Abstract: An imaging device includes: an array of liquid crystal cells, each liquid crystal cell providing a respective phase shift to electromagnetic radiation passing through the liquid crystal cell; control electronics for controlling the phase shifts provided by each of the liquid crystal cells; a detector; and an image processor for generating an image from electromagnetic radiation detected by the detector. The array of liquid crystal cells form a plurality of patches; and the control electronics is configured to control the phase shifts of the cells of each patch to form each patch into a respective lens that focuses electromagnetic radiation towards the detector such that the plurality of patches form an array of lenses.

Abstract: A spatially-distributed architecture (SDA) of antennas transmits respective uniquely coded signals. A first receiver having a known position in a coordinate system defined by the SDA receives reflected versions of the uniquely coded signals. A first processor receives the reflected versions of the uniquely coded signals and identifies a position of a non-cooperative object in the coordinate system. A platform with a platform receiver receives non-reflected versions of the uniquely coded signals. The platform determines a position of the platform in the coordinate system. In an example, the platform uses a self-determined position and a position of the non-cooperative object communicated from the SDA to navigate or guide the platform relative to the non-cooperative object. In another example, the platform uses a self-determined position and information from an alternative signal source in a second coordinate system to guide the platform. Guidance solutions may be generated in either coordinate system.

Abstract: The presently disclosed subject matter includes a computerized method and system for determining miss-distance between platforms. The proposed method and system make use of an electro optic sensor (e.g. camera) mounted on one of the platforms for obtaining additional data which is used for improving the accuracy of positioning data obtained from conventional positioning devices. A navigation error is calculated where the relative position of the two platforms is converted to the camera reference frame. Once the navigation error is available, it can be used to correct a measured miss-distance.

Abstract: Apparatus and associated methods relate to determining a course-correction signal for a spin-stabilized projectile based on a time sequence of images of a scene aligned with and obtained by a forward-looking imager coupled to the projectile. As the projectile rotates, the aligned scenes captured in the images obtained by the forward-looking imager are rotated. The rotation angle of each of the captured scenes corresponds to the spin angle of the projectile at the time of image exposure. Objects in the captured scenes will circle about a rotation center of the time-sequence images. The distances from a rotation center to the objects in the captured scenes, as well as the rotation angles of the captured scenes can be used to generate a course-correction signal so that the projectile can be guided to a target selected from the objects in the captured scene.

Abstract: Systems, methods, and computer-executable instructions for creating a query execution plan for a query of a database includes receiving, from the database, a set of previously executed query execution plans for the query. Each previously-executed query execution plans includes subplans. Each subplan indicates a tree of physical operators. Physical operators that executed in the set of previously-executed query execution plans are determined. For each physical operator, an execution cost based is determined. Invalid physical operators from the previously-executed query execution plans that are invalid for the database are removed. Equivalent subplans from the previously-executed query execution plans are identified based on physical properties and logical expressions of the subplans. A constrained search space is created based on the equivalent subplans. A query execution plan for the query is constructed from the constrained search space based on the execution cost.

Abstract: A device that causes a weapon to fire upon a target when the weapon is enabled by an operator, and when the weapon point of impact passes through a target or in a proximity thereto and when the target satisfies certain criteria as determined by one or more sensors/designations. The invention triggers the release of a round, multi-round burst, rocket, missile, or other projectile(s) when enabled by the operator, and when the target passes through the point of impact (or desired/computed proximity thereto), relieving the operator of the split second judgment in timing the release and/or cessation of such fire. The results include reduction in off-target rounds fired, increased hit rate, conservation of ammunition, more effective targeting for non-motion-stabilized weapons, and the introduction of a backup mode for nominally motion-stabilized weapons which may allow effective operations when primary stabilization systems fail or are overwhelmed by dynamics.

Abstract: A watching apparatus includes a housing, a display provided on the housing, a camera provided on the housing, a determiner that determines a watching target in a camera image captured by the camera, a position detector that detects a position of the watching target in the camera image, and a display controller that displays an application image that does not include the camera image on the display on the basis of the detected position of the watching target.

Abstract: A multiple target tracker and beam steerer utilizes liquid crystal waveguide (LCWG) beam steering to illuminate multiple tracked targets per frame one target at a time for designation, range finding or active imaging. The steering rate and range afforded by the LCWG supports various tracker configurations (out-of-band, in-band or dual-band video cameras), LADAR detectors (single pixel or pixelated) and prioritization of tracked targets to vary the revisit rate or dwell time for an illuminated target. A user interface accepts commands from an operator to select the targeting mode, control cue-box size and position within the FOV and target selection.

Abstract: A system for communicating with a projectile in flight toward an intended target includes a barrel-launched projectile and a remote receiver. The barrel-launched projectile includes an ordnance portion, an active communications apparatus and an onboard speed control. The active communications apparatus includes an onboard receiver, an electromagnetic wave reception device, and an active transmitter. The electromagnetic wave reception device includes at least one from the group consisting of an antenna and a photo receptor and is configured to receive an electromagnetic signal. The electromagnetic wave reception device is connected to provide a signal derived from the electromagnetic signal to the onboard receiver to deploy the onboard speed control. The active transmitter is connected and configured for transmitting a signal to the remote receiver during flight and before activation of the speed control.

Abstract: An ordnance munition is included in an intelligent ordnance projectile delivery system and equipped with targeting and guidance systems that allow the ordnance munition to collaborate with other devices to intelligently select targets and/or to guide the ordnance munition to its selected target. The ordnance munition may determine its approximate current location, form a communication group with a wireless transceiver that is in close proximity, and send the approximate current location to the wireless transceiver and/or other devices in the communication group. In response, the ordnance munition may receive location information from the wireless transceiver and/or other devices that are in the communication group. The ordnance munition may determine its more precise location based on the information received from the wireless transceiver, and alter its flight path based in the updated and more precise location.

Abstract: A mobile ballistics processing and display system for receiving data associated with one or more ballistics variables, for processing such variables, and for displaying a ballistics solution associated with such variables in an easily and quickly understandable map format. One or more ballistics variables are inputted into a mobile computing device or are otherwise acquired by such device. Projected in-flight projectile characteristics are calculated by the computing device based upon ballistics variables. Users are provided with the ability to input in-flight bullet characteristics criteria into the computing device. The computing device is configured to depict in map format, projected paths of a projectile from one or more shooter locations to one or more target locations.

Abstract: A method of identifying at least one target includes receiving a series of images over time of pulsed energy reflected from the at least one target, each image including a plurality of pulses related to different first and second pulse codes, detecting the pulses in an image of the received images, and outputting pulse detection information including XY coordinates and arrival time information associated with the respective detected pulses. The method further includes associating the pulse detection information with the first and second pulse codes based on the arrival time information, and generating output position information for the at least one target in space that indicates output positions for the at least one target based on the XY coordinates and being associated with the corresponding first and second pulse codes.

Abstract: A signal multiplexing apparatus and method using layered division multiplexing are disclosed. A signal multiplexing apparatus according to an embodiment of the present invention includes a combiner configured to generate a multiplexed signal by combining a core layer signal and an enhanced layer signal at different power levels; a power normalizer configured to reduce the power of the multiplexed signal to a power level corresponding to the core layer signal; a time interleaver configured to generate a time-interleaved signal by performing interleaving that is applied to both the core layer signal and the enhanced layer signal; and a frame builder configured to generate a broadcast signal frame using the time-interleaved signal and L1 signaling information.

Abstract: A reconfigurable optical device includes a spatial light modulator and an optical signal generator. The spatial light modulator includes a layer of optically-sensitized carbon nanotubes, and each optically-sensitized carbon nanotube is configured to transition between a conductive state and a semiconductive state responsive to an optical signal. The optical signal generator is configured to provide the optical signal to the spatial light modulator to cause the layer of optically-sensitized carbon nanotubes to form a pattern of conductive nanotubes, the pattern of conductive nanotubes configured to modify interfering signal to form an optical vortex.

Abstract: A system for communicating with a projectile in flight toward an intended target includes a barrel-launched projectile and a remote receiver. The barrel-launched projectile includes an ordnance portion, an active communications apparatus and an onboard speed control. The active communications apparatus includes an onboard receiver, an electromagnetic wave reception device, and an active transmitter. The electromagnetic wave reception device includes at least one from the group consisting of an antenna and a photo receptor and is configured to receive an electromagnetic signal. The electromagnetic wave reception device is connected to provide a signal derived from the electromagnetic signal to the onboard receiver to deploy the onboard speed control. The active transmitter is connected and configured for transmitting a signal to the remote receiver during flight and before activation of the speed control.

Abstract: A multiple target tracker and beam steerer utilizes liquid crystal waveguide (LCWG) beam steering to illuminate multiple tracked targets per frame one target at a time for designation, range finding or active imaging. The steering rate and range afforded by the LCWG supports various tracker configurations (out-of-band, in-band or dual-band video cameras), LADAR detectors (single pixel or pixelated) and prioritization of tracked targets to vary the revisit rate or dwell time for an illuminated target. A user interface accepts commands from an operator to select the targeting mode, control cue-box size and position within the FOV and target selection.

Abstract: Methods and apparatus for positioning aircraft based on images of mobile targets are disclosed. An example method includes identifying, by executing first instructions via a processor, a mobile target in an image obtained by a camera mounted on a first aircraft and obtaining, by executing second instructions via the processor, current coordinates of the first aircraft. The example method includes determining, by executing third instructions via the processor, coordinates of the mobile target based on the coordinates of the first aircraft and the image. The coordinates of the mobile target are within an area of uncertainty. The example method includes determining, by executing fourth instructions via the processor, a first position for the first aircraft that reduces the area of uncertainty of the coordinates of the mobile target.

Abstract: An improved emitter tracking system. In aspects of the present teachings, the presence of a desired emitter may be established by a relatively low-power emitter detection module, before images of the emitter and/or its surroundings are captured with a relatively high-power imaging module. Capturing images of the emitter may be synchronized with flashes of the emitter, to increase the signal-to-noise ratio of the captured images.

Abstract: A device for mounting a weapon system to an aircraft includes an adaptor to couple to an internal structure of the aircraft. The device also include a gun mount and a deployment system. The deployment system is coupled to the adaptor to the gun mount and is configured to move the gun mount from a first position internal to the aircraft to a second position at least partially external to the aircraft.

Abstract: A method for planning and launching two or more missiles, to be included in the same mission, and where this is done from one or more aircraft in such a way that the missiles arrive at same target approximately at the same time without interfering with each other on the way to the target. The planning of the mission is performed by sending a set of identical mission data to the missiles prior to launch; letting each missile be assigned a unique identity, letting each missile calculate identical trajectories and a unique offset to this, in one or more of four dimensions, where a resulting offset trajectory is unique for each missile and based on the identical mission data and unique identity, and launching the missiles included in the same mission.

Abstract: Aspects provide a surveillance device that is autonomous and includes data processing components which, in real time, process values measured by measurement components and transmit the results of processing operations to logging components for logging, the measurement components including elements that measure values of parameters representative of a mechanical environment and elements that measure values of parameters representative of a climatic environment. Aspects also include restitution components that enable restitution of the logged data and results of processing operations at any time.

Abstract: An independently operable flight data capture and transmission device includes an aerodynamically efficient main body having a mounting bracket for securing the device onto the wings, fuselage or strut of an aircraft during flight. A sensor suite is positioned within the main body to independently capture flight data information pertaining to the flight characteristics, statistics, metrics, performance and environment of the aircraft during flight. A control unit is positioned within the main body to selectively control an operation of the sensor suite, store the flight data information within a memory and communicate with a user device. A mobile application displays the flight data information and communicates operating instructions to the device, and a power generation unit generates power for use by the system components during flight.

Abstract: A system to merge and exploit two uniquely different types of seeker homing modes of functionality into a single, dual-mode seeker, using only an FPA as the active sensor to achieve both modes of operation. The disclosed embodiments also provide a means to actively designate & track, and also passively track the same target between active designation pulses to track a target at an update rate higher than the designator pulse rate with less demanding automatic target tracking algorithms. The disclosed embodiments eliminate the need for automatic target acquisition/recognition algorithms necessary for purely passive target tracking. The passive tracking methodology “aids” the passive tracking algorithm, based on frame-to-frame image registration, with active SAL track information to improve overall seeker guided weapon performance.

Abstract: A method for autonomous weapon effects planning includes receiving the desired lethality and collateral effects information on a target and autonomously selecting at least one weapon and fuze setting from an inventory of weapons based on the received lethality and collateral effects information. The method further includes autonomously; determining which weapon with fuze setting and terminal elevation and heading angles satisfies the desired lethality and collateral effects; shaping weapon trajectory to satisfy weapon maneuverability, terrain clobber avoidance and guidance requirements and planning weapon launch conditions for the one or more autonomously selected weapons. The weapon launch conditions include at least a launch point or a launch corridor.

Abstract: A combined submersible vessel and unmanned aerial vehicle preferably includes a body structure, at least one wing structure, at least one vertical stabilizer structure, and at least one horizontal stabilizer structure. A propulsion system is coupled to the body structure and is configured to propel the flying submarine in both airborne flight and underwater operation. Preferably, the propulsion system includes a motor, a gearbox coupled to the motor and configured to receive power generated by the motor and provide variable output power, a drive shaft coupled to the gearbox and configured to transfer the variable output power provided by the gearbox, and a propeller coupled to the drive shaft and configured to accept power transferred to it from the drive shaft. The propeller is further configured to rotate and propel the flying submarine in both an airborne environment and in an underwater environment.

Abstract: A system and method for tracking and engaging a boosting airborne object comprises a plurality of sensors, a first vehicle, and a second vehicle. The plurality of sensors are configured to detect and track the boosting airborne object. The first vehicle is configured to launch and guide an intercept object based on data it receives from the plurality of sensors. A second vehicle is configured to receive a cue from the first vehicle to acquire track of the airborne object and then provide track data to the first vehicle even after burnout, thereby enabling the first vehicle to provide midcourse guidance to the intercept object. The first vehicle may be positioned farther from a launch point of the airborne object than the second vehicle, thereby providing the first vehicle an increased engagement time and the second vehicle a better position to acquire track of the boosting airborne object.

Abstract: An automated process uses a local positioning system to acquire location (i.e., position and orientation) data for one or more movable target objects. In cases where the target objects have the capability to move under computer control, this automated process can use the measured location data to control the position and orientation of such target objects. The system leverages the measurement and image capture capability of the local positioning system, and integrates controllable marker lights, image processing, and coordinate transformation computation to provide tracking information for vehicle location control. The resulting system enables position and orientation tracking of objects in a reference coordinate system.

Abstract: A system for performing object identification combines pose determination, EO/IR sensor data, and novel computer graphics rendering techniques. A first module extracts the orientation and distance of a target in a truth chip given that the target type is known. A second is a module identifies the vehicle within a truth chip given the known distance and elevation angle from camera to target. Image matching is based on synthetic image and truth chip image comparison, where the synthetic image is rotated and moved through a 3-Dimensional space. To limit the search space, it is assumed that the object is positioned on relatively flat ground and that the camera roll angle stays near zero. This leaves three dimensions of motion (distance, heading, and pitch angle) to define the space in which the synthetic target is moved. A graphical user interface (GUI) front end allows the user to manually adjust the orientation of the target within the synthetic images.

Abstract: Missile guidance involving projection of laser light to define a Laser Information Field (LIF) is augmented by interposition of information pulses, interleaved between laser emissions establishing the LIF. Information pulses encode further information for receipt by a missile, such as an angle of roll of a missile launch platform from which the LIF is emitted.

Abstract: The object of the present invention is to provide an inventive guidance system for tracking and guiding at least one object, wherein said guidance system comprises a base station (1) including an optical imaging system (3) configured to determine the angular position vector of said at least one object (5, 15), an optical communication link for transmitting guidance control commands from said base station (1) to said at least one object (5, 15), and steering means provided on said at least one object (5, 15) for adjusting the direction of said at least one object (5, 15) in response to said guidance control commands. The invention also provides a corresponding guiding method.

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 is provided for optically providing at least one of power and data to a projectile from an external optical source. The method including: outputting an optical signal from an external optical source into an interior of the projectile; receiving the optical signal in the interior of projectile and at least one of converting the optical signal to electrical energy and storing data provided in the optical signal. The electrical energy can be provided to the one or more electronic components and/or energy storage medium disposed on the interior of the projectile. The data provided in the optical signal can be provided to a data storage medium disposed on the interior of the projectile.

Abstract: A relative navigation system projects a grid into space from a grid generator and an object, such as an unmanned aerial vehicle, may use the projected grid to aid in the landing of the object. Methods of adjusting the projected grid including stabilizing the projected grid and orienting the grid generator relative to the earth.

Abstract: An unmanned aerial vehicle with a camera and conventional sensors, where the processor navigates the vehicle based at least in part on the image data and the sensor data. A method for navigating an unmanned aerial vehicle where a processor navigates the vehicle based at least in part on image data corrected by traditional sensor data.

Abstract: A projectile and associated method are provided for seeking a target that has been laser designated even though the projectile does not include a laser receiver. A projectile includes an aerodynamic body and a GPS receiver configured to receive GPS signals indicative of a location of the aerodynamic body. The projectile also includes a radio receiver configured to receive radio signals from an offboard laser receiver that provide information relating to a location of the target based upon laser designation of the target. Further, the projectile includes a processor configured to direct flight of the aerodynamic body toward the target based upon the location of the aerodynamic body as determined from the GPS signals and the location of the target based upon the information provided by the offboard laser receiver.

Abstract: A mobile tracking and subduing apparatus of a target object that includes liquid storage tank that is configured hold a predetermined amount of a liquid, a probe configured to inject the liquid from the liquid storage tank into a skin surface of a target object, an optical detection unit for obtaining image or video data, a GPS unit that generates positional data, a wireless communications interface configured to receive command data, and a target tracking unit for detecting and tracking the target object based on the received positional data, command data, and images or video data and inject the contents of the liquid storage section into the target object via the probe.

Abstract: The invention relates to a method of guiding a salvo of guided projectiles to a target. The method comprises the steps of generating a beam defining a common reference coordinate system, determining the position of each projectile relative to the beam, and providing to each projectile: position information of other projectiles. Further, the method includes the step of associating dispersion parameters to the salvo of guided projectiles. In addition, the method comprises the step of determining numerical values of the dispersion parameters based on accuracy uncertainty. Also, the method includes the step of controlling the projectiles to an optimal dispersion by using a swarming technique based on the position information of the projectiles and on the numerical values of the dispersion parameters.

Abstract: A steerable projectile (30) comprises a body portion (32) and a nose portion (34). The nose portion and body portion are substantially coaxially arranged and rotatable relative to one another about their co-axis. The nose portion further comprises an asymmetric formation (36) operable to enable the projectile to be subjected to off-axis drag during flight.

Abstract: A method and system for determining an optimal missile intercept approach direction to maximize the probability of association between a remote sensor designated object and a corresponding missile seeker-observed object. The method and system calculates a distance metric between a remote sensor designated object and the corresponding missile seeker-observed object, and calculates the probability that the remote sensor designated object and the corresponding missile seeker-observed object have a smaller distance metric between them than between the remote sensor designated object and any other missile seeker-observed object.

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: In certain aspects, this invention is a “control system” that detects and minimizes (or otherwise optimizes) an angle between vehicle centerline (or other reference axis) and vehicle velocity vector—as for JDAM penetration. Preferably detection is exclusively by optical flow (which herein encompasses sonic and other imaging), without data influence by navigation. In other aspects, the invention is a “guidance system”, with optical-flow subsystem to detect an angle between the vehicle velocity vector and line of sight to a destination—either a desired or an undesired destination. Here, vehicle trajectory is adjusted in response to detected angle, for optimum angle, e.g. to either home in on a desired destination or avoid an undesired destination (or rendezvous), and follow a path that's ideal for the particular mission—preferably by controlling an autopilot or applying information from navigation.

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: A system for guiding a gun-fired or mortared round towards an intended target, the system including a round having: a forward facing image pick-up device for capturing image data; a first transceiver; guidance device for varying a flight path of the round; and a first processor. The system further including a control platform remotely located from the round, the control platform having: a second transceiver; a second processor; an input device; and a display. Where the first processor transmits image data from the image pick-up device through the first transceiver to the second processor through the second transceiver, the second processor transmits guidance information from the second transceiver to the first processor through the first transceiver and the first processor controls the guidance device based on the guidance information to guide the round towards the intended target.

Abstract: A method for determining a position of a device in a reference coordinate system. The method including: receiving, at the device, less than all of GPS signals necessary to determine the position of the device in the reference coordinate system; transmitting a signal from a? illuminating source defined in the reference coordinate system; receiving the signal at a cavity waveguide disposed on the device; and determining the position of the device in the reference coordinate system based on the GPS signals and the signal received in the cavity waveguide. The signal received in the cavity waveguide can also be used to confirm a position determined by the GPS signals.

Abstract: A sensor system uses ground emitters to illuminate a projectile in flight with a polarized RF beam. By monitoring the polarization modulation of RF signals received from antenna elements mounted on the projectile, both angular orientation and angular rate signals can be derived and used in the inertial solution in place of the gyroscope. Depending on the spacing and positional accuracies of the RF ground emitters, position information of the projectile may also be derived, which eliminates the need for accelerometers. When RF signals of ground emitter/s are blocked from the guided projectile, the sensor deploys another plurality of RF antennas mounted on the projectile nose to determine position and velocity vectors and orientation of incoming targets.

Abstract: A method for onboard determination of a roll angle of a projectile. 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 projectile with respect to a reference roll position on the projectile; measuring a difference between an output of the pair of polarized RF sensor cavities resulting from the received signal to determine zero output roll positions of the projectile; and comparing an output of the pair of polarized RF sensor cavities at each of the zero output positions to determine when the projectile is parallel to the predetermined polarization plane. The method can also include analyzing an output of at least one third sensor positioned on the projectile to determine whether the roll angle position of the projectile is up as compared to the horizon.

Abstract: Sensor(s) may be used to detect threat data. A processing system and/or a method may be used to fuse the detected threat data over time. Threat data may comprise information on a munition, missile, rocket, or nuclear/biological/chemical (NBC) projectile or delivery system. Detected threat data may be processed to create a target track-lethality list comprising the locations of any target(s) and a ranking of their lethality in comparison to decoys or chaff. The target track-lethality list may be used to create a target engagement-track list that matches available threat elimination resources (e.g. interceptors) to targets with a weapon-to-target assignment module.

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: The present invention provides a position control system for a remote-controlled vehicle, a vehicle operated by the control system, and a method for operating a remote-controlled vehicle. An electromagnetic energy receiver is configured to receive an electromagnetic beam. The electromagnetic energy receiver is further configured to determine a position of the remote-controlled vehicle relative to a position of the electromagnetic beam. The vehicle is directed to maneuver to track the position of the electromagnetic beam.

Abstract: A method is provided for guiding a mortar projectile fired longitudinally from a launcher along a ballistic trajectory. The method includes providing a first inertial navigation system (INS), a laser emitter and optical sensor on the launcher, providing a second INS and a laser reflector on the projectile, and presetting the second INS to an initial reference position prior to firing the projectile. Subsequent to launch, the method further includes emitting a longitudinally directed laser beam from the emitter to the reflector; receiving the reflected signal to the optical sensor; establishing a position and velocity of the projectile based on the reflected signal; transmitting a correction signal to the projectile from the launcher; resetting the second INS at a position prior to reaching maximum altitude; and guiding the projectile along the trajectory by adjusting control fin orientation.