GB958415A - Method and apparatus for automatically steering a missile - Google Patents
Method and apparatus for automatically steering a missileInfo
- Publication number
- GB958415A GB958415A GB2803661A GB2803661A GB958415A GB 958415 A GB958415 A GB 958415A GB 2803661 A GB2803661 A GB 2803661A GB 2803661 A GB2803661 A GB 2803661A GB 958415 A GB958415 A GB 958415A
- Authority
- GB
- United Kingdom
- Prior art keywords
- missile
- target
- gyro
- telescope
- produced
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S3/00—Direction-finders for determining the direction from which infrasonic, sonic, ultrasonic, or electromagnetic waves, or particle emission, not having a directional significance, are being received
- G01S3/78—Direction-finders for determining the direction from which infrasonic, sonic, ultrasonic, or electromagnetic waves, or particle emission, not having a directional significance, are being received using electromagnetic waves other than radio waves
- G01S3/782—Systems for determining direction or deviation from predetermined direction
- G01S3/785—Systems for determining direction or deviation from predetermined direction using adjustment of orientation of directivity characteristics of a detector or detector system to give a desired condition of signal derived from that detector or detector system
- G01S3/786—Systems for determining direction or deviation from predetermined direction using adjustment of orientation of directivity characteristics of a detector or detector system to give a desired condition of signal derived from that detector or detector system the desired condition being maintained automatically
Landscapes
- Physics & Mathematics (AREA)
- Electromagnetism (AREA)
- Engineering & Computer Science (AREA)
- General Physics & Mathematics (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
958, 415. Automatic steering of missiles. GENERAL DYNAMICS CORPORATION. Aug. 2, 1961, No. 28036/61. Heading G3R. In a system for automatically steering a missile towards a target, the missile is rolled continuously and a pair of oppositely disposed fixed incidence retractable wings are extended from the sides of the missile for such times as are necessary to correct heading and pitch. In Fig. 2 a Cassegrain telescope 17, 18 forms part of a gyro rotor having a permanent magnet 25 rotated by a pair of stator coils energized alternately by a magnetically operated switch (not shown) responsive to rotation of the permanent magnet. The gyro stabilized telescope is mounted in the nose of a missile having a window 24 transparent to radiation, e.g. infra-red, from a target, so that an image projected through a disc 21 having alternate transparent and opaque sectors and rotating with the rotor, produces, from a photo-cell 22, electric pulses on deviation of the telescope axis from the direction of the target. The pulses produced are applied through a transistor amplifier-demodulator, having automatic gain control, so that a coil 27 is energized to precess the gyroscope and bring the telescope into alignment with the target. A loud speaker is operated by the error signal so that it is known when the target has been acquired. The error signal applied to precess the gyro, together with a signal, representing the position of the gyro rotor relative to the missile, produced in a coil 28 by the rotor magnet, is applied to a demodulator the output of which controls an electromagnetically operated bleed valve controlling a hot gas fluid pressure jack 35, Fig. 11, to extend a pair of fixed angle of incidence wings 34 on each side at the rear end of the missile during appropriate periods of each roll cycle to turn the missile towards the target. The continuous roll of the missile is produced by canted nozzles or fins. An external battery is used to bring the gyro up to speed before launching. Hot gas for the control system is produced by solid propellant ignited at launching.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB2803661A GB958415A (en) | 1961-08-02 | 1961-08-02 | Method and apparatus for automatically steering a missile |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB2803661A GB958415A (en) | 1961-08-02 | 1961-08-02 | Method and apparatus for automatically steering a missile |
Publications (1)
Publication Number | Publication Date |
---|---|
GB958415A true GB958415A (en) | 1964-05-21 |
Family
ID=10269237
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB2803661A Expired GB958415A (en) | 1961-08-02 | 1961-08-02 | Method and apparatus for automatically steering a missile |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB958415A (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3714434A (en) * | 1967-07-31 | 1973-01-30 | Hughes Aircraft Co | Despin control system for a multispin stabilized device |
JPS5098355A (en) * | 1973-12-21 | 1975-08-05 | ||
DE1456122C1 (en) * | 1965-07-20 | 1978-06-15 | Messerschmitt Boelkow Blohm | Process for generating control commands that become effective in the correct phase for missiles rotating in the same direction around their longitudinal axis with a single control element and device for carrying out the process |
-
1961
- 1961-08-02 GB GB2803661A patent/GB958415A/en not_active Expired
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1456122C1 (en) * | 1965-07-20 | 1978-06-15 | Messerschmitt Boelkow Blohm | Process for generating control commands that become effective in the correct phase for missiles rotating in the same direction around their longitudinal axis with a single control element and device for carrying out the process |
US3714434A (en) * | 1967-07-31 | 1973-01-30 | Hughes Aircraft Co | Despin control system for a multispin stabilized device |
JPS5098355A (en) * | 1973-12-21 | 1975-08-05 | ||
JPS5842432B2 (en) * | 1973-12-21 | 1983-09-20 | ジヨ−ジ レオナ−ド エリオン | target tracking device |
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