Abstract: An optical system for use in an Earth-orbiting satellite includes a plurality of image sensors disposed on a focal plane having a reference axis orthogonal thereto, optics configured to focus incident light onto the image sensors, a piezoelectric actuator coupled to the image sensors and configured to translate the image sensors in at least two axes each orthogonal to the reference axis, and at least one controller operably coupled to the plurality of image sensors and the piezoelectric actuator. The image sensors are configured to generate at least one image frame from light detected by the plurality of image sensors, the image frame including a target star and at least one guide star. The controller is configured to stabilize the position of the target star by adjusting the position of the piezoelectric actuator based on the changes in the position of the guide star.

Abstract: A method of tracking a target comprising causing alteration to the target using a laser, recording an electromagnetic signature of the target after the causing alteration step, and tracking the target using the electromagnetic signature.

Abstract: A plate solving methodology determines celestial coordinates of an image. Star locations are extracted from the image in terms of pixel coordinates. A group of four stars, referred to as a “test quad”, is identified. A signature for the test quad is generated. In one embodiment, this test signature is derived by determining the separations of the four stars in the test quad, normalized by the largest separation. In one embodiment, the signature also includes the sum of these normalized separations. A query is performed, using the generated signature, against a database of reference signatures for known groups of stars (referred to as “reference quads”). A geometric transform is determined, establishing the relationship between the test quad and a reference quad that matches within a specified tolerance. This geometric transform defines the celestial coordinates of the image. Additional verification steps can be performed to confirm the accuracy of the match.

Abstract: A high-energy beam is precompensated by a process including receiving a high-energy beam from a source and energy from a target. The target energy includes wavefront aberrations related to atmospheric and other external disturbances encountered along a distance separating the target. A correction signal is determined responsive to the high-energy beam and the target energy. The correction signal is also configured to pre-compensate for wavefront aberrations related to the atmospheric and other external disturbances and to cancel aberrations introduced by the adaptive optics techniques. A wavefront of the outcoupled high-energy beam is adjusted responsive to the determined correction signal. A beam control system includes three adaptive optics servo loops and an aperture-sharing element.

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

Abstract: A method and system for at least three dimensional imaging comprising a processor for processing information; at least one photon light source generating a beam of light; a modulator for modulating the light of the at least one photon light source; a plurality of first receivers operative to detect the influence of a subject on the beam; the plurality of first receivers being operatively connected to the processor and operating to transmit nonspatial information to the processor; the plurality of first receivers being spaced at known, different distances from the subject, whereby comparison of each of the outputs of the plurality of first receivers provides three dimensional information concerning the subject; the processor operating to correlate the outputs of the plurality of first receivers with spatial information derived from the modulated light at correlating intervals of time to create a three dimensional image of the subject.

Abstract: A LIDAR system that includes a streak image sensor having multiple sensor elements for receiving optical return signals from portions of a spatial region within their respective instantaneous fields of view is operated by periodically sampling and storing electrical signals generated by the sensor elements respectively, and initiating the periodic sampling of the electrical signals of each sensor individually and independently by reference to a feature of that sensor's electrical signal that represents a boundary between materials with different optical properties.

Abstract: An optical apparatus and method for measuring the attitude of an object in outer space includes an optical system having an aperture to receive optical radiation and a focal plane to image the optical radiation and an aperture-sharing element attached to the optical element and at least partially surrounding an optical path into the aperture. The aperture-sharing element directs optical radiation from a field of view of the aperture-sharing element to a corresponding first portion of the focal plane to provide multi-axis stellar attitude measurements, and the aperture receives optical radiation along the optical path into the aperture and directs the optical radiation to a second portion of the focal plane.

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

Abstract: Systems and methods for imaging a distant light source at an enhanced resolution is provided. An evanescent field generator an evanescent field generator that receives an incident electromagnetic field representing at least one distant light source and restores high spatial frequency components to the incident electromagnetic field, resulting in an evanescent field. A negative refractive index lens assembly focuses the evanescent field onto a focal plane. A photodetector assembly located in the focal plane detects the focused evanescent field as an image of the at least one distant light source.

Abstract: Detection sensors utilizing linear arrays using one or more linear arrays of detectors sampled at a high rate. The invention is useful for target detection including hydrocarbon events such as guns, mortars, RPG missiles and artillery firings, lightning, and other optical events.

Abstract: Multiple observations using a reconfigurable space-based telescope are performed by independently targeting one or more sensor units, within a field of view, relative to a main body of the space-based telescope. The sensor units are capable of simultaneously obtaining an image of one or more targets, respectively. At least one of the sensor units is independently retargetable relative to the main body of the space-based telescope to obtain an image of at least one other target. Further, the sensor units are independently maneuverable in formation relative to the main body of the space-based telescope to obtain various lines of sight without changing an optical axis of the main body of the space-based telescope.

Abstract: The present invention relates to an absolute target system intended to be incorporated in observation satellites. To establish an absolute target system provided with maximum accuracy, the present invention proposes coupling a star sensor (4) to an optical metrological system (5N, 5R). Since these two items of equipment are normally already on board the satellites, in particular for formation flight missions, this solution adds no extra weight or cost.

Abstract: A optical instrument (e.g., coronagraph) is described herein that has a pick-off mirror with a surface having an array of reflective structures (reflective occulting mask) machined therein which enables an optical image of one or more low intensity objects (e.g., planets) to be obtained when the low intensity object(s) are located in close proximity to a high intensity object (e.g., sun). Also described herein, is a method for manufacturing the pick-off mirror which has a surface with an array of reflective structures (reflective occulting mask) that are machined therein.

Abstract: A system and method for protection of aircraft against surface-to-air missiles deploys sensors to provide coverage around an airport The use of a fixed (or slow moving) set of sensors around the airport allows detection of missile threats to all aircraft using the airport without requiring each individual aircraft to be provided with a threat detection system. Information about a detected threat is then typically transmitted in real time directly to the aircraft under threat to allow timely deployment of aircraft-based countermeasures. The detection system and method preferably employ spaced-apart sensors with overlapping fields of view to provide enhanced tracking through triangulation and reduced false alarm rates by redundancy of information. Airborne systems with overlapping coverage may be also used.

Abstract: A position of a feature in a scene is located by forming an image of the feature using a segmented array having a plurality of array subelements. Each of the array subelements has an output signal. The output signals from at least two spatially adjacent array subelements are cooperatively analyzed to establish a data set reflective of an extent to which output signals responsive to the image of the feature are produced from exactly one or from more than one of the adjacent array subelements. The data set is used to reach a conclusion as to a location of the image of the feature on the segmented array. Increased positional accuracy is attained with no loss of sensitivity.

Abstract: A distributed ground sensor threat detection system, which is an automated missile warning system designed to provide reliable, timely and accurate missile location information of shoulder-launched SAMs within the volume under surveillance by a network of sensors. Remote sensor nodes position in proximity to an airport runway monitor the area between the nodes to locate threat missiles. Detection information from each remote sensor node is sent to a central processing node which processes the information to determine if a threat missile is launched against a commercial aircraft.

Abstract: A distributed ground sensor threat detection system, which is an automated missile warning system designed to provide reliable, timely and accurate missile location information of shoulder-launched SAMs within the volume under surveillance by a network of sensors. Remote sensor nodes position in proximity to an airport runway monitor the area between the nodes to locate threat missiles. Detection information from each remote sensor node is sent to a central processing node which processes the information to determine if a threat missile is launched against a commercial aircraft.

Abstract: A computer-readable medium having computer-executable instructions for performing a method. The method includes determining the transformation of an origin of an imaging device positioned in a vehicle and implementing exponentially stabilizing control laws based on the determined transformation and a distance to an imaged target. The method also includes generating a rotation output from the exponentially stabilizing control laws, generating a zoom output from the exponentially stabilizing control laws, determining a system latency in redirecting an optical axis and modifying a lens system along the optical axis, and determining the transformation of the origin of the imaging device with respect to global coordinates. A centroid of the target image is maintained within a selected distance from the origin of the imaging device. The apparent distance between the imaged target and the imaging device is also maintained.

Abstract: The present invention relates to an absolute target system intended to be incorporated in observation satellites. To establish an absolute target system provided with maximum accuracy, the present invention proposes coupling a star sensor (4) to an optical metrological system (5N, 5R). Since these two items of equipment are normally already on board the satellites, in particular for formation flight missions, this solution adds no extra weight or cost.

Abstract: Apparatus for determining a direction of low power radiation originating from at least one source, the radiation arriving essentially collimated, the apparatus including an opening, at least two radiation sensors, a respective integrator for each radiation sensor, an integration enabler, a threat detector, and a processor, each integrator being coupled with a respective radiation sensor, the integration enabler being coupled with each integrator, the threat detector being coupled with the integration enabler, and the processor being coupled with the integrators and the threat detector, wherein the opening receives incoming radiation, the radiation sensors being located at different spatial locations behind the opening, each radiation sensor detecting at least a respective portion of the incoming radiation received from the opening and converting the respective portion of the incoming radiation into a respective electric signal, each integrator integrating the respective electric signal, wherein the threat det

Abstract: A method and device produce an optical link with laser pulses between an emitter of the pulses and a receiver of the pulses. The optical link is used by a locating device for locating a body moving at constant speed away from the locating device. The locating device delays the start of emission of the laser pulses with respect to the departure of the moving body and varies the energy of the successive laser pulses in proportion to the square of the time elapsed since the start of emission of the pulses.

Abstract: A computer-readable medium having computer-executable instructions for performing a method. The method includes determining the transformation of an origin of an imaging device positioned in a vehicle and implementing exponentially stabilizing control laws based on the determined transformation and a distance to an imaged target. The method also includes generating a rotation output from the exponentially stabilizing control laws, generating a zoom output from the exponentially stabilizing control laws, determining a system latency in redirecting an optical axis and modifying a lens system along the optical axis, and determining the transformation of the origin of the imaging device with respect to global coordinates. A centroid of the target image is maintained within a selected distance from the origin of the imaging device. The apparent distance between the imaged target and the imaging device is also maintained.

Abstract: A method to dynamically stabilize a target image formed on an image plane of an imaging device located in a moving vehicle. The method includes setting an origin in the image plane of the imaging device at an intersection of a first axis, a second axis and a third axis, imaging a target so that an image centroid of the target image is at the origin of the image plane, monitoring sensor data indicative of a motion of the vehicle, and generating pan and tilt output to stabilize the image centroid at the origin in the image plane to compensate for vehicle motion and target motion. The pan and tilt output are generated by implementing exponentially stabilizing control laws. The implementation of the exponentially stabilizing control laws is based at least in part on the sensor data.

Abstract: An optical system including a telescope and a principal pointing device for selecting a direction of observation is disclosed. The system furthermore includes at least one secondary pointing device arranged ahead of a part of the entrance of the telescope and oriented fixedly with respect to the principal pointing device. A set of photodetectors records a secondary image formed by the telescope from light rays directed by the secondary pointing device toward the entrance of the telescope The secondary image makes it possible to accurately determine the direction of observation.

Abstract: The invention relates to a detection device, comprising a parabolic mirror (1) and several radiation detectors (2-5). The detectors are placed in the focal plane (O, X?-X, Y?-Y) of the mirror with respective spacings in a common fixed direction (Y?-Y). The detection device further comprises a selector system, connected to each of the detectors (2-5), embodied to successively select each of the detectors and to transmit a received signal from the selected detector. The separations of the detectors (d2-d5) are selected such that a gain diagram, for the reception of said device, has a gain minimum, between two successive gain maxima, each corresponding respectively to one of the detectors, of less than 3.0 dB less than said gain maxima. Such a device permits a sweeping of a zone with several adjacent sub-sweeps from a machine overflying said zone.

Abstract: Embodiments of the present disclosure include self-aligning telescope control systems and self-alignment methods. In an embodiment, a telescope control system orients a telescope with respect to the celestial sphere by pointing the telescope in the direction of an alignment star or alignment area of the sky. The telescope control system images a field of view in the alignment area, and processes the images to determine the celestial coordinates of a center of the filed a field of view the alignment area. The telescope control system then maps the telescope's coordinate system to the celestial coordinate system. Once mapped, the telescope control system can advantageously slew the telescope to any desired celestial object in the viewable sky based on, for example, user selection, system recommendations, combinations of the same, or the like.

Abstract: A single, hard-mounted set of optics is utilized to replace a two field-of-view system for directed countermeasures. It includes within one continuous but distorted field of view the capability to detect, acquire and characterize targets at the edge of the field while precisely tracking with high target fidelity at the field center. With multiple targets, both tracking of a primary target and acquisition of a secondary target can occur simultaneously, greatly improving countermeasure effectiveness.

Abstract: The invention provides a method and apparatus for correcting for gain changes in detectors in a guided vehicle. In one version of the invention, an on board light source is used to generate a reference set of detector gains, which are stored in computer memory. The on board light source is then pulsed at subsequent times and the signals generated by the detectors are compared to the reference set of detector gains to determine whether any gains have changed.

Abstract: A plurality of optical sensing elements in an array where each element has a unique element address identifying the element location. Each element senses light and produces an element address signal in proportion to the intensity of the light sensed by the element. The element address signal corresponding to the highest intensity sensed by the array is asserted as an array output signal.

Abstract: A ground based launch detection system consisting of a sensor grid of electro-optical sensors for detecting the launch of a threat missile which targets commercial aircraft in proximity to a commercial airport or airfield. The electro-optical sensors are configured in a wireless network which broadcast threat lines to neighboring sensors with overlapping field of views. When a threat missile is verified, threat data is sent to a centrally located processing facility which determines which aircraft in the vicinity are targets and send a dispense countermeasure signal to the aircraft.

Abstract: A method of determining the attitude of a spacecraft is provided. The method may include sensing the projections of a plurality of stars on a sensor, converting the projections into sensor-star directions, and determining the angular values of the spacecraft relative to the stars. The method uses equations to introduce focal length errors into the equations which convert the projections into star-sensor directions, thereby reducing the uncertainty introduced by incomplete knowledge of the errors on the results of the attitude angles of the spacecraft.

Abstract: An optical arrangement (2) for a homing head (16), for the purpose of imaging an object scene onto a detector unit (4), including a control unit (24), a first optical unit (10) having two at least partially transparent optical elements, in particular prisms (42, 44), a second optical unit (14) and a beam deflecting unit (18), the first optical unit (10) directing radiation from at least two sections of the object scene onto the beam deflecting unit (18) in a superimposed fashion, and the beam deflecting unit (18) selecting one of the sections and, in conjunction with the second optical unit (14), imaging the selected section on the detector unit (4).

Abstract: A ground based launch detection system consisting of a sensor grid of electro-optical sensors for detecting the launch of a threat missile which targets commercial aircraft in proximity to a commercial airport or airfield. The electro-optical sensors are configured in a wireless network which broadcast threat lines to neighboring sensors with overlapping field of views. When a threat missile is verified, threat data is sent to a centrally located processing facility which determines which aircraft in the vicinity are targets and send a dispense countermeasure signal to the aircraft.

Abstract: A system and method are provided for controlling an optical imaging system capable of providing an image of a target. The system includes a reflector, an optical amplifier and a tracking device. The reflector is capable of reflecting light representative of the image provided by the optical imaging system. In addition, the reflector is capable of being adjusted in at least one direction based upon movement of the image provided by the optical imaging system. The optical amplifier is capable of amplifying an intensity of the light reflected by the reflector with a variable gain based upon the intensity of the reflected light. And the tracking device is capable of receiving the light from the optical amplifier. As such, the reflector can be driven to a position in at least one direction based upon an image of the target represented by the light received by the tracking device.

Abstract: A spatial information detecting apparatus using an intensity-modulated light has a photoelectric converter for receiving a light provided from a space, into which a light intensity-modulated by a predetermined modulation signal is being irradiated, and generating amounts of electric charges corresponding to an intensity of received light; charge discarding portion having an electrode for removing dispensable charges from the electric charges generated by the photoelectric converter according to a voltage applied to the electrode; charge storage portion for storing signal charges from the electric charges generated by the photoelectric converter; control circuit for controlling the voltage applied to the electrode at a timing synchronized with a period of the modulation signal to change a ratio of the signal charges stored in the charge storage portion to the electric charges generated by the photoelectric converter; charge ejector for outputting the signal charges from the charge storage portion; and an analy

Abstract: An improvement in a semi-active laser last pulse logic missile seeker is disclosed and claimed. In one embodiment, the improvement includes a first polarizer disposed in the detection field of view of the PIN photodiode detector and a second polarizer disposed in the detection field of view of the staring imaging infrared focal plane array. Each of the first and second polarizers has an identically configured plurality of segments. Each segment allows transmission of a different polarization than other segments and is sized to completely cover the fields of view of both the PIN photodiode detector and the staring imaging infrared focal plane array. First and second actuators are connected to the first and second polarizers, respectively, to synchronously and simultaneously step identical and corresponding segments in a plurality of discrete steps within the fields of view in response to incoming temporal and spatial laser returns.

Abstract: A system and method for focusing electromagnetic energy on a moving target. Generally, the inventive system sends a pilot beam to a target and analyzes a return wavefront to ascertain data with respect to any distortions and other phase and/or amplitude information in the wavefront. This information is then used to pre-distort an output beam by so that it is focused on the target by the intervening distortions. In an illustrative embodiment, the pilot beam is provided by a beacon laser mounted off-axis with respect to the output beam. The reflected wavefront is received through a gimbaled telescope. Energy received by the telescope is detected and processed to ascertain wavefront aberrations therein. This data is used to predistort a deformable mirror to create an output beam which is the phase conjugate of the received wavefront. In a first alternative embodiment, a nonlinear optical phase-conjugate mirror is employed to generate the required wavefront-reversed replica of the received wavefront.

Abstract: A system for tracking a projectile utilizing a laser beam modulated by an acousto-optic cell. Transponders distributed on hemispheres around the rear of the projectile detect the scanned beam and actively transmit a narrow optical beam back to a ground-based receiver in response to a detection of the scanned beam. IFF information can be modulated onto beam actively transmitted from the transponder. The system provides active two-way communications with comparatively simple components.

Abstract: The current invention describes a method for determining azimuth and elevation angles of a radiation source or other physical objects located anywhere within an cylindrical field of view. The invention makes use of an omni-directional imaging system comprising of reflective surfaces, an image sensor and an optional optical filter for filtration of the desired wavelengths. The said imaging system is designed to view an omni-directional field of view using a single image sensor and with no need for mechanical scan for coverage of the full field of view. Use of two such systems separated by a known distance, each providing a different reading of azimuth and elevation angle of the same object, enables classic triangulation for determination of the actual location of the object. The invention is designed to enable use of low cost omni-directional imaging systems for location of radiation sources or objects. Many additional needs and applications are envisaged for such a method.

Abstract: A dual mode seeker for intercepting a reentry vehicle or other target is disclosed. In one embodiment, the seeker is configured with an onboard 3D ladar system coordinated with an onboard IR detection system, where both systems utilize a common aperture. The IR and ladar systems cooperate with a ground based reentry vehicle detection/tracking system for defining a primary target area coordinate and focusing the IR FOV thereon. The IR system obtains IR image data in the IR FOV. The ladar system initially transmits with a smaller laser FOV to illuminate possible targets, rapidly interrogating the IR FOV. The ladar system obtains data on each possible target to perform primary discrimination assessments. Data fusion is employed to resolve the possible targets as between decoys/clutter and a reentry vehicle. The laser FOV is expandable to the IR FOV. Robust and reliable discrimination is obtained at high altitudes.

Abstract: A multi-axis laser scanner and receiver capable of providing laser scanning in multiple fields of view using a microscanner and a fold mirror with a patterned aperture. The fold mirror has a transmissive central region and a periphery that is reflective. Such scanners can be employed in a helicopter to scan in the forward field of view for obstacle detection, and in an upward field of view for air data measurements. Additional fields of view can be added, for example, to provide downward scans to detect height above terrain and ground speed.

Abstract: An imaging or viewing system, which automatically compensates for bright spots, which tend to overload or saturate imaging system. The system can be used with imaging type tracking systems, viewers and various types of optical devices which heretofore have been unable to provide satisfactory performance due to saturation or overloading of an imaging device due to bright spots, i.e., laser radiation flares or sunlight. The system in accordance with the invention is configured such that reflected radiation is imaged onto a first image plane without dividing the incoming radiation into two optical paths. A digital mirror device, i.e., is disposed at the first image plane. The radiation level of each pixel in the image plane is compared with a fixed threshold on a pixel by pixel basis and used to generate a mirror drive signal that automatically reduces the reflectivity of the corresponding mirror pixel to compensate for bright spots.

Abstract: A missile tracking and deflection system for protecting a platform includes a missile warning system for detecting the presence of a missile and generating a warning signal. A countermeasure processor receives the warning signal and analyzes characteristics of the missile to prioritize a trajectory signal. A track processor receives the trajectory signal and generates a pointer signal. The system also includes a receiver, which is positioned by a pointer that receives the pointer signal, for receiving a passive and/or active signature of the missile to confirm the presence thereof. The countermeasure processor then directs a laser beam at the missile to determine its operational parameters and receives an active signature from the missile.

Abstract: A method and apparatus is provide for receiving a first set of optical data from a first field of view and receiving a second set of optical data from a second field of view. A portion of the first set of optical data is communicated and a portion of the second set of optical data is reflected, both toward an optical combiner. The optical combiner then focuses the portions onto the image plane such that information at the image plane that is associated with the first and second fields of view is received by an optical detector and used to determine an attitude characteristic.

Abstract: A two-color infrared warning device, having both wide-angle and narrow-angle search capabilities, and a directional countermeasure device are mounted on a gimbal pointing in the same direction. The warning device and gimbal are initially operated in a wide-angle, step-stare mode to search for threats. When a potential hostile target is found, the warning device changes to a narrow-angle mode to determine whether the potential target is hostile. When a hostile target is identified, the directional countermeasure device, which is pointed at the target by virtue of its mounting with the warning device on the gimbal, is activated.

Abstract: A missile tracking and deflection system for protecting a platform includes a missile warning system for detecting the presence of a missile and generating a warning signal. A countermeasure processor receives the warning signal and analyzes characteristics of the missile to prioritize a trajectory signal. A track processor receives the trajectory signal and generates a pointer signal. The system also includes a receiver, which is positioned by a pointer that receives the pointer signal, for receiving a passive and/or active signature of the missile to confirm the presence thereof. The countermeasure processor then directs a laser beam at the missile to determine its operational parameters and receives an active signature from the missile.

Abstract: An apparatus for determining stellar inertial attitude based upon a plurality of stars includes a star tracker and a controller. The star tracker is used to sense the positions of stars and generate signals corresponding to the positions of the stars as seen in its field of view. The controller checks a star catalog and actively determines which stars to track. The controller does this determination in terms of each star's relative geometry. The controller then commands the star tracker to track these stars and uses them to determine the spacecraft attitude.

Abstract: An optical system includes a curved window, an asymmetric, scoop-shaped optical corrector adjacent to a curved inner surface of the window, an optical train positioned such that the optical corrector lies between the curved window and the optical train, a movable optical train support upon which the optical train is mounted, and a sensor disposed to receive an optical ray passing sequentially through the window, the optical corrector, and the optical train. The optical corrector has an inner surface and an outer surface, at least one of which has a shape defined by an asymmetric polynomial.

Abstract: A laser tracking system steers a beam of laser energy which is dithered in two directions to scan the surface of a moving object. A laser energy detector detects laser energy reflected from the target. Reflected energy is filtered to distinguish dither frequencies for signals in both directions, which signals are independently analyzed to determine the location of the target in relation to the laser beam. A bias signal is generated which causes the beam of laser energy to be steered toward a surface radius to be steered toward a surface with the largest compound curvature within the trackers, field-of-regard, to the target, to the tracked location on-target, or modified signals steer a portion of the beam to an optimum track location on target while offsetting most of the beam's energy to a second engagement location on target. Also, a track testing system is capable of monitoring a laser beam focused on a missile and determining the effective laser engagement on a spinning target.

Abstract: A system for ultrasonically cleaning tubes includes an elongated cleaning tank adapted to hold a quantity of detergent-containing water and a series of transducers mounted on the bottom wall of the tank in a generally linear arrangement extending between opposite end walls of the tank. The transducers generate ultrasonic cavitational energy within the water in the tank. An inclined upper tube entry ramp supported above the tank guides delivery of tubes in single file fashion into the tank to a reversely inclined middle tube transfer ramp. The inclined middle ramp guides transfer of tubes in single file fashion into the water in the tank and to a lower tube soak ramp having a tube accumulating terminal end. The lower ramp feeds the tubes across the tank within the water and above the transducers therein to its tube accumulating end such that each tube will pass through and be cleaned by the cavitation energy in the water.