Abstract: A collision and conflict avoidance system for autonomous unmanned air vehicles (UAVs) uses accessible on-board sensors to generate an image of the surrounding airspace. The situation thus established is analyzed for imminent conflicts (collisions, TCAS violations, airspace violations), and, if a probable conflict or collision is detected, a search for avoidance options is started, wherein the avoidance routes as far as possible comply with statutory air traffic regulations. By virtue of the on-board algorithm the system functions independently of a data link. By taking into account the TCAS zones, the remaining air traffic is not disturbed unnecessarily. The system makes it possible both to cover aspects critical for safety and to use more highly developed algorithms in order to take complicated boundary conditions into account when determining the avoidance course.

Abstract: The disclosed system, device and method for targeting and measurement of stationary target locations in addition to prediction of moving target positions for given weapon intercept times generally includes: a target location system (TLS) configured with a computing device, a GPS receiver, mapping software, calibration software and digital filtering software. Disclosed features and specifications may be variously controlled, adapted or otherwise optionally modified to improve target acquisition and engagement. Exemplary embodiments of the present invention generally provide for improved accuracy of range finders, magnetometers and inclinometers as well as for improved prediction of moving target positions.

Abstract: A receiver, such as a miniaturized microwave-photonic coherent receiver (MMPR) is disclosed. The receiver includes an antenna to output an electrical RF signal received on a section of the antenna, a laser to produce an optical signal, a photonic modulator to receive the optical signal and the electrical RF signal and produce an EO-RF signal and to receive the optical signal and an electrical LO signal and produce an EO-LO signal, a signal combiner to provide a combined EO-RF and EO-LO signal and a photodiode to receive the combined signal and produce an IF signal. A method of detecting an object using the MMPR includes receiving an electrical RF signal corresponding to the object, outputting the electrical RF signal to a photonic modulator, modulating the electrical RF signal onto an optical carrier, demodulating the electrical RF signal to produce an IF signal and processing the IF signal.

Abstract: A distributed aperture sensor system and sensing method comprising a plurality of sensors each having an aperture and window that provides electromagnetic interference shielding by a material with a bulk resistivity of less than or approximately equal to 10 ohm-cm that is substantially uniform throughout the window.

Abstract: A guidable projectile has a nose member, a projectile body, and a nose member articulation assembly which couples the nose member to the projectile body. The nose member articulation assembly includes a stator attached to the nose member, a rotor attached to the projectile body, and rotational support hardware interconnecting the stator to the rotor. The stator defines a central axis. The rotational support hardware is constructed and arranged to guide rotation of the rotor around the central axis defined by the stator. Such a guidable projectile enables circuitry such as the driver of the stator and the power source to reside at fixed locations relative to the stator thus alleviating the need for slip rings which would otherwise present potential points of failure.

Abstract: A circuit for compensating for frequency modulation on a radar signal is disclosed. The disclosed circuit includes an adaptive narrow band filter in the feedback path of a phase-locked detector, such filter having a bandwidth which is narrower than the frequency range of the signal being compensated, and means for detecting the amplitude of such signal. The invention herein described was made in the course of, or under a contract or subcontract thereunder, with the Department of Defense.

Abstract: A MEMS apparatus includes a substrate; electrical contacts disposed on the substrate; a thermal arch beam supported by and connected between the contacts, the thermal arch beam including a midpoint and a protrusion located at about the midpoint; a lever having an axis of rotation and a bearing surface upon which the protrusion is operable to bear, a pair of lever supports disposed on the substrate for rotatably supporting the lever about the axis of rotation, an area of contact between the protrusion and the bearing surface being positioned vertically between the axis of rotation and the plane of the substrate. A voltage difference between the electrical contacts causes the thermal arch beam to move horizontally in the plane and the protrusion to bear against the lever causing rotation of the lever out of the plane.

Abstract: The invention concerns a device for countering and tracking a threat with optical delay device in the form of a homing-head missile, comprising a homing head adapted to receive an incident coherent light beam and in deflecting same to produce a transmitted beam. The invention is characterized in that the homing head comprises a biprism dividing the transmitted beam into two sub-beams, the biprism being associated with an optical delay device introducing an optical path difference between the two sub-beams greater than the coherence length of the incident beam.

Abstract: An apparatus includes a radome and an evanescent wave-coupled windowing system in the radome. In operation, the apparatus receives radiation reflected from an object that is incident upon a windowing system; emits evanescent waves from the windowing system whose amplitudes are proportional to the angle of incidence of the radiation; and non-coherent, Fresnel direction finds the object.

Abstract: A system under international control is in possession of the firing codes required to launch missiles owned by the parties to the system. Upon a request to the international authority for the release of its firing codes so that it may launch a first strike, the target party is advised of the request and given the opportunity to launch its own missiles first. The system deters first strikes.

Abstract: A DIRCM (Direct IR Counter Measures) system includes a detection and warning apparatus for detecting a missile that might pose a threat on the platform to which said system is allocated, and for generating a warning of its existence. The warning may include data that enable the calculation of the expected direction from which the missile is approaching. The DIRCM system may also include an acquisition device for performing acquisition of the approaching missile in accordance with the data provided by the detection and warning apparatus, and issuing data that may enable the calculation in real time of the updated position of the missile, a fiber laser for generating a laser beam, and a motion and aiming enabled turret, coupled with the laser, for directing the laser beam onto the approaching missile.

Abstract: Embodiments of the invention, therefore, provide improved systems and methods for tracking targets in a simulation environment. Merely by way of example, an exemplary embodiment provides a reflected laser target tracking system that tracks a target with a video camera and associated computational logic. In certain embodiments, a closed loop algorithm may be used to predict future positions of targets based on formulas derived from prior tracking points. Hence, the target's next position may be predicted. In some cases, targets may be filtered and/or sorted based on predicted positions. In certain embodiments, equations (including without limitation, first order equations and second order equations) may be derived from one or more video frames. Such equations may also be applied to one or more successive frames of video received and/or produced by the system.

Abstract: A reconnaissance system includes a projectile having an opening through which images of a target area are acquired, a portable launcher having a mechanism for affixing the launcher to a rifle for launching the projectile to fly along and above the target area, an image acquiring device within the projectile for acquiring images of the target area through the opening, a transmitter within the projectile for transmitting during its flight the acquired images to a remote station, a stabilizing mechanism for stabilizing at least one of the projectile and the image acquiring device while flying in a ballistic trajectory above the target area and a remote station. The remote station includes a receiver for receiving the images transmitted from the projectile and a monitor having a display for displaying the received images.

Abstract: A missile guidance system and method for guiding a missile, mainly horizontally flying, to pass a target at a desired passage height.

Abstract: The invention described herein provides an apparatus and a method to cooperatively track and intercept a plurality of highly maneuvering asymmetric threats using networks of small, low-cost, lightweight, airborne vehicles that dynamically self-organize into an ad hoc network topology. This is accomplished using distributed information sharing to maintain cohesion and avoid vehicle collisions, while cooperatively pursuing multiple targets. An oracle vehicle relays network information to a control base.

Abstract: On adjusting a target specification data error predicted value so as to become larger on detecting maneuver of a target, the target specification data error predicted value is adjusted, in consideration of type of the maneuver and a course of the target, so as to make a direction of varying specification data large and to make a direction of constant specification data small. It is therefore possible to quickly recover a delay of the following of the varying specification data and to avoid increasing an error of the constant specification data.

Abstract: Systems, including apparatus and methods, for driving airflow along a surface of a gimbal. The systems may comprise a gimbal apparatus including a payload and also including a gimbal mount supporting a first gimbal and a second gimbal. The first gimbal may be coupled pivotally to the gimbal mount. The second gimbal may be coupled pivotally to and supported by the first gimbal. The second gimbal may be coupled to and may support the payload. The gimbal apparatus may orient the payload by pivotal movement of the first and second gimbals relative to the gimbal mount about at least two nonparallel axes. The system also may comprise a fan mounted to the first gimbal. The systems also may comprise operating the fan to drive airflow through a gap disposed between the first and second gimbals.

Abstract: A laser target seeker device arranged to receive a laser beam reflected from an object. Detector elements are arranged to detect the reflected laser beam. A processor is arranged to determine the received radiation on the respective detector element in order to determine the origin of the laser beam. A diffractor is arranged relative to the detector elements and configured to diffract the reflected laser beam into portions prior to being detected by the detector elements. The detector elements are arranged to detect the respective portion. A flyable body is for hitting a target by means of a laser beam. A system for hitting a target by means of a laser beam. A method for detecting a laser beam reflected from an object. Use of a kinoform member in a laser target seeker for diffracting a laser beam.

Abstract: There is provided an active protection system and an active protection method preferably for airborne platforms. According to the embodiment of the invention, the active protection system is mounted onboard a platform for protecting the platform, and comprises a radar system configured for generating output data including threat output data corresponding to a velocity, a range, and an angle of the threat with respect to the platform in an airspace around the platform, the output data being useful for detecting, identifying and tracking of at least one threat approaching the platform; a countermeasure system capable of launching at least one non-fragmentation interceptor projectile in response to receiving a control command; and a control unit configured for receiving the output data from the radar system and for generating the control command and transmitting the control command to the at least one non-fragmentation interceptor projectile, thereby enabling countering the threat.

Abstract: A method for obtaining a sky view of a battle site, comprising launching an interceptor (2) towards at least one detected flying threat (3); the interceptor (2) tracking the threat (3) using at least one remote sensor for achieving a kill of the threat (3) at a designated kill site (4) being at a large range from the at least one sensor; when the interceptor (2) approaches the kill site (4), releasing from the interceptor (2) at least one detachable vehicle (7) that includes at least one local sensor (8) for sensing the kill site (4) from a range considerably shorter than the large range and communicating the sensed data.

Abstract: A method, device, and projectile having a device for guiding or piloting projectiles or missiles (self-propelled or non-self-propelled), to deflect, in a direction Y, a hypervelocity projectile operating in a gas, such as a shell, a bullet, or a missile, having a nose, generally in the shape of a cone, with a more or less pointed tip, by generating a first high-voltage discharge able to produce a plasma over a first limited sector of the projectile surface and in direction Y, maintaining the plasma, and generating another low-voltage discharge able to supply the plasma with energy over a second limited sector of the projectile surface and in direction Y, the first and the second sectors being different and may overlap.

Abstract: Methods and apparatus according to various aspects of the present invention comprise a propelling system for propelling projectiles with variable velocity. In one embodiment, a cartridge comprises a cartridge case, the propelling system, and the projectile attached to the cartridge case.

Abstract: An aircraft 1 with a spiral inducing assembly 2 which is capable of inducing the aircraft to travel in a continuous spiraling motion without the aircraft rolling. A ramjet 6b is attached to a tube 3a that is able to rotate around the encircled part of the fuselage. The ramjet 6b is able to rotate in a pivoting manner on the rotate-able tube 3a with respect to the rotate-able tube 3a, thereby changing their pitch relative to the longitudinal axis of the rotate-able tube 3a. Ramjet 6b is rotated as is another ramjet on the right side of the tube 3a. The rotate-able tube 3a is rotated by means of an electric motor 3b rotating a wheel 3c. The difference in degree of rotation between the ramjets makes the ramjet 6b exert a greater force on the rotate-able tube 3a than the ramjet on the right side when the ramjets are rotated in the same direction. The imbalance between the rotational forces thus causes the rotate-able tube 3a to rotate.

Abstract: An aircraft 1 with a spiral inducing assembly 2 which is capable of inducing the aircraft to travel in a continuous spiraling motion without the aircraft rolling. A ramjet 6b is attached to a tube 3 that is able to rotate around the encircled part of the fuselage. The ramjet 6b is able to rotate in a pivoting manner on the rotate-able tube 3 with respect to the rotate-able tube 3, thereby changing their pitch relative to the longitudinal axis of the rotate-able tube 3. Ramjet 6b is rotated to a greater than another ramjet on the right side of the tube 3. The difference in degree of rotation between the ramjets makes the ramjet 6b exert a greater force on the rotate-able tube 3 than the ramjet on the right side when the ramjets are rotated in the same direction. The imbalance between the rotational forces thus causes the rotate-able tube 3 to rotate. When rotated, the ramjets would exert a lateral force on the rotate-able tube 3.

Abstract: An aircraft 1 with a spiral inducing assembly 2 which is capable of inducing the aircraft to travel in a continuous spiraling motion without the aircraft rolling. A ramjet 6b is attached to a tube 3a that is able to rotate around the encircled part of the fuselage. The ramjet 6b is able to rotate in a pivoting manner on the rotate-able tube 3a with respect to the rotate-able tube 3a, thereby changing their pitch relative to the longitudinal axis of the rotate-able tube 3a. Ramjet 6b is rotated as is another ramjet on the right side of the tube 3a. The rotate-able tube 3a is rotated by means of an electric motor 3b rotating a wheel 3c. The difference in degree of rotation between the ramjets makes the ramjet 6b exert a greater force on the rotate-able tube 3a than the ramjet on the right side when the ramjets are rotated in the same direction. The imbalance between the rotational forces thus causes the rotate-able tube 3a to rotate.

Abstract: A method for attacking dispersed targets from a single aircraft standing off at a significant distance from the target area, wherein pods of individually targeted UAVs are carried in lieu of a bomb on a conventional bomb rack.

Abstract: This disclosure involves aerial robots that dispenses conductive filament or systems, methods, and software for support such aerial robots. One remotely powered aerial robot system includes an aerial robot and a power source. The aerial robot comprises a body, a first propeller coupled to the body and operable to provide thrust to the aerial robot, a rotatable spool coupled to the body, and a conductive filament that is dispensed from the spool by rotation of the spool is one direction and retrieved by rotation of the spool in another direction. The power source is coupled with, and remote from, the aerial robot via the conductive filament, where the conductive filament is operable to power the first propeller using power from the power source.

Abstract: The present invention provides an unpowered low-cost “smart” micromunition unit for a weapon system for defense against an asymmetric attack upon ships and sea or land based facilities. A plurality of air dropped micromunition units are each capable of detecting and tracking a plurality of maneuvering targets and of establishing a fast acting local area wireless communication network among themselves to create a distributed database stored in each deployed micromunition unit for sharing target and micromunition unit data. Each micromunition unit autonomously applies stored algorithms to data from the distributed database to select a single target for intercept and to follow an intercept trajectory to the selected target. It is emphasized that this abstract is provided to comply with the rules requiring an abstract that will allow a searcher or other reader to quickly ascertain the subject matter of the technical disclosure.

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: An apparatus for vectoring the thrust of a motor that produces thrust along a longitudinal axis by expelling combustion gases through a nozzle may include a plurality of linearly-positionable non-rotatable thrust deflectors. The thrust deflectors may be disposed at around a perimeter of the nozzle. Each thrust deflector may be independently extended to simultaneously generate both a force transverse to the longitudinal axis and a torque about the longitudinal axis.

Abstract: A method is disclosed for controlling a flight trajectory of a spinning projectile. In one aspect the method may involve supporting a nose of the projectile in a manner permitting the nose to be wobbled. At least one electrically responsive component may be coupled at a first end to the nose and at a second end to a base portion of the projectile. An angular position of the nose of the projectile may be sensed as the projectile flies through an atmosphere after being fired from a weapon. An electrical signal is controllably applied to the electrically responsive component, in relation to the sensed angular position of the nose, to control an attitude of the nose during flight of the projectile.

Abstract: A guided missile has a sensor unit, a propulsion unit, and a payload unit. A missile casing forms the outer contour, extends along a longitudinal direction, and accommodates the sensor unit, the propulsion unit, and the payload unit. At least two of the units can be fitted alongside one another in the longitudinal direction. In comparison to conventional guided missiles, the guided missile is distinguished by increased modularity and thus by increased flexibility with regard to different operational scenarios.

Abstract: A system for the measurement of an angle of roll of a projectile is disclosed. The projectile has a casing with a rear end, a front end, and a side wall extending therebetween. The system includes a radar configured to transmit a polarized electromagnetic signal toward the projectile and a groove disposed on the side wall of the casing. The groove has a width, a depth, and a length, the width extending along a longitudinal axis of the projectile, the depth extending inwardly from an outer surface of the casing toward the longitudinal axis, and the length extending along the outside of the casing. The radar is further configured to receive a return signal from the projectile, wherein the return signal from the groove is modulated as a function of the angle of roll of the projectile. Amplitude or phase modulation of the return signal from the groove can be used to uniquely determine the roll angle of the projectile.

Abstract: A spin-stabilized correctible-trajectory artillery shell has a generator in the rotation-decoupled engagement region between a canard guidance unit and its munition body. The generator can be switched over to avoid load fluctuations between an adjusting motor and a substitute load. In order to avoid an additional heat source in the interior of the guidance unit the substitute load is in the form of an electrical resistance on, at or in canard surfaces behind the afflux flow edges. The canard surfaces are preferably formed on anti-spin canards which are not adjustably mounted.

Abstract: The invention relates to a method and device for producing an optical link using light flashes. According to the invention, an arrangement (13) comprising a plurality of capacitors (C1 to C5) is provided in order to power a flash lamp (3) and the connection of said capacitors within the arrangement is controlled in a programmed manner such that the resulting capacitance thereof increases from one flash in the next.

Abstract: The present invention relates to a strap down SAL seeker that includes an optical system having an engineered diffuser for transforming a laser spot into a uniform distribution of optical energy with a predetermined shape. The predetermined shape is preferably a square “top hat” or uniform scatter pattern. The SAL seeker further includes a silicon quad detector, having a focal plane defined by at least two axes. The detector is operatively associated with the engineered diffuser, and it generates signals indicative of the position of the optical energy with respect to the focal plane of the detector.

Abstract: One aspect of the invention relates to a laser ranging system. In this version of the invention, a guided missile is provided with laser that directs laser radiation in the general direction of a target that is subsequently reflected from the target back to the missile. A receiving lens is mounted on the missile that receives the reflected laser radiation. A ferrule containing optical fibers divided into a plurality of pixels that receive the reflected laser radiation from the receiving lens, wherein each pixel in the plurality of pixels is provided a different pointing angle by arranging the fibers within the pixel such that the centroid of the field of view of the fibers is different from the centroids of the field of views of the other fibers in the other pixels.

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 guidance method for a powered ballistic missile involves using an onboard computer to numerically simulate the flight path of the missile in real time, using a model with at least 3 degrees of freedom. The results of this simulation are used to update in real time an aim point and/or a predicted intercept point. An iterative process may be used in adjusting the aim point and/or the predicted intercept point. The process may be carried out until a specified number of steps have been completed, and/or until a specified heading error threshold of the aim point and a specified time of flight threshold have been achieved. The use of real time updating of an aim point of the missile advantageously takes into account variations in missile velocity and position due to individual variations in the rocket motor of the missile.

Abstract: The present invention comprises a device for determining the roll orientation of a body with respect to a local fixed coordinate system or a predetermined reference vector. The device uses a measurement of an external magnetic field, such as the Earth's magnetic field, to determine a roll orientation reference with respect to the field or an uncompensated roll orientation. The uncompensated roll orientation is then adjusted according to a bias angle, such as an angular difference between the external magnetic field and a local fixed coordinate system, to determine the roll orientation of the device with respect to the local fixed coordinate system or a compensated roll angle.

Abstract: A method for generating plans against ballistic missiles begins with the locations of regions from which missiles may be launched and identifies regions to be defended. The available sensor and engagement assets, their capabilities and possible locations are identified. At least some of the assets have sensor and engagement capabilities independent those of other assets. Initial potential plans are binary encoded, and applied to a genetic algorithm for producing a population of genetically modified solutions. These modified solutions are decoded and evaluated for fitness. The fitness evaluations are iteratively reapplied to the genetic algorithm to ultimately produce improved plans. The improved plans are decoded and finally evaluated for fitness and application. This process continues for a fixed number of iterations, at the end of which the best solution is presented as the plan best fit to achieve a valid defense against the BMD threats.

Abstract: Boresighting systems and methods are disclosed. In one embodiment, an assembly adapted for boresighting a launch system includes first and second elongated members adapted to be coupled to the launch system. First and second alignment members are coupled to and extend between the first and second elongated members and are adapted to position the elongated members in a substantially aligned, spaced-apart relationship. A mirror assembly is coupled to each elongated member, the mirror assemblies being adapted to provide an average angular position resulting in a single corrector value for the launch system. In a particular embodiment, each of the first and second elongated members is sized to simulate a Stinger missile.

Abstract: The multi-target tracking and discrimination system (MOST) fuses with and augments existing BMDS sensor systems. Integrated devices include early warning radars, X-band radars, Lidar, DSP, and MOST which coordinates all the data received from all sources through a command center and deploys the GBI for successful interception of an object detected anywhere in space, for example, warheads. The MOST system integrates the optics for rapid detection and with the optical sensor array delivers high-speed, high accuracy positional information to radar systems and also identifies decoys. MOST incorporates space situational awareness, aero-optics, adaptive optics, and Lidar technologies. The components include telescopes or other optical systems, focal plane arrays including high-speed wavefront sensors or other focal plane detector arrays, wavefront sensor technology developed to mitigate aero-optic effects, distributed network of optical sensors, high-accuracy positional metrics, data fusion, and tracking mounts.

Abstract: An optical element mount is effective in high G environments to protect brittle optical elements in which tensile stresses are generated on surface S2 without degrading optical performance. A flexible spacer formed of a relatively low-stiffness material supports an optical element having a tapered outer periphery in an optical seat having a complementary tapered surface. When the optical assembly is exposed to the high G environment, the inertial loading drives the optical element in the aft direction into the flexible spacer and seat. This puts the optical element into a plate bending condition thereby inducing tensile stress on S2 which is at least partially offset by a compressive stress caused by the reaction force normal to the tapered interface. The stresses, both compressive and tensile, placed on the optical element in the high G environment can be very large.

Abstract: A method for varying the flight path of a missile, in particular of a spin-stabilized projectile, which has an outer wall and which is provided with at least one impulse device. The impulse device can be activated deliberately at a defined time during the flight of the missile. The impulse device is arranged with respect to the longitudinal axis of the missile such that, when it is activated, it generates an impulse that initiates a tumbling movement which causes the flight-path of the missile to be shortened or varied. A spin-stabilized projectile is provided with such an impulse device and it is configured so that the impulse device may be triggered during flight so as to initiate the flight-altering tumbling movement.

Abstract: A hollow cylinder has an electromagnet to hold back a canister and either an induction heating linear actuator or a firing pin to ignite the primer-containing combustive material inside the canister to eject a locked piston from the cylinder. There is a motor-included turbogenerator around the cylinder, which converts the energy of the post-combustion gases into electricity to get stored and to power an integrated or separate annular stator assembly to give the ejected piston a rotatory motion for stability in projectile motion. Another device has a helically arranged, multi-pole permanent magnet assembly annularly integrated around the cylinder to give the ejected piston a rotatory motion for stability in projectile motion. In other forms, an annular stator assembly around the cylinder is supplied with switched, externally generated electric power without either a turbogenerator or the motor-included turbogenerator to respectively produce electricity or to provide gyroscopic stability to the cylinder.

Abstract: Methods and apparatus for a guidance system according to various aspects of the present invention comprise include an energy concentrator configured to transmit an energy entering the entrance through the exit if the energy enters the entrance within a predetermined acceptance angle, and reject the energy entering the entrance if the energy enters the entrance outside the predetermined acceptance angle. The system may further comprise a detector coupled to the exit of the energy concentrator and configured to generate signals corresponding to a location of the transmitted energy incident upon the detector.

Abstract: There is provided a guidance system for allowing an air vehicle to guide a moving object, comprising a Synthetic Aperture Radar located on the air vehicle, and a means of communication for allowing the air vehicle to communicate with the moving object, wherein the Synthetic Aperture Radar is capable of determining the position and orientation of the air vehicle relative to a desired location, and information provided by the Synthetic Aperture Radar is used, via the means of communication, to guide the moving object towards the desired location. A guidance system wherein a seeker is utilised on the moving object is also provided.

Abstract: An optically guided mortar comprising a three axis canard assembly, an optical seeker, a guidance and control processor, and a fuze mechanism. The optical seeker is a direct replacement for existing standard mortar fuzes. The resulting system significantly improves current mortar circular error probability (CEP) and results in overall reduction of cost of target prosecution, reduction in collateral damage, improved crew survivability, and adds compatibility against limited non-stationary targets. The optical seeker detects an optical illuminator located at a target and supplies signals to the guidance and control processor which through a guidance algorithm supplies steering commands to drive motors of the three axis canard assembly which move a plurality of guidance canards to accurately direct the munition toward a target.

Abstract: Methods and apparatus for guidance systems according to various aspects of the present invention operate in conjunction with a projectile including a guidance system having a guidance controller, a detector, and an optical system. The guidance controller controls the path of the projectile according to signals from the detector. The detector generates signals according to an angle of incident energy. The optical system transfers the energy to the detector via a spreader and a condenser. The spreader spreads the incident energy, and the condenser converges the spread energy onto the detector.