. In one implementation, the system includes a user interface, a global positioning component, a local positioning component, and a processing system.

Abstract: According to the invention, the system comprises an infrared detector (7) for alternately generating images (5?) of sources of light (5) in the near infrared emitted by a missile flying towards a target and thermal images of the observed scene, said thermal images being visible on the display means (11).

Abstract: A diverter for changing the trajectory of a projectile includes a release mechanism that extends along a longitudinal axis between first and second ends. A mass is coupled to the first end, and the second end is coupled to the projectile. The release mechanism includes a groove and an explosive charge. The groove is disposed between the first and second ends and cinctures the longitudinal axis. The explosive charge is disposed along the longitudinal axis between the groove and the second end.

Abstract: A system and method of detecting, processing, and selectively responding to radio frequency transmissions detected by at least one projectile deployed above a geographic area.

Abstract: A system for estimating an antenna boresight direction. The novel system includes a first circuit for receiving a Doppler measurement and a line-of-sight direction measurement corresponding with the Doppler measurement, and a processor adapted to search for an estimated boresight direction that minimizes a Doppler error between the Doppler measurement and a calculated Doppler calculated from the estimated boresight direction and the line-of-sight direction measurement. The line-of-sight direction measurement is measured relative to the true antenna boresight, and the calculated Doppler is the Doppler calculated for a direction found by applying the line-of-sight direction measurement to the estimated boresight direction. In a preferred embodiment, the first circuit receives a Doppler measurement and a line-of-sight direction measurement from each of a plurality of pixels, and the processor searches for an estimated boresight direction that minimizes a sum of squares of Doppler errors for each of the pixels.

Abstract: A guidance system for actively guiding a projectile, such as a bullet after it has been fired from a gun. The guidance system includes a radar unit that includes a plurality of receiver arrays. An optical scope is also mounted to the gun for optically sighting a target. An inertial measurement unit provided on the gun locks onto the target after it has been sighted by the scope, and provides a reference location at the center of the receiver arrays from which the bullet can be directed. The receiver arrays receive radar monopulse beacon signals from the bullet. The signals from the bullet are used to identify the position of the bullet and the roll of the bullet. The signals sent to the bullet provide flight correction information that is processed on the bullet, and used to control actuators that move steering devices on the bullet.

Abstract: The invention relates to a process to control the initiation of an attack module, such as a projectile or sub-projectile, such attack module having at least one pre-determined direction of action. Before firing or on trajectory, the coordinates of at least one target are programmed into a fixed terrestrial reference, the orientation of the direction(s) of action in the fixed terrestrial reference is determined at least once on trajectory, and the initiation of the attack module is only authorized if the direction of action is oriented in the direction of the target. The invention also relates to the device implementing such a process.

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 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: This scanning array scans an area around the array for nearby objects, collision obstructions, and terrain topography. The scanning array can scan for sounds emitted by objects in the vicinity of the scanning array, passive energy receipt sources, or it can also send out an energy beam and scan for reflections from objects within the energy beam. The energy beam can be optical, laser, radar or other energy emitting sources. The scanning array of the invention can be used for helicopter detection and avoidance of collision risk and can be used for other scanning purposes. Scanning of an entire hemisphere or greater is accomplished by manipulating the scanner platform through the coordination of either linear actuators or gimbals so as to produce nutation without rotation. This motion allows transceivers to be directly coupled to transmitting and sensing modules without the losses associated with slip rings and other coupling devices.

Abstract: A method for onboard measurement of a deviation in orientation of an object from a desired orientation of the object. The method including: transmitting a polarized RF signal from a reference source, with a predetermined polarization plane: receiving the signal at a pair of polarized RF sensor cavities positioned symmetrical on the object with respect to the predetermined polarization plane: analyzing an output of the pair of polarized RF sensor cavities resulting from the received signal: and determining the deviation in orientation of the object relative to the predetermined plane based on the analysis. The method can further include controlling the object based on the determined deviation in orientation.

Abstract: An interception system for intercepting incoming missiles and/or rockets including a launch facility, a missile configured to be launched by the launch facility, the missile having a fragmentation warhead, a ground-based missile guidance system for guiding the missile during at least one early stage of missile flight and a missile-based guidance system for guiding the missile during at least one later stage of missile flight, the missile-based guidance system being operative to direct the missile in a last stage of missile flight in a head-on direction vis-a-vis an incoming missile or rocket.

Abstract: Methods and systems are disclosed that automatically display an optimized aimpoint on a target image in received seeker data. In one embodiment, a method receives missile seeker target data. A seeker mode data is extracted from the received missile seeker target data. The location of a most vulnerable spot on a target is identified based on a comparison of target library data with seeker image data. A marker is generated at the location of the optimized aimpoint and output to a display.