CN103063086A - Missile image guiding system - Google Patents
Missile image guiding system Download PDFInfo
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- CN103063086A CN103063086A CN2012102014300A CN201210201430A CN103063086A CN 103063086 A CN103063086 A CN 103063086A CN 2012102014300 A CN2012102014300 A CN 2012102014300A CN 201210201430 A CN201210201430 A CN 201210201430A CN 103063086 A CN103063086 A CN 103063086A
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Abstract
A missile image guiding system is mainly applied to an antiaircraft missile. A missile which has the advantages of resisting jamming ways like electronic jamming and infrared jamming and the like, and deactivating stealth technology and decoy flare technology of existing airplanes and the like can be designed through an electronic control system, a positioning device of an image tracking system, a target search method of the image tracking system, and a multiple image center point tracking method of the image tracking system.
Description
Affiliated technical field
The present invention relates to a kind of guided missile image guidance system, be mainly used in air defence missile.
Background technology
At present, the guidance system of known guided missile is used radar or infrared guidance more, and these guidance systems exist be difficult to find to lock aircraft with stealth technology, simultaneously exist easily disturbed, easily the problem such as induced by the bait bullet.When the country with absolute air superiority carries out asymmetric warfare to lacking the country that makes empty ability, lack the empty ability of system country and often lack effective anti-means and hit back.
Summary of the invention
For being difficult to of overcoming that existing missile brain exists find to lock aircraft with stealth technology, simultaneously exist easily disturbed, easily the deficiency such as induced by the bait bullet, the invention provides a kind of guided missile image guidance system, this guided missile image guidance system not only can make the stealth technology means of existing aircraft and bait bullet technological means lose efficacy, and can resist the interference of the interference means such as electronic interferences and infrared interference.
The technical solution adopted for the present invention to solve the technical problems is, it is a kind of guided missile image guidance system, comprise: positioning shooting head (1), travelling gear (2), power gear (3), positioning shooting head (4), Positioning Gear (5), image processing chip (6), motor (7), Positioning Gear (8), image processing chip (9), process chip (10), motor (11,12,20,21), rudder plate (13,14,19,22), storage chip (15), the main camera (16) of following the trail of, data importing interface (17): it is characterized in that: image guidance system electronic control system: data importing interface (17) is connected with storage chip (15) by data wire, storage chip (15) is connected with process chip (10) by data wire, the main camera (16) of following the trail of is connected with process chip (10) by data wire, motor (7) is connected with process chip (10) by the control wire jumper, positioning shooting head (1) is connected with image processing chip (6) by data wire, image processing chip (6) is connected with process chip (10) by data wire, positioning shooting head (4) is connected with image processing chip (9) by data wire, image processing chip (9) is connected with process chip (10) by data wire, motor (11,12,20,21) be connected motor (11 by the control wire jumper with process chip (10), 12,20,21) be respectively applied to adjust rudder plate (13,14,19,22).
The image tracing system positioning device: positioning shooting head (1) is fixed in Positioning Gear (5), positioning shooting head (4) is fixed in Positioning Gear (8), positioning shooting head (1) and the mutual level of positioning shooting head (4), the main camera (16) of following the trail of is positioned at positioning shooting head (1,5) on the connecting line central point vertical line, gear (2,3,5,8) be in contact with one another, gear (3) is driven by motor (7), gear (2,3) shape specification is identical, Positioning Gear (5,8) shape specification is identical, so Positioning Gear (5,8) after power gear (3) is rotated the direction of motion in opposite directions and move angle identical, Positioning Gear (5,8) the number of teeth is 360 integral multiple, and the higher detection range of distance (s) longer then accuracy is also far away between the higher and AB of tooth number.
Image tracing aims of systems searching method: guided missile is set to the rear main camera (16) of following the trail of of target direction emission the guided missile front region is made a video recording continuously, shooting is arrived film transmission to process chip (10), process chip (10) compares film determines object mobile in the film, process chip (10) is with mobile object and the contrast of the information bank in the storage chip (15) determined, determine that whether mobile object is aircraft in the firing area, if the target of attack of being defined as then the corresponding rudder plate of process chip (10) control carries out pursuit attack to target.
Image tracing system many image centers point tracking method: process chip (10) will be from main camera (16) and the positioning shooting head (1 followed the trail of, 4) image that obtains compares, adjust motor (7) with positioning shooting head (1 according to image contrast result treatment chip (10), 4) central point focuses on main camera (16) central point of following the trail of, determine that by the revolution that motor (7) is adjusted travelling gear (3) rotates the number of teeth, thereby determine Positioning Gear (5,8) rotate the number of teeth, namely know angle (α between target of attack and the AB, β) angle, angle (α between known attack target and the AB, β) distance (s) can calculate distance (h) between guided missile and target of attack between angle and the AB, process chip (10) to main follow the trail of camera (16) continuously between the image contrast that obtains of shooting and known guided missile and target of attack distance (h) can calculate target of attack (18) translational speed, process chip (10) is according to distance (h) between the guided missile that calculates and target of attack and target of attack (18) the translational speed adjustment motor (11 that calculates, 12,20,21), and then adjust control rudder plate (13,14,19,22) and guided missile propulsion device navigate missile pursuit attack.
The invention has the beneficial effects as follows, can make missile attack radar invisible target, and not affected and the bait technique influence by various perturbation techniques.
Description of drawings
The present invention is further described below in conjunction with drawings and Examples.
Fig. 1 is schematic diagram of the present invention.
Fig. 2 is many image centers point tracking method schematic diagram of the present invention.
The specific embodiment
In Fig. 1, positioning shooting head (1), travelling gear (2), power gear (3), positioning shooting head (4), Positioning Gear (5), image processing chip (6), motor (7), Positioning Gear (8), image processing chip (9), process chip (10), motor (11), motor (12), rudder plate (13), rudder plate (14), storage chip (15), main camera (16), the data importing interface (17) followed the trail of.
In Fig. 2, distance (s) between distance (h), the AB between angle (β), guided missile and target of attack between angle (α), target of attack and the BA between camera (1), camera (4), Support Gear (5), Support Gear (8), target of attack (18), gear centre point (A), gear centre point (B), target of attack and the AB.
Image guidance system electronic control system, the implementation technical scheme is as follows: data importing interface (17) is connected with storage chip (15) by data wire, storage chip (15) is connected with process chip (10) by data wire, the main camera (16) of following the trail of is connected with process chip (10) by data wire, motor (7) is connected with process chip (10) by the control wire jumper, positioning shooting head (1) is connected with image processing chip (6) by data wire, image processing chip (6) is connected with process chip (10) by data wire, positioning shooting head (4) is connected with image processing chip (9) by data wire, image processing chip (9) is connected with process chip (10) by data wire, motor (11,12,20,21) be connected motor (11 by the control wire jumper with process chip (10), 12,20,21) be respectively applied to adjust rudder plate (13,14,19,22).
The image tracing system positioning device, the implementation technical scheme is as follows: positioning shooting head (1) is fixed in Positioning Gear (5), positioning shooting head (4) is fixed in Positioning Gear (8), positioning shooting head (1) and the mutual level of positioning shooting head (4), the main camera (16) of following the trail of is positioned at positioning shooting head (1,5) on the connecting line central point vertical line, gear (2,3,5,8) be in contact with one another, gear (3) is driven by motor (7), gear (2,3) shape specification is identical, Positioning Gear (5,8) shape specification is identical, so Positioning Gear (5,8) after power gear (3) is rotated the direction of motion in opposite directions and move angle identical, Positioning Gear (5,8) the number of teeth is 360 integral multiple, and the higher detection range of distance (s) longer then accuracy is also far away between the higher and AB of tooth number.
Image tracing aims of systems searching method, the implementation technical scheme is as follows: guided missile is set to the rear main camera (16) of following the trail of of target direction emission the guided missile front region is made a video recording continuously, shooting is arrived film transmission to process chip (10), process chip (10) compares film determines object mobile in the film, process chip (10) is with mobile object and the contrast of the information bank in the storage chip (15) determined, determine that whether mobile object is aircraft in the firing area, if the target of attack of being defined as then the corresponding rudder plate of process chip (10) control carries out pursuit attack to target.
Image tracing system many image centers point tracking method, the implementation technical scheme is as follows: process chip (10) will be from main camera (16) and the positioning shooting head (1 followed the trail of, 4) image that obtains compares, adjust motor (7) with positioning shooting head (1 according to image contrast result treatment chip (10), 4) central point focuses on main camera (16) central point of following the trail of, determine that by the revolution that motor (7) is adjusted travelling gear (3) rotates the number of teeth, thereby determine Positioning Gear (5,8) rotate the number of teeth, namely know angle (α between target of attack and the AB, β) angle, angle (α between known attack target and the AB, β) distance (s) can calculate distance (h) between guided missile and target of attack between angle and the AB, process chip (10) to main follow the trail of camera (16) continuously between the image contrast that obtains of shooting and known guided missile and target of attack distance (h) can calculate target of attack (18) translational speed, process chip (10) is according to distance (h) between the guided missile that calculates and target of attack and target of attack (18) the translational speed adjustment motor (11 that calculates, 12,20,21), and then adjust control rudder plate (13,14,19,22) and guided missile propulsion device navigate missile pursuit attack.
Claims (4)
1. a guided missile image guidance system comprises: positioning shooting head 1, travelling gear 2, power gear 3, positioning shooting head 4, Positioning Gear 5, image processing chip 6, motor 7, Positioning Gear 8, image processing chip 9, process chip 10, motor 11,12,20,21, rudder plate 13,14,19,22, storage chip 15, main camera 16, the data importing interface 17 followed the trail of; It is characterized in that: image guidance system electronic control system: data importing interface 17 is connected with storage chip 15 by data wire, storage chip 15 is connected with process chip 10 by data wire, the main camera 16 of following the trail of is connected with process chip 10 by data wire, motor 7 is connected with process chip 10 by the control wire jumper, positioning shooting head 1 is connected with image processing chip 6 by data wire, image processing chip 6 is connected with process chip 10 by data wire, positioning shooting head 4 is connected with image processing chip 9 by data wire, image processing chip 9 is connected with process chip 10 by data wire, motor 11,12,20,21 pass through the control wire jumper is connected motor 11 with process chip 10,12,20,21 are respectively applied to adjust rudder plate 13,14,19,22.
2. guided missile image guidance system, it is characterized in that, the image tracing system positioning device: positioning shooting head 1 is fixed in Positioning Gear 5, positioning shooting head 4 is fixed in Positioning Gear 8, positioning shooting head 1 and positioning shooting head 4 mutual levels, the main camera 16 of following the trail of is positioned at positioning shooting head 1, on the 5 connecting line central point vertical lines, gear 2,3,5,8 are in contact with one another, gear 3 is driven by motor 7, gear 2,3 shape specification are identical, Positioning Gear 5,8 shape specification are identical, so Positioning Gear 5,8 after power gear 3 is rotated the direction of motion in opposite directions and move angle identical, Positioning Gear 5,8 the number of teeth is 360 integral multiple, and is also far away apart from the higher detection range of the longer then accuracy of s between the higher and AB of tooth number.
3. guided missile image guidance system, it is characterized in that, image tracing aims of systems searching method: guided missile is set to the rear main 16 pairs of guided missile front region of camera of following the trail of of target direction emission and is made a video recording continuously, shooting is arrived film transmission to process chip 10,10 pairs of films of process chip compare determines object mobile in the film, process chip 10 is with mobile object and the contrast of the information bank in the storage chip 15 determined, determine that whether mobile object is aircraft in the firing area, if the target of attack of being defined as then the corresponding rudder plate of process chip 10 controls carries out pursuit attack to target.
4. guided missile image guidance system, it is characterized in that, image tracing system many image centers point tracking method: process chip 10 will be from main camera 16 and the positioning shooting head 1 followed the trail of, 4 images that obtain compare, adjust motor 7 with positioning shooting head 1 according to image contrast result treatment chip 10,4 central points focus on main camera 16 central points of following the trail of, determine that by the revolution that motor 7 is adjusted travelling gear 3 rotates the number of teeth, thereby determine Positioning Gear 5,8 rotate the number of teeth, namely know angle α between target of attack and the AB, the β angle, angle α between known attack target and the AB, can calculate between guided missile and target of attack apart from h apart from s between β angle and the AB, can calculate target of attack 18 translational speeds apart from h between the image contrast that 10 pairs of main tracking cameras 16 continuous shootings of process chip obtain and known guided missile and target of attack, process chip 10 is according to adjusting motor 11 apart from h with target of attack 18 translational speeds that calculate between the guided missile that calculates and target of attack, 12,20,21, and then adjust control rudder plate 13,14,19,22 and guided missile propulsion device navigate missile pursuit attack.
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| Application Number | Priority Date | Filing Date | Title |
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| CN2012102014300A CN103063086A (en) | 2012-06-04 | 2012-06-04 | Missile image guiding system |
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| CN2012102014300A CN103063086A (en) | 2012-06-04 | 2012-06-04 | Missile image guiding system |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104990465A (en) * | 2015-07-21 | 2015-10-21 | 胡校峰 | Tracking reconnaissance locator and missile having locator |
| CN109885101A (en) * | 2019-01-04 | 2019-06-14 | 北京测威科技有限公司 | A kind of method and system using unmanned vehicle simulated missile terminal guidance |
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| JPH11295422A (en) * | 1998-04-07 | 1999-10-29 | Mitsubishi Electric Corp | Light wave sensor |
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| JP2007120993A (en) * | 2005-10-25 | 2007-05-17 | Tokyo Institute Of Technology | Object shape measuring device |
| CN101334276A (en) * | 2007-06-27 | 2008-12-31 | 中国科学院自动化研究所 | Visual sense measurement method and device |
| JP2011163589A (en) * | 2010-02-05 | 2011-08-25 | Mitsubishi Electric Corp | Guided flying object device |
| JP2011203057A (en) * | 2010-03-25 | 2011-10-13 | Tokyo Electric Power Co Inc:The | Distance measuring instrument for flying object and flying object position measuring instrument |
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2012
- 2012-06-04 CN CN2012102014300A patent/CN103063086A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| JPH11295422A (en) * | 1998-04-07 | 1999-10-29 | Mitsubishi Electric Corp | Light wave sensor |
| JP2001153649A (en) * | 1999-11-26 | 2001-06-08 | Mitsubishi Electric Corp | Light wave sensor device |
| JP2007120993A (en) * | 2005-10-25 | 2007-05-17 | Tokyo Institute Of Technology | Object shape measuring device |
| CN101334276A (en) * | 2007-06-27 | 2008-12-31 | 中国科学院自动化研究所 | Visual sense measurement method and device |
| JP2011163589A (en) * | 2010-02-05 | 2011-08-25 | Mitsubishi Electric Corp | Guided flying object device |
| JP2011203057A (en) * | 2010-03-25 | 2011-10-13 | Tokyo Electric Power Co Inc:The | Distance measuring instrument for flying object and flying object position measuring instrument |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104990465A (en) * | 2015-07-21 | 2015-10-21 | 胡校峰 | Tracking reconnaissance locator and missile having locator |
| CN109885101A (en) * | 2019-01-04 | 2019-06-14 | 北京测威科技有限公司 | A kind of method and system using unmanned vehicle simulated missile terminal guidance |
| CN109885101B (en) * | 2019-01-04 | 2022-02-22 | 北京测威科技有限公司 | Method and system for simulating missile terminal guidance by using unmanned aerial vehicle |
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Addressee: Ye Feng Document name: Notification of Publication and of Entering the Substantive Examination Stage of the Application for Invention |
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Address after: 510600 Guangdong State Taxation Bureau, 10 South Jing Road, Guangzhou, Guangdong, Tianhe District Applicant after: Ye Feng Address before: 516003, 8C, room 2, Xin Li Lou, third Xinxing garden, No. 13, Lake Zhang Road, Huicheng District, Guangdong, Huizhou Applicant before: Ye Feng |
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Address after: 516003, 8C, room 2, Xin Li Lou, third Xinxing garden, No. 13, Lake Zhang Road, Huicheng District, Guangdong, Huizhou Applicant after: Ye Feng Address before: 510600 Guangdong State Taxation Bureau, 10 South Jing Road, Guangzhou, Guangdong, Tianhe District Applicant before: Ye Feng |
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Application publication date: 20130424 |