GB910242A - Stable optical tracking fire control system - Google Patents
Stable optical tracking fire control systemInfo
- Publication number
- GB910242A GB910242A GB1807460A GB1807460A GB910242A GB 910242 A GB910242 A GB 910242A GB 1807460 A GB1807460 A GB 1807460A GB 1807460 A GB1807460 A GB 1807460A GB 910242 A GB910242 A GB 910242A
- Authority
- GB
- United Kingdom
- Prior art keywords
- target
- fighter
- radar
- pitch
- components
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41G—WEAPON SIGHTS; AIMING
- F41G9/00—Systems for controlling missiles or projectiles, not provided for elsewhere
- F41G9/002—Systems for controlling missiles or projectiles, not provided for elsewhere for guiding a craft to a correct firing position
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Radar Systems Or Details Thereof (AREA)
Abstract
910,242. Radiant-energy aircraft gun sights. NORTH AMERICAN AVIATION Inc. May 23, 1960, No. 18074/60. Class 40 (7). [Also in Groups XXI and XXXIII] Relates to a fire control system for a fighter aircraft in which the pilot maintains the fighter 5, Fig. 3, on a lead pursuit course towards a moving target 1 such that a missile fired at any time from the fighter in a fixed direction relative thereto will strike the target by maintaining a " disturbed " optical sight coincident with the visual image of the target. According to the present invention the optical sight is displaced from a datum position in accordance with the algebraic sum of (1) the angular displacement of the target from the longitudinal axis of the fighter as determined by an automatic tracking radar or an equivalent infra-red system and (2) a steering error signal computed as a function of the range r, range rate r, direction and angular velocity # of the target relative to the fighter as determined by the radar and the velocity vector Vo of the missile relative to the fighter as a function of the roll #, pitch # and angle of attack α of the fighter and the pressure ratio Ps/Pso, where Ps is the static air pressure at the fighter altitude and Pso is the static pressure at sea level. When the target is not visible the target and sight images may be displayed on an equivalent cathode-ray tube display. Assuming that the target is following a straight line path, the steering error, which is zero when the fighter is on a lead pursuit course, is given by where #M is the miss distance vector between the predicted positions C and D of the target and the missile explosion point at a time T f after firing the missile. The steering error is computed as components Mx/T # , My/T # , Mz/T # along x, y, z axes fixed relative to the fighter, as shown in Fig. 4, and the value of T # is given by equating Mx - to zero. The resultant value of T f thus T f gives the instant of nearest approach of the missile to the target and substitution of this value in the expressions for the z and y components of M/T # gives the pitch and yaw steering error signals. As shown in Fig. 2 and Fig. 5 (not shown), the output data from the tracking radar 7 is coupled to the computer 11 and the output yaw and pitch steering error signals are combined at 14 and 15 with signals from the radar aerial 6 representing the azimuth and elevation of the target to give resultant yaw and pitch signals which actuate servos 20, 21 controlling a sight head 22 so that an image 4, Fig. 1, of the sight reticle as projected on to the windscreen 2 of the fighter is displaced horizontally and vertically from the visual image 1 of the target as seen by the pilot in accordance with the yaw My Mz and pitch steering errors - and -. Thus T f T f the pilot controls the fighter to follow the correct course by maintaining the images 1 and 4 coincident. Computer.-If the orthogonal co-ordinate axes of the radar aerial are i, j and k with the beam along the i axis then when the beam is tracking the target the rate of change r in equation (7) above of the target range vector relative to the fighter is given by where #l i , # lj , and #l k are unit vectors along the aerial axes i, j, and k, and # k and # j are the rates of rotation of the radar beam about the k and j aerial axes as determined by rate gyros mounted on the aerial. Equation (7) may thus be expressed in i, j and k components which are then transformed into x, y and z components by means of resolvers set in accordance with the azimuth # and elevation # of the radar beam to give the x, y and z components of #M/T # and hence the time of flight T f and yaw and pitch steering error signals as described above. Certain components of the computer 11 may be as described in Specification 900,047 and the radar data may be smoothed before entering the computer by a vector filter as in Specification 824,177.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH686760A CH404469A (en) | 1960-06-16 | 1960-06-16 | Fire control system |
Publications (1)
Publication Number | Publication Date |
---|---|
GB910242A true GB910242A (en) | 1962-11-14 |
Family
ID=4316273
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB1807460A Expired GB910242A (en) | 1960-06-16 | 1960-05-23 | Stable optical tracking fire control system |
Country Status (2)
Country | Link |
---|---|
CH (1) | CH404469A (en) |
GB (1) | GB910242A (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN112731324A (en) * | 2020-12-16 | 2021-04-30 | 中交第一公路勘察设计研究院有限公司 | Multi-radar cross-regional networking multi-target tracking method for expressway |
CN113608186A (en) * | 2021-09-13 | 2021-11-05 | 中国工程物理研究院应用电子学研究所 | Calibration method for radar system and photoelectric imaging system |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4244272A (en) * | 1978-10-10 | 1981-01-13 | General Electric Company | Dispersion-controlled multibarrel gun system |
-
1960
- 1960-05-23 GB GB1807460A patent/GB910242A/en not_active Expired
- 1960-06-16 CH CH686760A patent/CH404469A/en unknown
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN112731324A (en) * | 2020-12-16 | 2021-04-30 | 中交第一公路勘察设计研究院有限公司 | Multi-radar cross-regional networking multi-target tracking method for expressway |
CN112731324B (en) * | 2020-12-16 | 2024-07-23 | 中交第一公路勘察设计研究院有限公司 | Multi-radar cross-regional networking multi-target tracking method for expressway |
CN113608186A (en) * | 2021-09-13 | 2021-11-05 | 中国工程物理研究院应用电子学研究所 | Calibration method for radar system and photoelectric imaging system |
CN113608186B (en) * | 2021-09-13 | 2023-10-20 | 中国工程物理研究院应用电子学研究所 | Calibration method of radar system and photoelectric imaging system |
Also Published As
Publication number | Publication date |
---|---|
CH404469A (en) | 1965-12-15 |
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