Abstract: A pressure oscillation damping mechanism comprises a cavity having an entrance exposed to fluid flowing on an exterior of the cavity. The damping mechanism may include a constriction positioned adjacent to the entrance and being sized to dampen an amplitude of the pressure oscillations occurring within the cavity.

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

Abstract: A method for determining a location of a flying target included identifying and measuring the target by at least two seeker systems disposed at a distance from one another. The position of the target relative to at least one of the two seeker systems is determined from measurement data derived therefrom. The position of the target is measured inconspicuously and without active radiation, in that the seeker systems are data-networked, passive target tracking systems for missiles, which autonomously track the target and align the missile with the target. The measurement data determined by the data-networked seeker systems are combined, and the location of the target is determined from the combined data.

Abstract: A target tracking device incorporating a Position Sensitive Detector (PSD) 1 is described. A target is illuminated by a laser of a suitable wavelength. The target reflects the laser radiation and the reflected radiation is incident on a flying vehicle carrying a target tracking device. The PSD in the device outputs a signal representative of the position of the incident laser spot. The output signal is input into control electronics, the control electronics incorporating a resistive transimpedance amplifier. A higher than usual bias voltage is applied to the PSD yielding improved pulse response of the target tracking device. Therefore, the tracking device is particularly suited for use with a target marking laser having a short pulse duration.

Abstract: A micro designator dart engages a target to allow for designation and tracking of the target by transmitting a radio-frequency identification code. The housing of the micro designator dart is configured to enclose its components and deform upon impact with a target to allow a target-engaging member to physically attach the micro designator dart to the target. Also upon impact with the target, an impact-sensitive triggering mechanism in the micro designator dart activates a power source, causing a transmitter to send a predetermined coded infrared signal to the seeker unit of a precision guided munitions system. The micro designator dart may also include a self-destruct device.

Abstract: An optical guidance system for guiding a projectile is disclosed. The optical guidance system includes a laser, a first and second cylindrical holographic lenses and a variable zoom lens. The laser generates a laser beam, and the first and second cylindrical holographic lenses transform the laser beam into a x-direction and y-direction scan patterns, respectively. The variable zoom lens projects the x-direction and y-direction scan patterns in the form of multiple scan fields, each within a scan corridor, in order to guide a projectile along a flight path towards a target.

Abstract: A method for guiding a gun-fired or mortared round towards an intended target. The method including: capturing image data from an image pick-up device during a descent of the round; transmitting the image data to a control platform remotely located from the round; transmitting guidance information to the round from the remote platform based on the captured image data; varying a flight path of the round based on the guidance information to guide the round towards its intended target.

Abstract: An optical impact system controls munitions termination through sensing proximity to a target and preventing effects of countermeasures on false munitions termination. Embodiments can be implemented on in a variety of munitions such as small and mid caliber that can be applicable in non-lethal weapons and in weapons of high lethality with airburst capability for example and in guided air-to-ground and cruise missiles. Embodiments can improve accuracy, reliability and lethality of munitions depending on its designation without modification in a weapon itself and make the weapon resistant to optical countermeasures.

Abstract: Autonomous collision avoidance systems for unmanned aerial vehicles are disclosed. Systems illustratively include a detect and track module, an inertial navigation system, and an auto avoidance module. The detect and track module senses a potential object of collision and generates a moving object track for the potential object of collision. The inertial navigation system provides information indicative of a position and a velocity of the unmanned aerial vehicle. The auto avoidance module receives the moving object track for the potential object of collision and the information indicative of the position and the velocity of the unmanned aerial vehicle. The auto avoidance module utilizes the information to generate a guidance maneuver that facilitates the unmanned aerial vehicle avoiding the potential object of collision.

Abstract: An object of interest in a cloud of objects is identified by RF and IR sensing. The RF and IR signals are separately discriminated to determine the probability that the RF tracked object is one of a predetermined number of possible object types, and the IR tracked object is one of the possible object types. Joint probabilities are calculated for all pairs of RF and IR signals and all objects, and the joint probabilities are normalized. Marginal probabilities of the joint RF/IR discrimination results are calculated to produce a vector set of marginal optical probabilities. The vector set is normalized over all object types to thereby produce a vector set of normalized marginal optical probabilities. The object of interest is selected to be the IR object of said vector set of normalized joint optical probabilities with the highest probability of being the object type of interest.

Abstract: This disclosure includes embodiments of laser-seeking munitions, and methods of constructing laser-seeking munitions. Some embodiments of these munitions comprise a body; one or more sensors; a plurality of lenses coupled to the body and configured to be capable of transmitting light to the one or more sensors. Some embodiments comprise one or more baffles coupled to the plurality of lenses, the one or more baffles configured to substantially block a portion of the plurality of lenses from transmitting light to the one or more sensors. Some embodiments comprise a plurality of optical fibers optically coupled to the sensor(s) and the lense(s), where the fibers are configured to substantially block a portion of each of the plurality of lenses from transmitting light to the one or more sensors.

Abstract: A modulation device provides optical energy to hamper the operation of a mobile tracking device. The optical energy may include multiple mobile device specific optical codes directed at the mobile tracking device in parallel.

Abstract: An optical system for a missile has optics for imaging an object through a beam path on an imaging plane. The optics have external optics, rotatably mounted about a roll axis and a pitch axis of the missile, and internal optics, and one of the ends of the beam paths is fixed with respect to the structure in the missile. In order to prevent image disturbances caused by shadows which are caused at a high squint angle by an element which is fixed to the structure, the optical system includes a shutter, which can be introduced into the beam path during flight of the missile, in order to mask out a shadow, which is produced by an element of the missile, in the beam path in a viewing direction of the external optics which is tilted with respect to the roll axis.

Abstract: A communication interface for a laser-guided projectile is configured to use the SAL seeker on board the laser-guided projectile as a communication link. A communication device generates a pulsed optical beam that overlaps the detection band of the SAL seeker. The pulsed optical beam is encoded with data for the SAL seeker. Computer-readable program code is loaded into and executed by the seeker's signal processor to process the signals generated in response to the pulsed optical beam to extract the data for the SAL seeker. Data is typically coupled to the projectile pre-launch but may be coupled in flight to the target.

Abstract: An off-axis reflective transmit telescope for a DIRCM system is mounted on the gimbal along a transmit-axis offset laterally from the optical axis of the receive telescope but nominally aligned with the line-of-sight of the receive telescope to transmit a laser beam. The telescope comprises an optical port optically coupled to a laser to receive and direct the laser beam away from the dome and a reflective optical assembly that reflects the laser beam through the dome. The reflective optical assembly comprises an off-axis mirror segment and a second optical element that together precompensate the laser beam for dome aberrations induced by the lateral offset of the transmit telescope's transmit axis from the optical axis. The off-axis mirror segment comprises a segment of a parent mirror having an aspheric curvature (e.g. parabolic, elliptical or higher-order asphere) about an axis of symmetry. The segment is offset so that it is not centered on the axis of symmetry of the parent mirror.

Abstract: An optical device forms a beam path between an optical end element at a beam path end and an object scene into which the beam path is directed via a field of view of the end element. The optical device contains an alignment device for pivoting the field of view relative to a predetermined direction, an end optical unit and an optical articulation for guiding the beam path from the pivoted field of view into the end optical unit. In order to achieve good shielding against spurious radiation, the device has a shielding unit containing a shielding element led partly around the optical articulation, which shielding unit shields the optical articulation against incident radiation that is not incident through the entrance or exit aperture of the optical articulation.

Abstract: A communication interface for a laser-guided projectile is configured to use the SAL seeker on board the laser-guided projectile as a communication link. A communication device generates a pulsed optical beam that overlaps the detection band of the SAL seeker. The pulsed optical beam is encoded with data for the SAL seeker. Computer-readable program code is loaded into and executed by the seeker's signal processor to process the signals generated in response to the pulsed optical beam to extract the data for the SAL seeker. Data is typically coupled to the projectile pre-launch but may be coupled in flight to the target.

Abstract: The present invention relates to a method for measuring the angular position of a contrasting edge of an object having a luminance transition zone which is substantially rectilinear in a given direction and separates two regions of different luminances. This method comprises the functional steps of: —carrying out, in a transverse direction different from the given direction, an amplitude modulation of the signals delivered by a first and a second optical sensor; and —calculating an output signal (Yout(t)) starting from the signals delivered by the first and the second optical sensors (D1, D2) as a function of the angular position of the luminance transition zone. Device and set of devices for measuring the angular position of a contrasting edge and steering aid system for fixation and tracking a target comprising at least one such contrasting edge.

Abstract: A semi-active laser (SAL) sensing system is provided that uses a lightpipe to pass received reflected laser light from an aperture to a detector. The lightpipe facilitates further miniaturization of the SAL sensing system by taking the place of a larger lens system that would otherwise be required. For example, the use of the lightpipe in a missile or guided projectile can facilitate the placement of the SAL sensing system with other sensors in the limited available space at the front of the missile. In one embodiment, the lightpipe is formed from cladded optical fibers that are bundled together, shaped, and fused together. The core material from the optical fibers are then dissolved away, leaving the outer cladding. This remaining outer cladding remains fused together, and maintains its shape, thus forming a lightpipe that can be used in a SAL sensing system.

Abstract: An optical window for a detection system and method of employing the same. In one embodiment, the detection system includes an optical window configured to internally channel external incident radiation to an exit surface for emission. The detection system also includes a detector oriented to receive emitted radiation from the exit surface.

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

Abstract: A countermeasure device for directing a mobile tracking device away from an asset is provided. The countermeasure device includes a continuous wave laser source whose output is directed at a seeker head of the mobile tracking device. The countermeasure device causes the generation of localized sources within the mobile tracking device and confuses the mobile tracking device as to the true location of the asset.

Abstract: A missile nose fairing system includes sections attached at an aft end thereof to a missile body, a restraint for normally preventing aftward displacement of the plurality of sections, and a drive unit for releasing the restraint in response to a received signal. Each of the sections has an outer surface that converges to a common forward pointed tip for enclosing and protecting a guidance head when in an extended position and is retractable into a corresponding recessed region formed within a missile nose when the drive unit is activated releasing the restraint.

Abstract: Some embodiments relate to an optical assembly that includes an energy collection system that collects energy and a heat shield that axially restrains the energy collection system. The optical assembly further includes a sensor and a structure which supports the energy collection system such that the energy collection system directs the energy to the sensor. Other embodiments relate to a projectile that includes a propulsion system, a guidance system and an optical assembly as described above. Other embodiments relate to a method of directing a projectile that includes collecting energy using an energy collection system; directing the energy to a sensor; axially restraining the energy collection system using a heat shield; using a guidance system to determine the position of the projectile based on data received from the sensor; and directing the projectile toward the destination using a propulsion system that is commanded by a guidance system.

Abstract: The invention relates to an unmanned air vehicle control system and method, designed such that, in one mission mode, the vehicle follows the mission route. The system comprises means (400, 450) for storing data indicating at least one auxiliary route (4000, 4001, 4002, 4003), such that each of a plurality of the mission route segments (10, 20), is assigned at least part (30, 31, 32, 33) of at least one auxiliary route. Furthermore, the system comprises route change means (53) designed for, as a response to a mission abandonment event (52), determining which part of which auxiliary route is assigned to the mission route segment where the vehicle is located, such that the vehicle can change the mission route to the corresponding auxiliary route.

Abstract: A mount for a seeker head includes a plane spanned by a holder frame in which the pitch motion of the device containing at least one detector can be performed with respect to the missile structure and within the holder frame, at right angles to the plane spanned by the holder frame, a rotating mechanism for the rotational yaw motion of the device containing at least one detector is arranged about a rotation axis lying in the plane spanned by the holder frame. The pitch and yaw motion of the device is possible in a range of much more than +/?90°.

Abstract: Guided airborne weapons fired in a salvo against multiple targets are deconflicted by performing a scene correlation of multiple cued targets to TLOs acquired by the seeker's imaging sensor to track a target package. If the weapon is provided with a multimode seeker, target cues for a common designated target and a common SAL code are provided to each weapon. Each weapon uses its SAL sensor to detect and process a SAL return to verify the common SAL code and augment their scene correlations by fixing the TLO track file of the common designated target to the cued track file associated with the designated target. At terminal, each weapon commits to a particular target by referencing its assigned target to the tracked target package. Correlation to multiple targets in the target package makes the acquisition and tracking process more robust and reduces targeting ambiguity. Furthermore, a single SAL designation can improve the tracking of all the weapons to their respective targets.

Abstract: Disclosed herein is a spinel article. The article comprises a spinel material, wherein the spinel material has a monomodal grain size distribution with average grain sizes of less than or equal to about 15 micrometers, and a biaxial flexural strength of greater than or equal to about 300 megapascals when measured by a ring-on-ring flexural test as per ASTM Standard C1499-08. Disclosed herein too is a spinel article manufactured by a method comprising calcining a spinel powder; milling the powder in a milling medium; granulating the powder; screening the powder to a mesh size of about 40 to about 200 mesh; pressing the powder to form an article; burning out organics from the article; sintering the article; and hot isostatically pressing the article.

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

Abstract: In an IR jamming system for defense against missiles with IR-sensitive homing heads, one or more jamming beams are generated, whose diameter is less than that of the optical aperture of the IR-sensitive homing head of the missile. The optical aperture of the IR-sensitive homing head of the missile is at least partially illuminated by the jamming beam or beams.

Abstract: An optical impact system controls munitions termination through sensing proximity to a target and preventing effects of countermeasures on false munitions termination. Embodiments can be implemented on in a variety of munitions such as small and mid caliber that can be applicable in non-lethal weapons and in weapons of high lethality with airburst capability for example and in guided air-to-ground and cruise missiles. Embodiments can improve accuracy, reliability and lethality of munitions depending on its designation without modification in a weapon itself and make the weapon resistant to optical countermeasures.

Abstract: A spin-stabilized projectile has its course controlled by counter rotation of an internal mass about a longitudinal axis of the projectile. The internal mass may be a boom within a cavity of an external body of the projectile. The internal mass may be tiltable relative to the hull, and may be configured to counter rotate relative to the hull about the axis of the hull. The counter-rotation may keep the boom in a substantially same orientation relative to the (non-spinning) environment outside of the projectile. The positioning of the boom or other weight within the projectile thus may be used to steer the projectile, by providing an angle of attack to the projectile hull. A magnetic system may be used to counter rotate the boom or other weight. The projectile may have a laser guidance system to aid in steering the projectile toward a desired aim point.

Abstract: Embodiments of an infrared spectral modulator for scene-based non-uniformity image correction are generally disclosed herein. The spectral modulator may be suitable for use in a system for navigating an object having a flight path comprising an infrared sensor having an optical path; an infrared modulator in the optical path of the infrared sensor, wherein the infrared modulator is configured to allow the infrared sensor to perform in situ, real-time, scene-based non-uniformity correction; and a guidance system within the object, wherein the guidance system can adjust the flight path of the object based on the non-uniformity correction.

Abstract: A laser lead designator for guiding a laser guided weapon (LGW) to strike a moving target includes a laser source for providing a laser beam and a controller coupled to receive a position and a velocity of the moving target. The controller provides a control signal for pointing the laser beam a specified lead distance ahead of the position of the moving target to position a laser spot on a ground location ahead of the moving target. The lead distance compensates for an impact shortfall value that is a function of at least one shortfall parameter including a speed of the moving target so that the LGW shortfalls the laser spot on the moving target. The laser designator is separate from the LGW.

Abstract: A method is provided for characterizing luminous celestial objects (e.g., stars) in celestial navigation of a missile system. The method includes segmenting, assigning, measuring, computing, ratioing, producing, scaling, and determining operations. Segmenting includes subdividing wavelength range into discrete contiguous bins. Assigning arranges each bin into a plurality of color bands. Establishing sets a transmissivity to each bin of each color band. Computing calculates broad-based fluxes for a reference value as a reference flux. Ratioing computes a ratio between the target flux to the library flux as a color scale for each band. Squaring determines the library flux for each band as a library flux squared. Producing sums a spectral scale over the color bands, a second multiplication of the color scale and the library flux squared as a first sum product, and sums over all the bands the library flux squared as a second sum product and dividing the sum products.

Abstract: A countermeasure method for directing a mobile tracking device away from an asset is provided. The countermeasure method includes directing the output of a continuous wave laser source at a seeker head of the mobile tracking device. The countermeasure method causes the generation of localized sources within the mobile tracking device and confuses the mobile tracking device as to the true location of the asset.

Abstract: A projectile has a pair of different parts with respective orientation sensors for detecting orientation, such as the roll position of the parts. The orientation sensors may be any of a variety of sensors, such as magnetometers, light sensors, infrared (IR) sensors, or ultraviolet (UV) sensors. Orientation events of the orientation sensors, such as maxima or minima of sensor output, are determined. The orientation events of the two sensors are compared to produce an alignment correction factor for correcting for misalignment of the parts relative to one another, that is to correct for differences in alignment between the sensors of the two parts. This allows (for example) instructions produced at one of the parts to be usable at the other of the parts.

Abstract: A guidance system may include an optical system to focus incident radiation onto a detector configured to generate at least one guidance signal in response to the focused incident radiation. The optical system may include a first lens having a first side and a second side, the first side consisting of a Fresnel lens formed on a generally convex surface and the second side being generally planar.

Abstract: A weapon and weapon system, and methods of manufacturing and operating the same. In one embodiment, the weapon includes a warhead including destructive elements and a guidance section with a target sensor configured to guide the weapon to a target. The target sensor includes a front lens configured to provide a cover to protect the target sensor from an environment and a fast fresnel lens behind the front lens to provide a multi-lens focusing system for the target sensor. In a related embodiment, the weapon includes an aft section including a tail fin having a modifiable control surface area thereby changing an aspect ratio thereof.

Abstract: A pointing device is provided for directing electromagnetic radiation along a line of sight within a flight vehicle. The pointing device includes a beam deviation structure; a rotation assembly configured to support the beam deviation structure such that the beam deviation structure is pivotable about the rotation axis; and a nod gimbal configured to support the rotation assembly and the beam deviation structure such that the rotation assembly and the beam deviation structure are pivotable about a nod axis.

Abstract: A compact SAL seeker for a projectile guidance system comprises an optical sub-assembly to focus incident electro-magnetic radiation (EMR) such that target bearing in object space is mapped to a spatial irradiance in image space and a detector sub-assembly to generate at least one guidance signal in response to the position of the centroid of the focused EMR. The optical sub-assembly includes an integrated filter stack of a primary optical element, a spreader, a filter and secondary optical element in which at least one and typically both of the spreader and filter are immersed within the optical media of the stack. The detector sub-assembly may include a field lens in which the detector is immersed. Immersion reduces the number of “air-to-glass” interfaces, hence improves optical throughput. The detector sub-assembly may be integrally formed with a mounting bracket adapted to mate with mounting features on the optical sub-assembly to provide a self-aligned seeker.

Abstract: The present invention provides apparatus and methods for accurate guidance of small munitions to a target. The guidance for the small munition is mainly provided by a device external to the small munition, such as an unmanned aerial vehicle (UAV). The UAV may provide external guidance commands by use of a command transmitter to the small munition. The small munition is equipped to receive the guidance commands and consequently use a maneuvering mechanism to react to the guidance commands. The UAV may determine a successful release point of the small munition and track a flight path from a release point toward the target of the small munition using a passive sensor mounted in a gimbaled mount, which is controlled by use of a closed-loop control system. The UAV may be controlled by a ground control device, such as an operator control unit (OCU), to release small munitions.

Abstract: A vehicle including electro-optic (EO) imaging has a vehicle body having an outer surface including a front portion and a side portion, wherein the side portion includes a plurality of portholes. A propulsion source is within the vehicle body for moving the vehicle. A fixed EO imaging system having a field-of-regard (FOR) includes a plurality of fixed EO imaging sub-systems arrayed within the vehicle body. The fixed EO imaging sub-systems each have a different field-of-view (FOV) for providing a portion of the FOR and include a camera affixed within the vehicle body and an optical window secured to one of the portholes for transmitting electromagnetic radiation received from one of the portions of the FOR to the camera, wherein the cameras each generate image data representing one of the portions of the FOR therefrom. A processor is coupled to receive the image data from the plurality of fixed EO imaging sub-systems for combining the image data to provide composite image data spanning the FOR.

Abstract: In a co-boresighted SAL/IR seeker, the optical system and particularly the secondary lens and position of the SAL detector are configured to produce a well-corrected spot of laser energy at the SAL detector. A spreader is positioned between the secondary mirror/lens and the SAL detector, possibly on the secondary mirror, away from the aperture stop and not in the optical path to the IR detector. The spreader is configured to spatially homogenize the laser energy to increase the size of the spot of focused laser energy at the SAL detector to set the system transfer function to meet slope requirements. Spatial homogenization serves to reduce both boresight shift and slope non-linearities. This approach greatly simplifies the time and labor intensive calibration of the SAL detector's system transfer function.

Abstract: A molded dichroic mirror and a seeker comprising a molded dichroic mirror are provided. The dichroic mirror may be molded from polysiloxane or lithia potash borosilicate and may be coated to reflect an infrared signal and configured to transmit a radio frequency signal between 33 GHz and 37 GHz.

Abstract: There is provided an interception system that employs miniature kill vehicles. According to certain embodiments of the invention, a small kill-vehicle (KV) accommodated within an interceptor missile together with additional at least one KV, each KV is equipped with an image acquisition sensor operable in the visible or near IR range, and adapted to be launched from the interceptor missile during exo-atmospheric flight and utilizing said sensor for tracking and homing at least one Re-entry Vehicle (RV) of a Ballistic Missile (BM).

Abstract: A laser source assembly (210) for generating an assembly output beam (212) includes a first laser source (218A), a second laser source (218B), and a dispersive beam combiner (222). The first laser source (218A) emits a first beam (220A) having a first center wavelength, and the second laser source (218B) emits a second beam (220B) having a second center wavelength that is different than the first center wavelength. The dispersive beam combiner (222) includes a common area 224 that combines the first beam (220A) and the second beam (220B) to provide the assembly output beam (212). The first beam (220A) impinges on the common area (224) at a first beam angle (226A), and the second beam (220B) impinges on the common area (224) at a second beam angle (226B) that is different than the first beam angle (226A). Further, the beams (220A) (220B) that exit from the dispersive beam combiner (222) are substantially coaxial, are fully overlapping, and are co-propagating.

Abstract: The present invention relates to the field of unmanned air vehicles, more commonly designated drone. More specifically, the invention applies to an armed drone system (10), notably equipped with a firing device and a steerable optronics ball (B) comprising means of illuminating targets (C). The invention proposes that the firing device be oriented towards the rear, so as to reduce the problems of masking of the optronics ball (B) by elements located in its line of sight, such as a front wheel (FW) for example. Moreover, because of operational use involving a phase (10S) for firing weapons and illuminating the target (C) from the back, the armed drone (10) moving away from the target, the vulnerability of the drone (10) is lessened.

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 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.