|Publication number||USRE33287 E|
|Application number||US 07/355,741|
|Publication date||Aug 7, 1990|
|Filing date||May 19, 1989|
|Priority date||Feb 4, 1980|
|Publication number||07355741, 355741, US RE33287 E, US RE33287E, US-E-RE33287, USRE33287 E, USRE33287E|
|Inventors||John B. Allen|
|Original Assignee||Texas Instruments Incorporated|
|Export Citation||BiBTeX, EndNote, RefMan|
|Patent Citations (71), Non-Patent Citations (17), Referenced by (10), Classifications (7), Legal Events (2)|
|External Links: USPTO, USPTO Assignment, Espacenet|
This invention relates to an infrared carrier tracking, and more particularly to a system for tracking the carrier through clutter.
In the past guidance techniques, such as those disclosed in U.S. patent application, Ser. No. 896,087, filed Apr. 13, 1978 for a "Missile Detecting and Tracking Unit", have provided some clutter immunity as follows. During the early portion of the carrier flight, the carrier engine, if it has one and if not a beacon, is the brightest object in the detector field of view; all clutter objects have less intense images. The size and location of the clutter is stored so that it will not become confused with the beacon during the latter portion of flight when the carrier engine image is dim. In addition, a two dimension track gate is placed about the carrier to gate out any clutter. The gate is made just large enough to contain the portion of space into which the carrier is moving; as the carrier moves away, the gate is narrowed to eliminate widely scattered clutter. Nevertheless, when a moving carrier is tracked, new clutter is brought into the field view. Further, aspect angles of the clutter during the flight can change and clutter location can change due to operator jitter.
Accordingly, it is an object of this invention to provide for reliable, effective tracking of a carrier through clutter.
Another object of the invention is to provide a tracking system having a heat source whose intensity is controllable at short range to avoid blooming and to effect smoke penetration at long range.
Still another object of the invention is to provide a tracking system having clutter cancellation while tracking the carrier.
Yet another object of the invention is to provide a tracking system whose sub-system aboard the carrier is highly efficient and reliable, yet economical to produce using mass production techniques.
Briefly stated the invention comprises a tracking system which includes a beacon sub-system mounted upon a carrier, and a beacon control sub-system located remotely to the carrier. When a clutter ambiguity enters the field, the control sub-system sends a beacon interrupt signal to the beacon sub-system to interrupt the beacon. The resulting video frame is stored for comparison with a subsequent video frame taken with the beacon emitting energy. The subsequent frame is compared with the previous frame and the comparison reviewed to determine the location of the beacon. Any clutter present will be in both frames; however, the beacon will be present in only one frame. By this technique the clutter is differentiated from the carrier.
The novel features characteristic of the embodiments of the invention may best be understood by reference to the following detailed description when read in conjunction with the accompanying drawings wherein;
FIG. 1 depicts the utilization of a combined infrared sight and tracker unit;
FIG. 2 is an isometric view of the carrier including the beacon shutter system;
FIG. 3 is an isometric view of the beacon shutter system;
FIG. 4 is an isometric view of the shutter drive having a portion of the housing broken away to show more clearly the shutter drive mechanism;
FIG. 5 is a fragmentary cross sectional view of the thermal beacon taken along line A--A of FIG. 3;
FIG. 6 is a schematic view of the shutter-signal separation circuit and power driver of the shutter electronics;
FIG. 7 is a schematic of the beacon/carrier interface; and
FIG. 8 is a simplified flow diagram of the infrared sight and tracker unit.
For purposes of description and not by way of limitation the invention shall be described in connection with a guided missile used as the carrier. Such a guided missile is shown in FIG. 1 in which an infrared sight and tracker unit 10 comprises a missile 12 which has been launched from launcher 14 toward its destination or target 16. The target is shown as a tank viewed through the visual sight. It could also have been viewed through the infrared sight at the gunner's option. A beacon 18 is attached to the aft end of the missile 12. The beacon 18 is a part of the beacon system described hereinafter. A sighting means 20 which may be, for example, a thermal night sight such as that manufactured by Texas Instruments Incorporated under the designation AN/TAS4 Night Sight, is attached to the launcher 14 for viewing and tracking the carrier 12. The night sight is a forward looking infrared receiver and imaging device which includes a linear array of infrared detectors for scanning a field of view to detect the thermal energy emitted from the carrier's beacon. The night sight is modified, as hereinafter described, to accommodate a beacon control sub-system.
Each detector of the sighting means together with its preamplifier constitutes a channel (not shown) connected to an electronics package 22. A controller 24 controls the launching of the missile, activation of the night sight infrared receiver and activation of the beacon tracker unit. The electronics package 22 includes a microprocessor, which is preferably a Texas Instruments Incorporated SBP9900 microprocessor, controlled by the controller 24.
The carrier missile 12 (FIG. 2) includes a beacon system 26, a housing 28, an electronics pod 30 attached to the housing, an umbilical connector 32, and ballast 34 attached to the faring 36. The housing 28 has an aft end to which the beacon system is attached and a body portion to which the electronics pod 30 is attached. The electronics pod 30 contains the electronics for the beacon system. The umbilical connector 32 connects the electronics pod 30 to the beacon system 26. The ballast 34 attached to the faring 36 is to maintain the center of gravity or balance of the carrier owing to the weight of the beacon system.
Referring now to FIG. 3, the beacon system comprises a housing 38, a pyrotechnic igniter 40, a squib hammer 42, a shutter actuator 44, shutter drive linkage 46, a shutter return spring 48, installation hooks 50, and an installation bracket 52. The housing 38 is attached to the missile housing 28 (FIG. 2) by the bracket 52 and hooks 50. The housing 38 includes a case 54 FIG. 5 having an open end covered by a frangible glass cover 56. The case 54 may be, for example, a cast carbon type case. The frangible glass cover is shattered for removal by the squib hammer 42 (FIG. 3). A layer of non-combustible insulation material 58 (FIG. 5) covers the bottom of the case. A pyrotechnic heater 60 is hermetically sealed in foil 62 for protection during storage. The pyrotechnic heater may be selected from the group of intermetallic reaction pyrotechnic materials consisting of titanium boride, titanium boride plus titanium carbide, titanium carbide, zirconium boride, and zirconium carbide. The foil 62 is a heat meltable foil which melts when the pyrotechnic heater is ignited thereby enhancing the thermal path to an emitter 64. The emitter 64 is, for example, a carbon type emitter capable of withstanding the high temperature (3800° C.) effects.
An apertured base plate 66 covers the emitter 64. An apertured sheet 68 is slidably mounted in base plate guides between the apertured base plate 66 and an apertured honeycomb optics 70. The aperture sheet 68 acts as a shutter for obscuring the apertures of the base plate 66 and honeycomb optics 70, which are in alignment, when displaced by about 1/2 the hole spacing. The apertured sheet or shutter 68 has two flexures 48 and 74 at opposite ends (FIG. 4). Flexure 48 acts as a return spring to hold the shutter 68 open, i.e. the aperture sheet holes are aligned with those of the base plate and honeycomb optics. Flexure 74 acts as a transfer lever to the drive linkage 46.
The drive linkage 46 includes a rod 76 having, for example, ball shaped ends. The ball shaped ends of rod 76 extend, respectively, through slots in flexure 74 and one arm of a slotted flexure-pivoted bell crank 78. The other arm of the flexure-pivoted bell crank is attached to the core 79 of a linear solenoid comprising the shutter actutor 44. Thus, with the return spring 48 pulling the aperture sheet and the linear solenoid pulling the shutter drive linkage to close it the system always acts in tension thereby utilizing the tensile strength of the member to substantially reduce the size of the members.
The shutter electronics 30 (FIG. 2) comprises a shutter-signal separation circuit and power driver packaged separately from the beacon to fit the available space and reduce mass unbalance in the missile. A power source such as, for example, the existing missile battery 80 (FIG. 6) provides power to a dc regulator 82 and power driver 84. The dc regulator provides selected dc voltages to a buffer amplifier 86, 2-pole low pass filter 88 and threshold detector 90. The buffer amplifier 86 reestablishes the values of the guidance and beacon actuator signals received by the missile. The two-pole, low pass filter, with a preselected corner frequency rejects the missile steering commands and passes the shutter actuating dc pulse. The dc shutter pulse signal triggers a threshold detector 90 which drives the power driver output stage 84. The power driver contact is connected to the shutter actuator 44 solenoid (FIGS. 3 & 4). The command pulse duration is selected to keep the shutter closed for an interval equal to one time frame of the night sight.
The beacon/missile interface electronics (FIG. 7) comprises the power source 80 which is connected to the junction of the shutter drive electronics pod 30, fusible link 92 of a pyrotechnic initiator branch circuit, and switch 94 of a squib hammer branch circuit. The pyrotechnic initiator branch circuit, in addition to the fusible link 92 includes a pyrotechnic initiator 96, which is, for example, an electrically fired heat match. The squib hammer branch circuit includes, in addition to the switch 94, a fusible link 98 connected to the switch 94 and to a squib 100. The fusible links 92 and 98 are included in the heater ignition and cover removal circuits to protect the battery from potential overloading.
At start up, the squib of the squib hammer circuit is fired electrically and the gas generated drives the hammer 102 which is a low brisance pyrotechnic hammer. The cover 56 being a chemically tempered glass having a thickness of about 0.050 to 0.060 inch and a modulus of rupture of about 40,000 psi. is fragmented and removed by the hammer within about 10 milliseconds. Also at start up the beacon or heater is fired. The heater pyrotechnic has a propagation velocity such that the time for the reaction to spread to the entire source is comparable to the missile's flight time. Thus, the emitter 64 (FIG. 5) first meets the need for lower intensity early in flight and is gradually raised throughout the flight to meet the higher intensity need during the later stages of flight.
As previously described the shutter drive electronics 30 (FIG. 2) controls the actuation of the shutter actuator 44 solenoid (FIG. 3). Standby power for the shutter electronics 30 is low (about 1 watt). When shutter operation is commanded, each cycle draws up to about 10 watt-seconds.
Shutter operation, if it occurs at all, will happen near the end of the flight. The microprocessor of the electronics package 22 (FIG. 1) is programmed (FIG. 8) so that upon receipt of a start up signal 104 tracker conditioning 106 is effected by starting the clock, timing sequence and determining pre-fire conditions. A time decision 108 is then made. If the time is less than a preselected time, a decision 110 is made whether the tracker is in handoff. Handoff results when the tracker looses the missile. If the answer is no the computer commands the missile to fly a standard track link 112, and the computer returns 114 to start 104. If the tracker is in handoff, a decision 116 is made whether the missile is in the field of view of the forward looking infrared (FLIR) sight. If not, a command 118 is given for the missile to fly a preprogrammed flight profile. Next a command 120 is given to activate a GLI tracker for missile acquisition and the computer returns 122 to start 104. If the missile is in the field of view a command 124 is given to compute the centroid area of the last field and based thereon to compute a position estimate. The computer then returns 126 to start.
When the decision 108 is that the preselected time has been reached, commands 128 and 130 are given to establish, respectively, scene stabilization and a peak set. Next a command 132 is given to establish a clutter map reference from the stabilized scene. Then a command 134 is given to reject peaks in the clutter maps by comparing the established peaks with the clutter map reference. Next a command 136 is given to update the clutter map. Then a decision 138 is made whether any peak remains. If no peak remains a command 140 is given for the tracker to coast and then return 142 to start 104. If yes, a decision 144 is made whether more than one peak exists within a reasonable radius of the previous missile track. If only one peak exists, a command 146 is given to compute the centroid area which is converted to guidance signals. Then the computer returns 148 to start. If more than one peak exists, a command 150 is given to actuate the beacon shutter system, and the beacon shutter 68 is closed for one video frame. All peaks appearing in the map during this frame are known to be clutter and are entered in the clutter map. The beacon is then turned on again and the computer returned 152 to the start.
Although only a single embodiment of this invention has been described herein, it will be apparent to one skilled in the art that various modifications to the details of construction shown and described such as for example, substituting a laser (CO2 laser) for the pyrotechnic, may be made without departing from the scope of the invention.
|Cited Patent||Filing date||Publication date||Applicant||Title|
|US2906885 *||Jun 2, 1955||Sep 29, 1959||Itt||Apparatus for detecting hot journal boxes|
|US2930894 *||Jul 13, 1954||Mar 29, 1960||Republic Aviat Corp||Optical sighting and tracking device|
|US2989640 *||Jun 22, 1956||Jun 20, 1961||Jean Turck Ets||Automatic optical remote-control device for remote-guided machines|
|US3065931 *||Mar 19, 1958||Nov 27, 1962||Dixon Edgar O||Target-seeking guidance system|
|US3098933 *||Oct 23, 1957||Jul 23, 1963||Republic Aviat Corp||Photosensitive electronic tracking head|
|US3111088 *||Feb 27, 1962||Nov 19, 1963||Martin Marietta Corp||Target seeking missile|
|US3128061 *||Aug 11, 1945||Apr 7, 1964||Chew Thornton W||Automatic self-guidance system for movable objects|
|US3219826 *||Oct 7, 1963||Nov 23, 1965||Raytheon Co||Target tracking guidance system with false signal detecting means|
|US3227879 *||Oct 21, 1963||Jan 4, 1966||Gen Precision Inc||Infrared simulator|
|US3233847 *||Nov 5, 1962||Feb 8, 1966||Contraves Ag||System for guiding a missile toward a moving target|
|US3242485 *||Mar 30, 1964||Mar 22, 1966||Barnes Eng Co||Infrared acquisition aid for a tracking system|
|US3275829 *||Aug 15, 1960||Sep 27, 1966||Special Devices Inc||Cavity radiator with a pyrotechnic charge that remains intact during and after combustion|
|US3366346 *||Jul 19, 1965||Jan 30, 1968||Army Usa||Remote missile command system|
|US3448271 *||Sep 21, 1965||Jun 3, 1969||Ibm||Object tracking and imaging system having error signal duration proportional to off-center distance|
|US3478212 *||Jan 4, 1967||Nov 11, 1969||Telecommunications Sa||Aiming system for the remote guidance of self-propelled missiles toward a target|
|US3564257 *||Jan 31, 1962||Feb 16, 1971||Emi Ltd||Radiation detecting apparatus|
|US3566026 *||Feb 27, 1967||Feb 23, 1971||Hughes Aircraft Co||Automatic acquisition and tracking system|
|US3567163 *||Oct 8, 1964||Mar 2, 1971||Martin Marietta Corp||Guidance system|
|US3598344 *||Feb 2, 1968||Aug 10, 1971||Philco Ford Corp||Missile command system|
|US3640628 *||Dec 18, 1969||Feb 8, 1972||Hughes Aircraft Co||Electro-optical target acquisition blanking system|
|US3711046 *||Oct 22, 1969||Jan 16, 1973||Barhydt H||Automatic missile guidance system|
|US3727553 *||Dec 6, 1966||Apr 17, 1973||Hawker Siddeley Dynamics Ltd||Fuze device with target detecting means|
|US3733133 *||Mar 13, 1970||May 15, 1973||Hughes Aircraft Co||Balanced tiltable, rotating mirror with its optical axis angularly offset from its axis of rotation|
|US3742238 *||Dec 14, 1970||Jun 26, 1973||Texas Instruments Inc||Two axes angularly indexing scanning display|
|US3751166 *||Jun 3, 1971||Aug 7, 1973||Us Army||Command guidance transmitter system|
|US3753538 *||May 12, 1971||Aug 21, 1973||British Aircraft Corp Ltd||Vehicle command systems|
|US3761180 *||Sep 22, 1972||Sep 25, 1973||Maxwell R||Synchronously gated active night sight|
|US3787668 *||Feb 22, 1973||Jan 22, 1974||Us Army||Adaptive threshold unit|
|US3796396 *||Oct 30, 1972||Mar 12, 1974||Crovella C||Method and apparatus for modulating a pyrotechnic tracer|
|US3797395 *||Apr 1, 1966||Mar 19, 1974||Us Army||Signalling device|
|US3804976 *||May 15, 1972||Apr 16, 1974||Kaiser Aerospace & Electronics||Multiplexed infrared imaging system|
|US3820742 *||Feb 8, 1965||Jun 28, 1974||Watkins R||Missile guidance and control system|
|US3848830 *||Nov 16, 1972||Nov 19, 1974||Messerschmitt Boelkow Blohm||Missile guidance system|
|US3856237 *||Aug 3, 1967||Dec 24, 1974||Fairchild Hiller Corp||Guidance system|
|US3868883 *||Feb 20, 1964||Mar 4, 1975||Mc Donnell Douglas Corp||Guidance system|
|US3889117 *||May 3, 1973||Jun 10, 1975||Cincinnati Electronics Corp||Tapered detector scanning array system|
|US3944730 *||Mar 5, 1974||Mar 16, 1976||Aga Aktiebolag||Device for the elimination of the effect of background radiation on the image representation in an ir-camera|
|US3954228 *||Feb 23, 1968||May 4, 1976||The United States Of America As Represented By The Secretary Of The Army||Missile guidance system using an injection laser active missile seeker|
|US3955046 *||Apr 26, 1967||May 4, 1976||E M I Limited||Improvements relating to automatic target following apparatus|
|US3974383 *||Feb 3, 1975||Aug 10, 1976||Hughes Aircraft Company||Missile tracking and guidance system|
|US3974984 *||Mar 23, 1962||Aug 17, 1976||British Aircraft Corporation||Control of guided missiles|
|US3998406 *||May 28, 1964||Dec 21, 1976||Aeronutronic Ford Corporation||Guided missile system|
|US4001588 *||Jul 17, 1975||Jan 4, 1977||General Atomic Company||Radioactive heat source and method of making same|
|US4009393 *||Sep 14, 1967||Feb 22, 1977||General Dynamics Corporation||Dual spectral range target tracking seeker|
|US4019422 *||Jul 19, 1976||Apr 26, 1977||Paccar Inc.||Vehicular mounted tow missile system|
|US4020339 *||May 19, 1975||Apr 26, 1977||Aktiebolaget Bofars||System for determining the deviation of an object from a sight line|
|US4027834 *||Apr 13, 1964||Jun 7, 1977||Ford Aerospace & Communications Corporation||Missile nozzle configuration|
|US4027837 *||Oct 23, 1969||Jun 7, 1977||The United States Of America As Represented By The Secretary Of The Army||Optical tracking link utilizing pulse burst modulation for solid state missile beacons|
|US4038547 *||May 31, 1966||Jul 26, 1977||Philco Corporation||Tracking and sighting instrument|
|US4040744 *||Oct 5, 1973||Aug 9, 1977||General Dynamics||Multiple spectrum co-axial optical sight and closed loop gun control system|
|US4047117 *||Dec 27, 1976||Sep 6, 1977||Hughes Aircraft Company||Multi-level laser illuminator|
|US4047678 *||Nov 7, 1969||Sep 13, 1977||The United States Of America As Represented By The Secretary Of The Army||Modulated, dual frequency, optical tracking link for a command guidance missile system|
|US4054797 *||Sep 23, 1976||Oct 18, 1977||The United States Of America As Represented By The Secretary Of The Navy||Series-parallel scan, IR, CID, focal-plane array|
|US4060830 *||Oct 22, 1976||Nov 29, 1977||Westinghouse Electric Corporation||Volumetric balance video tracker|
|US4064533 *||Oct 24, 1975||Dec 20, 1977||Westinghouse Electric Corporation||CCD focal plane processor for moving target imaging|
|US4072281 *||Dec 27, 1976||Feb 7, 1978||The United States Of America As Represented By The Secretary Of The Army||Optical attitude reference|
|US4133004 *||Nov 2, 1977||Jan 2, 1979||Hughes Aircraft Company||Video correlation tracker|
|US4146196 *||Jul 20, 1976||Mar 27, 1979||The United States Of America As Represented By The Secretary Of The Air Force||Simplified high accuracy guidance system|
|US4151968 *||Nov 26, 1976||May 1, 1979||Societe Anonyme De Telecommunications||Night guiding device for self-propelled missiles|
|US4162052 *||Dec 15, 1976||Jul 24, 1979||Societe Anonyme De Telecommunications||Night guidance of self-propelled missiles|
|US4174818 *||Jan 14, 1977||Nov 20, 1979||Elliott Brothers (London) Limited||Guidance systems for mobile craft|
|US4183482 *||Dec 2, 1976||Jan 15, 1980||Societe Anonyme De Telecommunications||Night guiding device for self-propelled missiles|
|US4193688 *||Oct 28, 1970||Mar 18, 1980||Raytheon Company||Optical scanning system|
|US4220296 *||Nov 3, 1977||Sep 2, 1980||Licentia Patent-Verwaltungs-G.M.B.H||Method for guiding the final phase of ballistic missiles|
|US4234141 *||Mar 10, 1970||Nov 18, 1980||The United States Of America As Represented By The Secretary Of The Army||Range gated retroreflective missile guidance system|
|US4247059 *||Oct 25, 1978||Jan 27, 1981||The United States Of America As Represented By The Secretary Of The Army||Light emitting diode beacons for command guidance missile track links|
|US4406429 *||Apr 13, 1978||Sep 27, 1983||Texas Instruments Incorporated||Missile detecting and tracking unit|
|US4732349 *||Oct 8, 1986||Mar 22, 1988||Hughes Aircraft Company||Beamrider guidance system|
|DE1914250A1 *||Mar 20, 1969||Oct 1, 1970||Messerschmitt Boelkow Blohm||Waffensystem zur Ortung und Bekaempfung ruhender oder bewegter Objekte|
|DE2657261A1 *||Dec 17, 1976||Jul 7, 1977||Telecommunications Sa||Verfahren, um bei einem optischen anzeigegeraet, das einem thermischen fernrohr zugeordnet ist, welches fuer die nachtlenkung von selbstfahrenden und eine infrarotquelle tragenden maschinen bzw. projektilen dient, die abbildung einer verhaeltnismaessig intensiven stoerstrahlungsquelle abzudecken, und vorrichtung zur durchfuehrung des verfahrens|
|FR2279063A1 *||Title not available|
|1||Bernard D. Steinberg, Modern Radio Analysis, Evaluation, and System Design, Chapter 2, "MTI Radar Filters", pp. 491-492.|
|2||*||Bernard D. Steinberg, Modern Radio Analysis, Evaluation, and System Design, Chapter 2, MTI Radar Filters , pp. 491 492.|
|3||Cwo, T. L. Golden, National Defense, "The Dragon Missile", Jan.-Feb. 1974, pp. 348-349.|
|4||*||Cwo, T. L. Golden, National Defense, The Dragon Missile , Jan. Feb. 1974, pp. 348 349.|
|5||*||Dictionary of Scientific and Technical Terms; McGraw Hill; 1978; pp. 825 & 1022.|
|6||Dictionary of Scientific and Technical Terms; McGraw-Hill; 1978; pp. 825 & 1022.|
|7||James R. Spencer, Radio Electronics, "Infrared Guides Missiles", 1/60.|
|8||*||James R. Spencer, Radio Electronics, Infrared Guides Missiles , 1/60.|
|9||*||Merrill I. Skolnik, Introduction to Radar Systems, 1962, pp. 534 536, 594 602.|
|10||Merrill I. Skolnik, Introduction to Radar Systems, 1962, pp. 534-536, 594-602.|
|11||Philip J. Klass, Aviation Week, "Infrared Challenges Radar's Monopoly", 4/25/57.|
|12||Philip J. Klass, Aviation Week, "Optical Guidance Designed for Missiles", 12/8/58, pp. 67, 69, 71.|
|13||*||Philip J. Klass, Aviation Week, Infrared Challenges Radar s Monopoly , 4/25/57.|
|14||*||Philip J. Klass, Aviation Week, Optical Guidance Designed for Missiles , 12/8/58, pp. 67, 69, 71.|
|15||*||Texas Instruments 9900 SBP 9989 Advanced 16 Bit I 2 L Microprocessor, Microprocessor Series Data Manual, 1982.|
|16||Texas Instruments 9900 SBP 9989 Advanced 16 Bit I2 L Microprocessor, Microprocessor Series Data Manual, 1982.|
|17||*||Texas Instruments TMS9900 Microprocessor Series Data Manual; 1978.|
|Citing Patent||Filing date||Publication date||Applicant||Title|
|US5074490 *||Jan 30, 1991||Dec 24, 1991||Texas Instruments Incorporated||Carrier tracking system|
|US5444262 *||Dec 21, 1993||Aug 22, 1995||The United States Of America As Represented By The Secretary Of The Army||Thermoelectric device for vehicle identification|
|US6872960 *||Apr 18, 2001||Mar 29, 2005||Raytheon Company||Robust infrared countermeasure system and method|
|US7203580 *||Feb 11, 2004||Apr 10, 2007||Denso Corporation||Electrical control unit and control system comprising plural electrical control units|
|US7410119 *||Jul 1, 2004||Aug 12, 2008||Mbda France||Rotating missile emitting light pulses|
|US20040162653 *||Feb 11, 2004||Aug 19, 2004||Denso Corporation||Electrical control unit and control system comprising plural electrical control units|
|US20050178875 *||Jun 30, 2004||Aug 18, 2005||Shumov Sergeyi A.||Portable surface-to-air missile system|
|US20060255204 *||Jul 1, 2004||Nov 16, 2006||Mbda France||Rotating missile emitting light pulses|
|EP0435589A2 *||Dec 20, 1990||Jul 3, 1991||Hughes Aircraft Company||Microcontroller for controlling an airborne vehicle|
|EP0435589A3 *||Dec 20, 1990||Apr 8, 1992||Hughes Aircraft Company||Microcontroller for controlling an airborne vehicle|
|International Classification||G01S3/786, F41G7/30|
|Cooperative Classification||G01S3/786, F41G7/301|
|European Classification||G01S3/786, F41G7/30B|
|Aug 7, 1997||AS||Assignment|
Owner name: RAYTHEON TI SYSTEMS, INC., TEXAS
Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:TEXAS INSTRUMENTS INCORPORATED;TEXAS INSTRUMENTS DEUTSCHLAND GMBH;REEL/FRAME:008628/0414
Effective date: 19970711
|Apr 2, 1999||AS||Assignment|
Owner name: RAYTHEON COMPANY, A CORPORATION OF DELAWARE, MASSA
Free format text: CHANGE OF NAME;ASSIGNOR:RAYTHEON TI SYSTEMS, INC.;REEL/FRAME:009875/0499
Effective date: 19981229