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: Dual mode SAL/IR imaging seekers are described herein. In some embodiments, a dual-mode SAL/IR imaging seeker described herein includes a focal plane array (FPA), an objective optical assembly providing a common optical path to the FPA for incident laser radiation of a first wavelength band and incident ambient radiation of a second wavelength band non-overlapping with the first wavelength band, a first optical filter operable to selectively pass the incident laser radiation to the FPA in a transmissive mode and selectively block the incident laser radiation from the FPA in a non-transmissive mode and a second optical filter assembly operable to selectively pass the incident ambient radiation to the FPA in a transmissive mode and selectively block the incident ambient radiation from the FPA in a non-transmissive mode.

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: An optical device for a missile seeker head includes an optical sensor with a plurality of pixels, a light source, a detection device, and an optical system. The light source is configured to illuminate, using the optical system, an object that can be mapped using the optical system on at least one subarea of a predefined pixel of the optical sensor. The detection device is configured to detect the light emitted from the light source and reflected by the object.

Abstract: Control surfaces secured tangentially to a round projectile, such that the lift force generated by the control surfaces is generated through the projectiles centerline. This eliminates the need for an opposing fin to counter roll moment. Sizing the control surfaces to form an equilateral triangle gives each panel equal span, and enables the force generated by two panels to be equal and opposite to that of the opposing panel. The end effect is that each panel only has two active states (neutral and positive deflection). Thus, a solenoid and a return spring may be used to control the canards. Additionally, the control panels may fold along the surface of the projectile, which frees up internal volume and minimizes the length of the control section.

Abstract: Embodiments of a multi-mode seeker are provided for use in conjunction with a predetermined laser designator. In one embodiment, the multi-mode seeker includes a focal plane array and a bi-modal processing system. The focal plane array includes a detector array and a Read-Out Integrated Circuit (ROIC) operatively coupled to the detector array. The bi-modal processing system is operatively coupled to ROIC and is switchable between: (i) an imaging mode wherein the bi-modal processing system generates video data as a function of signals received from ROIC indicative of irradiance across the detector array, and (ii) a semi-active laser guidance mode wherein the bi-modal processing system generates line-of-sight data as a function of signals received from ROIC indicative of laser pulses detected by the detector array and qualified as corresponding to the predetermined laser designator.

Abstract: The present invention includes, in various aspects and embodiments, a method and apparatus for guiding a laser guided munition to an offset aim point relative to the laser spot. In one aspect, the laser guided munition comprises a propelled explosive ordnance; an optical sensor; means for indicating an offset from a laser designation; and a flight control system. The flight control system is responsive to an output from the optical sensor to: home on the laser designation during the descent of an arcing trajectory for the propelled explosive ordnance; determine that the propelled explosive ordnance traversed a predetermined point in the descending trajectory; and upon traversing the predetermined point, guide the propelled explosive ordnance to the position defined by the offset indicator. In a second aspect, the laser guided munition is deployed as part of a system that also includes a laser designator.

Abstract: A munition guidance system is disclosed. The system comprises a generally tubular enclosure, having an internal cavity adapted for receiving a munition, wherein an outer diameter of the enclosure is at most the largest outer diameter of the munition; and a processing and control unit enclosed within the enclosure and being configured for controlling guidance wings so as to maneuver the munition while flying.

Abstract: Embodiments of a propulsion and maneuvering system that may be suitable for use during a terminal phase in an interceptor are generally described herein. The propulsion and maneuvering system may include one or more axial thrusters to provide thrust along axial thrust lines that run through a center-of-gravity of the interceptor and a plurality of divert thrusters to provide thrust in radial directions. The combination of divert and axial thrusters may allow the interceptor to respond to a maneuvering target and may allow the interceptor to increase its velocity along a line-of-sight (LOS) to a target to change target impact/engagement time.

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: 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 seeker configured to guide the weapon to a target. The seeker includes a detector configured to receive a distorted signal impinging on an objective lens from the target, memory configured to store target criteria and a correction map, and a processor configured to provide a correction signal based on the distorted signal, the target criteria and the correction map to guide the weapon to the target.

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: 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: The invention concerns a device for countering and tracking a threat in the form of a homing-head missile, comprising a homing head adapted to receive an incident coherent light beam and to deflect same to produce a transmitted beam. The invention is characterized in that the homing head comprises a biprism including two prisms made of different materials and adapted to divide the transmitted beam into two sub-beams, the refractive index difference between the prisms being adapted to introduce an optical path difference between the two sub-beams which is greater than the coherence length of the incident beam.

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: A shield for use with a detector includes a first opening adjacent the detector, a second opening opposite the first opening along an optical axis intersecting the detector, and a field of view defined by the detector and the second opening. A shield body includes alternating curved profile regions and linear profile regions coaxially aligned along the optical axis. The curved profile regions have respective curved interior surfaces concave facing toward the second opening, and the linear profile regions have respective interior surfaces facing toward the first opening. In this way, specular reflections associated with stray light may be greatly reduced.

Abstract: An unmanned aerial vehicle including a controller operating in a search mode of operation where a receiver of an acquisition sensor searches for a target and causes flight control surfaces to guide the vehicle in a downward spiral path, a terminal mode of operation where the acquisition sensor detects a target and causes flight control surfaces to direct the vehicle toward the target, and an activation mode of operation where a trigger sensor detects a target within a predetermined distance to the vehicle and the controller activates a responder.

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 reflector 38 includes a mirrored surface 48 and a frequency selective surface 46. The frequency selective surface 46 is arranged to reflect radiation of a first frequency band 52 and allow radiation of a second frequency band 50 to pass. The mirrored surface 48 is arranged to reflect radiation of the second frequency band 50. In this manner, the focal power for radiation of the first frequency band 52 is independent to the focal power for radiation of the second frequency band 50. Accordingly, the design of optical components associated with the second frequency band 50 can be undertaken independently of those associated with the first frequency band 52 so as to achieve the optimised focusing for each frequency band.

Abstract: A miniature lightweight high-maneuverability missile (10) has a missile body (12) with three sets of at least two aerodynamic control surfaces (14, 16, 18) for independent control of roll, pitch and yaw of the missile. Each set of control surfaces (14, 16, 18) is independently controlled by a corresponding actuator (20) deployed within the missile body (12). Other preferred features include selection of an elevation angle of incidence at a target, and switching between explosive and kinetic modes of operation.

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: A laser communication and spatial referencing system and related methods provides effective and secure non-line-of-sight communications. A laser communication and spatial referencing system includes a laser transmitter transmitting a pulsed laser beam encoded with binary communications data, and an imaging data receiver for receiving the pulsed laser beam reflecting off a reflective target. The imaging receiver decodes the binary communications data and determines the position of the laser beam. The laser communication and spatial referencing system may operate synchronously and/or asynchronously, and may include a display displaying a video image of area surrounding the target with the reflecting location superimposed on the image to provide visual identification of the target.

Abstract: This invention advances the related state-of-the-art by eliminating the physical EO window used by electro-optical imaging infrared seekers for tactical missiles and high-altitude endo-atmospheric interceptors, widely employed in integrated defense systems. This invention increases the probability of intercepting exo-atmospheric ballistic warheads by exo-atmospheric interceptors, and eliminates the existing altitude “gap” of interception, as well as the geographical limitations posed by the mesospheric Noctilucent Clouds. The problem of protecting an imaging EO sensor from aeroheating is solved in this invention by a special purpose device which is enabled immediately after the nose cone ejection event.

Abstract: A system is disclosed to identify authorized EO devices and unauthorized EO devices within a scene. The system hampers the operation of the unauthorized EO devices detected within the scene.

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: 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: An active vortex control system (AVOCS) includes a set of primary injectors that inject gas into a cavity to generate a vortex in front of and possibly around components inside the cavity. The vortex interferes with an external flow field in an opening to the cavity to protect the components from the external environment. Sets of secondary injectors may inject gas at a reduced mass flow into the cavity to compensate for energy losses to maintain the coherence of the vortex. The AVOCS is well suited for use in windowless endo- and exo-atmospheric interceptors to protect the electro-optical imagers and optical components from Earth atmosphere.

Abstract: A SAR image recorded by a reconnaissance system is transferred as a reference edge image together with the data of the trajectory as a reference. The signal of the infrared seeker head of the missile is converted into a virtual SAR edge image and compared to the SAR reference image to calculate the precise position of the missile.

Abstract: A semi-active laser (SAL) sensing system is thus provided that uses a lens concentrator system to pass received reflected laser light from an aperture to a detector. The lens concentrator system facilitates the use of SAL systems with different laser designator wavelengths to improve the performance of the SAL system. In one embodiment, the lens concentrator system is formed from polymer having substantial optical clarity for radiation having wavelengths between approximately 1.5 and approximately 1.65 ?m. For example, the lens concentrator system may be formed from amorphous fluoropolymer. The lens concentrator system formed from amorphous fluoropolymer facilitates the use SAL designators using different wavelengths than those in past SAL sensing systems.

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 6-axis position and attitude of an imaging vehicle's detector assembly is measured by mounting the detector assembly on a compliant isolator and separating the main 6-axis IMU on the vehicle from a secondary IMU comprising at least inertial rate sensors for pitch and yaw on the detector assembly. The compliant isolator couples low-frequency rigid body motion of the vehicle below a resonant frequency to the isolated detector assembly while isolating the detector assembly from high-frequency attitude noise above the resonant frequency. A computer processes measurements of the 6-axis rigid body motion and the angular rate of change in yaw and pitch of the isolated detector assembly to mitigate the drift and noise error effects of the secondary inertial rate sensors and estimate the 6-axis position and attitude of the detector assembly.

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 seeker configured to guide the weapon to a target. The seeker includes a detector configured to receive a distorted signal impinging on an objective lens from the target, memory configured to store target criteria and a correction map, and a processor configured to provide a correction signal based on the distorted signal, the target criteria and the correction map to guide the weapon to the target.

Abstract: A jitter sensing mechanism for a gimbaled optical sensor system. In one example, the jitter sensing mechanism includes a faceted retro-mirror configured to allow a double-pass line-of-sight monitoring beam to sense line-of-sight jitter in a multi-axis gimbaled optical sensor system where the inner-most gimbal axis includes a 2:1 gain mirror.

Abstract: A passive guidance system including a viewpoint capture system (VCS) including a first processor in communication with first memory and a first SWIR imager for creating a viewpoint image database having a plurality of images, at least one of the images having a target point. A weapon guidance module is in communication with the VCS and coupled to a weapon. The weapon guidance module includes a second processor in communication with second memory and a second SWIR imager for storing the viewpoint image database and correlating in-flight images from the second SWIR imager to provide guidance commands directing the weapon to the target point.

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: A system and method of reducing turbulence sensitivity in a laser spot detector. Embodiments may include using beam splitters, reflectors, and beam deviators. The reflectors may be trihedral reflectors and the beam deviators may be segmented wedge plates having predetermined physical angles and angle directions in each wedge segment designed to produce opposing blurs for each segment of the aperture. A predetermined blur introduced into each line of sight eliminates the need for de-focus, thereby mitigating effects such as centroid shift caused by turbulence or dirty/damaged sensor apertures.

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.

Abstract: A dual-mode sensor uses the active guidance radiation as a “guide star” to generate a wavefront error estimate for the primary optical element in-situ without interfering with the generation of either the active guidance or passive imaging guidance signals. An array of optical focusing elements performs the normal function of spatially encoding an angle of incidence of the active guidance radiation at an entrance pupil onto an active imaging detector. The array also performs an additional function of spatially encoding wavefront tilt deviations emanating from sub-pupils of an exit pupil onto the active imaging detector. A processor processes the electrical signals from the imaging detector in accordance with the respective spatial encodings to generate an active guidance signal and the wavefront error estimate for the primary optical element.

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: In the field of steered munitions intended to destroy a target after at least one flight phase followed by a target approach phase, a munition comprises a munition body of cylindrical shape of longitudinal axis having, on the same side as a front end of the munition which is the end intended to be directed toward the target, a front body comprising an optic of a guidance device that guides said munition toward the target, a cap for protecting the optic, secured to the munition body, characterized in that the protective cap comprises at least one recess having a pyrotechnic device intended to destroy said protective cap so as to free the optic and make the munition guidance device operational during the target approach phase. Application: steered or guided munitions such as those of the rocket or projectile type, or missiles.

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 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: 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: In a CLOS missile guidance system, target and missile tracking data e.g. video image data are acquired on a UAV and transmitted to the missile where they are processed to provide guidance control data to the missile. Alternatively the video image data may be transmitted to a command station where the guidance control data is generated and transmitted to the missile, preferably via the UAV.

Abstract: Embodiments of a guided munition are provided, as are embodiments of a method for equipping a guided munition with a self-deploying dome cover. In one embodiment, the guided munition includes a munition body, a seeker dome coupled to the munition body, and a self-deploying dome cover disposed over the seeker dome. The self-deploying dome cover is configured to deploy and expose the seeker dome during munition flight in response to aerodynamic forces acting on the self-deploying dome cover.

Abstract: An optically guided munition and control system has a replacement fuse assembly mounted on the front of a munition body or shell casing. An optical seeker subsystem detects an illuminated target and supplies signals to a processor. The processor develops steering commands sent to a flight control subsystem having a plurality of guidance canards which are actuated by drive motors through gear assemblies. The roll of the munition is established and left/right and up/down steering commands are sent to the canard drive motors based upon the optical seeker subsystem detection of the target illuminator. Range adjustment is based upon bore sight lockdown angle and cross range control is based upon left/right centering error. A code is contained in the optical radiation received from the illuminated target which must be validated by a preset code in the system processor to arm the munition.

Abstract: Embodiments of a guided munition system are provided, as are embodiments of a combustive dome cover and methods for equipping a guided munition with a combustive dome cover. In one embodiment, the guided munition system includes a guided munition, which has a munition body and a seeker dome coupled thereto, and a combustive dome cover disposed over the seeker dome. The combustive dome cover is configured to uncover the seeker dome at a predetermined time of deployment and to combust when so deployed to minimize the production of debris.

Abstract: A one-piece extended dome having a spanning angle greater than 180 degrees. The dome is integrally formed of a Nano/Nano class Nanocomposite Optical Ceramic (NNOC) material. The extended dome comprises seamless first and second non-complementary geometric shapes, such as a first spherical geometry and a second conical or ogive geometry. The Nano/Nano class NNOC material comprises two or more different chemical phases (nanograins) dispersed in one another, each type having a sub-micron grain dimension in at least the direction of light transmission. The material is a true NNOC material in that all of the constituent elements have sub-micron grain dimensions, there is no host matrix.