CN103847975B - A kind of inserted airborne photoelectric capstan head and aircraft - Google Patents
A kind of inserted airborne photoelectric capstan head and aircraft Download PDFInfo
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- CN103847975B CN103847975B CN201410103099.8A CN201410103099A CN103847975B CN 103847975 B CN103847975 B CN 103847975B CN 201410103099 A CN201410103099 A CN 201410103099A CN 103847975 B CN103847975 B CN 103847975B
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Abstract
The invention provides a kind of inserted airborne photoelectric capstan head and aircraft, this inserted airborne photoelectric capstan head is contained within the first system (17), second system (18) and central authorities' coupling mirror (2), after light arrives central authorities' coupling mirror (2), a part of light enters the first system (17) from through hole (21), another light is reflected into second system (18) through central coupling mirror (2), by different optical system coupled in same optical channel, thus realizing coaxial and common road, and then change two optical windows of prior art into one.The aircraft containing this inserted airborne photoelectric capstan head is made to have good aeroperformance, mobility, structural behaviour and security performance.
Description
Technical field
The present invention relates to airborne opto-electronic device technical field, particularly a kind of inserted airborne photoelectric capstan head, or a kind of aircraft containing this inserted airborne photoelectric capstan head.
Background technology
Existing airborne photoelectric capstan head can be divided into external hanging type capstan head and the big class of Integral turning tower two.Wherein external hanging type airborne photoelectric capstan head is generally divided in plug-in turret part and cabin and controls part two body, and the factor of the aspect such as the volume of plug-in turret part, weight, structural strength and planform, all can produce bigger adverse effect for the aeroperformance of aircraft, mobility, structural behaviour and security performance etc..So-called monoblock type airborne photoelectric capstan head is by integrated for an all parts entirety, it is mounted on airframe outer surface, or the head of capstan head is stretched outside fuselage, other parts are then positioned within fuselage, so just can reduce structural volume and the weight impact on aircraft of external fuselage, but existing capstan head generally or has two optical windows, or adopt super-hemispherical optical window mouth mirror.
, all there is respective weak point in existing airborne photoelectric capstan head, whether external hanging type capstan head or Integral turning tower.Wherein the volume and weight of the outer portion that external hanging type capstan head is hung on outward airframe because of it is relatively big, thus the aeroperformance of aircraft, mobility, structural behaviour and security performance etc. all can be produced very big adverse effect.And Integral turning tower or cause that because having two optical windows outboard portion volume is relatively big, or in order to realize the working range in its hemisphere spatial domain, in addition it is also necessary to adopts the super-hemispherical optical window mouth mirror that one value is high.Due to the fast and frequent landing of aircraft flight speed, the foreign material such as ground and aerial dust, sandstone very easily pollute and damage super-hemispherical optical window mouth mirror.
Summary of the invention
Two awkward technical problems of optical window are had in order to solve Integral turning tower in prior art.The invention provides a kind of inserted airborne photoelectric capstan head and a kind of aircraft, this inserted airborne photoelectric capstan head, both fuselage overhang it had been absent from, also without offering two optical windows, value more need not be adopted high and subject to stained super-hemispherical optical window mouth mirror, can make above-mentioned to affect flight vehicle aerodynamic performance, mobility, structural behaviour, the external-hanging structure form problem of security performance, volume weight problem, hemispherical optical window are worth expensive and subject to stained problem etc. and be solved in the lump.
The present invention solves that its technical problem the technical scheme is that a kind of inserted airborne photoelectric capstan head, including capstan head body and the trousers being arranged on capstan head body lower part；Described inserted airborne photoelectric capstan head is contained within the first system, second system and central authorities' coupling mirror, central authorities' coupling mirror is arranged between the camera lens of the first system and the camera lens of second system, it is provided with through hole in central authorities' coupling mirror, after light can enter described inserted airborne photoelectric capstan head from the window of bottom part of fairing and arrive central authorities' coupling mirror, a part of light enters the first system from through hole, and another light is reflected into second system through central authorities' coupling mirror.
It is originally internal that the first system and second system are arranged at capstan head, and the angle of central authorities' coupling mirror and optical axis is 45 °.
The surface of central authorities' coupling mirror is coated with total reflection film, and the through hole in central authorities' coupling mirror is track type.
Described inserted airborne photoelectric capstan head is contained within the first reflecting mirror, the second reflecting mirror, the 3rd reflecting mirror and the 4th reflecting mirror, first reflecting mirror and the second mirror parallel, 3rd reflecting mirror and the 4th mirror parallel, angle between second reflecting mirror and the 3rd reflecting mirror is 90 °, and the angle between the 4th reflecting mirror and central authorities' coupling mirror is 90 °；Light can enter described inserted airborne photoelectric capstan head from the window of bottom part of fairing and sequentially pass through the first reflecting mirror, the second reflecting mirror, the 3rd reflecting mirror and the 4th reflecting mirror back reflection to central authorities' coupling mirror.
Trousers is contained within pitching slew gear, this pitching slew gear includes the pitching mirror unit for installing the first reflecting mirror and the pitching motor for driving the first reflecting mirror to rotate, and this pitching motor can drive the first reflecting mirror to rotate for axle with horizontal direction through the optical axis of the first reflecting mirror.
This pitching slew gear includes hollow gyroaxis, and hollow gyroaxis is tubular, and the first reflecting mirror and pitching mirror unit are arranged in hollow gyroaxis, and described pitching motor can drive the first reflecting mirror, pitching mirror unit and hollow gyroaxis together to rotate.
The barrel of hollow gyroaxis is provided with the planar wave window mirror corresponding with window, and light can sequentially pass through window and plane optical window mirror to the first reflecting mirror.
Trousers is contained within orientation slew gear, this orientation slew gear includes the orientation mirror unit for installing the second reflecting mirror, the 3rd reflecting mirror and the 4th reflecting mirror, this orientation slew gear also includes azimuth-drive motor, and this azimuth-drive motor can drive the second reflecting mirror on orientation mirror unit, the 3rd reflecting mirror, the 4th reflecting mirror and described pitching slew gear together to rotate for axle with vertical direction through the optical axis of central authorities' coupling mirror.
The bottom of trousers be shaped as spherical crown, the height of this spherical crown is less than the radius of this spherical crown place spheroid.
A kind of aircraft, this aircraft contains above-mentioned inserted airborne photoelectric capstan head, and the capstan head body of this inserted airborne photoelectric capstan head is arranged in this aircraft, and the bottom-exposed of trousers is outside the wallboard of this aircraft.
The invention has the beneficial effects as follows:
1, the inserted airborne photoelectric capstan head in the present invention includes two parts inside and outside fuselage, outboard portion is movable part, by above 360 ° of revolutions and its can ± optical window of 90 ° of pitching realizes hemisphere spatial domain working range, in machine, part can by central authorities' coupling mirror according to function and space requirement flexible combination.
2, the inserted airborne photoelectric capstan head in the present invention only has a planar wave window, and can forward concealed location to when not working in order to avoid tarnishing.
3, the inserted airborne photoelectric capstan head in the present invention, the outer rotating part of machine be shaped as spherical crown, height less than the radius of this spherical crown place spheroid, revolution steadily, aeroperformance good, the impact of aircraft is little.
Accompanying drawing explanation
Below in conjunction with accompanying drawing, inserted airborne photoelectric capstan head of the present invention is described in further detail.
Fig. 1 is the structural representation of this inserted airborne photoelectric capstan head.
Fig. 2 is the schematic diagram of central authorities' coupling mirror.
Wherein 1. capstan head body, 2. central authorities' coupling mirror, 3. the first reflecting mirror, 4. pitching mirror unit, 5. planar wave window mirror, 6. hollow gyroaxis, 7. bearing, 8. bearing block, 9. pitch reference, 10. drive mechanism, 11. control circuits, 121. second reflecting mirrors, 122. the 3rd reflecting mirror, 123. the 4th reflecting mirrors, 13. orientation mirror units, 14. hollow bearings, 15. azimuth sensor, 16. trouserss, 17. the first systems, 18. second systems, 19. window, 20. wallboards, 21. through holes, 22. drive mechanisms.
Detailed description of the invention
Below in conjunction with accompanying drawing, inserted airborne photoelectric capstan head of the present invention is described in further detail.A kind of inserted airborne photoelectric capstan head, including capstan head body 1 and the trousers 16 being arranged on capstan head body 1 bottom；Described inserted airborne photoelectric capstan head is contained within the first system 17, second system 18 and central authorities' coupling mirror 2, central authorities' coupling mirror 2 is arranged on the camera lens below the first system 17 and between the camera lens on the right side of second system 18, it is provided with through hole 21 in central authorities' coupling mirror 2, after optical signal can enter described inserted airborne photoelectric capstan head from the window 19 bottom trousers 16 and arrive central authorities' coupling mirror 2, a part of optical signal enters the first system 17 from through hole 21, another optical signal is reflected into second system 18 through central authorities' coupling mirror 2, as depicted in figs. 1 and 2.
Capstan head body 1 can be made up of aluminium alloy or other materials, and position between, the internal each function parts of capstan head fixing for installing between inserted airborne photoelectric capstan head and aircraft wallboard is fixing.Central authorities' coupling mirror 2 can be made up of common optical glass, quartz-optical glass or other materials, realize functional requirements such as the different reflection of pedigree light, transmission, light splitting, conjunction light by polishing, plated film or other technique, and it is placed on the optical axis of the optical channel shown in Fig. 1 chain lines with 45° angle, for different optical systems (such as viewing optical system, measurement optical system etc.) is coupled in same optical channel, thus realizing coaxial and common road.It is achieved thereby that change two optical windows of prior art into one.
As it is shown in figure 1, the first system 17 and second system 18 are arranged in capstan head body 1, the angle of central authorities' coupling mirror 2 and top optical axis is 45 °.Central authorities' coupling mirror 2 is made up of K9 optical glass, and the work surface after polishing is coated with total reflection film, and the through hole 21 in central authorities' coupling mirror 2 is track type, as shown in Figure 2.The via design of this central authorities' coupling mirror 2 is track type is that the radius of the two ends semicircle of this track type is 15mm, and the major axis of this track type is 43mm in order to make it horizontally and vertically be projected as circle on direction in FIG.
As shown in Figure 1, described inserted airborne photoelectric capstan head is contained within the first reflecting mirror the 3, second reflecting mirror the 121, the 3rd reflecting mirror 122 and the 4th reflecting mirror 123, first reflecting mirror 3 is parallel with the second reflecting mirror 121,3rd reflecting mirror 122 is parallel with the 4th reflecting mirror 123, angle between second reflecting mirror 121 and the 3rd reflecting mirror 122 is 90 °, and the angle between the 4th reflecting mirror 122 and central authorities' coupling mirror 2 is 90 °；Shown in the direction of arrow in Fig. 1, light can from the window 19 bottom trousers 16 enter described inserted airborne photoelectric capstan head and sequentially pass through first reflecting mirror the 3, second reflecting mirror the 121, the 3rd reflecting mirror 122 and the 4th reflecting mirror 123 back reflection to central authorities coupling mirror 2, then a part of light enters the first system 17 from through hole 21, and another light is reflected into second system 18 through central authorities' coupling mirror 2.
In order to realize the hemisphere spatial domain working range of this inserted airborne photoelectric capstan head, trousers 16 is contained within pitching slew gear, this pitching slew gear includes the pitching mirror unit 4 for installing the first reflecting mirror 3 and the pitching motor for driving the first reflecting mirror 3 to rotate, and this pitching motor can drive the first reflecting mirror 3 to rotate for axle ± 90 ° with horizontal direction through the optical axis of the first reflecting mirror 3.This pitching slew gear also includes hollow gyroaxis 6, hollow gyroaxis 6 is tubular, first reflecting mirror 3 and pitching mirror unit 4 are arranged in hollow gyroaxis 6, and described pitching motor can drive the first reflecting mirror 3, pitching mirror unit 4 and hollow gyroaxis 6 together to rotate for axle ± 90 ° with horizontal direction through the optical axis of the first reflecting mirror 3.
The barrel of hollow gyroaxis 6 is provided with the planar wave window mirror 5 corresponding with window 19, and light can sequentially pass through window 19 and plane optical window mirror 5 directive the first reflecting mirror 3.Planar wave window mirror 5 can rotate with hollow gyroaxis 6 one is logical, and such planar wave window mirror 5 can forward concealed location to when not working in order to avoid tarnishing.As it is shown in figure 1, this pitching slew gear also includes bearing 7, bearing block 8, pitch reference 9, drive mechanism 10 and control circuit 11.
In order to realize the hemisphere spatial domain working range of this inserted airborne photoelectric capstan head, trousers 16 is contained within orientation slew gear, this orientation slew gear includes for installing the second reflecting mirror 121, the orientation mirror unit 13 of the 3rd reflecting mirror 122 and the 4th reflecting mirror 123, i.e. the second reflecting mirror 121, the position of the 3rd reflecting mirror 122 and the 4th reflecting mirror 123 is relatively fixed, this orientation slew gear also includes azimuth-drive motor, this azimuth-drive motor can drive the second reflecting mirror 121 on orientation mirror unit 13, 3rd reflecting mirror 122, 4th reflecting mirror 123, pitching slew gear and trousers 16 together pass through the optical axis of central authorities' coupling mirror 2 for the rotation of 360 ° of axle with vertical direction.This orientation slew gear also includes hollow bearing 14, azimuth sensor 15, drive mechanism 22 and control circuit 11.This control circuit 11 is arranged in capstan head body 1.
Trousers 16 is lightweight carbon fibre composite.The bottom of trousers 16 be shaped as spherical crown, the height of this spherical crown is less than the radius of this spherical crown place spheroid.So when this inserted airborne photoelectric capstan head is installed on board the aircraft, revolution is steady, aeroperformance is good, and the impact of aircraft is little.
Due to just reversible, the first system 17 can be optical signal launch or the system of reception, the clear aperture of the first system 17 is 20mm, second system 18 can also be optical signal launch or the system of reception, the clear aperture of second system 18 is 80mm, and now being optical signal reception system for the first system 17 and second system 18 introduces the work process of this inserted airborne photoelectric capstan head.As shown in Figure 1, light arrives central authorities' coupling mirror 2 after being passed sequentially through planar wave window mirror the 5, first reflecting mirror the 3, second reflecting mirror the 121, the 3rd reflecting mirror the 122, the 4th reflecting mirror 124 by the direction of arrow, then a part of light enters the first system 17 from through hole 21, and another light is reflected into second system 18 through central authorities' coupling mirror 2.First reflecting mirror 3 can rotate for axle ± 90 ° with horizontal direction through the optical axis of the first reflecting mirror 3, for realize optical channel ± 90 ° of pitching scanning；First reflecting mirror the 3, second reflecting mirror the 121, the 3rd reflecting mirror 122 and the 4th reflecting mirror 123 together can pass through the optical axis of central authorities' coupling mirror 2 for the rotation of 360 ° of axle with vertical direction, for realizing the n × 360 ° azimuth scan of optical channel.
A kind of aircraft, this aircraft contains above-mentioned inserted airborne photoelectric capstan head, as shown in Figure 1, the capstan head body 1 of this inserted airborne photoelectric capstan head is arranged in this aircraft, capstan head body 1 is fixing with the wallboard 20 of this aircraft to be connected, and only the spherical bottom-exposed of trousers 16 is outside the wallboard 20 of this aircraft.
The above, be only specific embodiments of the invention, it is impossible to limits, with it, the scope that invention is implemented, so the displacement of its equivalent assemblies, or the equivalent variations made according to scope of patent protection of the present invention and modification, all should still fall within the category that this patent is contained.It addition, all can independent assortment use between technical characteristic and technical characteristic in the present invention, between technical characteristic and technical scheme, between technical scheme and technical scheme.
Claims (2)
1. an inserted airborne photoelectric capstan head, it is characterised in that described inserted airborne photoelectric capstan head includes capstan head body (1) and is arranged on the trousers (16) of capstan head body (1) bottom；
Described inserted airborne photoelectric capstan head is contained within the first system (17), second system (18) and central authorities' coupling mirror (2), central authorities' coupling mirror (2) are arranged between the camera lens of the first system (17) and the camera lens of second system (18), it is provided with through hole (21) in central authorities' coupling mirror (2), after light can enter described inserted airborne photoelectric capstan head from the window (19) of trousers (16) bottom and arrive central authorities' coupling mirror (2), a part of light enters the first system (17) from through hole (21), another light is reflected into second system (18) through central coupling mirror (2)；
The first system (17) and second system (18) are arranged in capstan head body (1), and the angle of central authorities' coupling mirror (2) and optical axis is 45 °；
The surface of central authorities' coupling mirror (2) is coated with total reflection film, and the through hole (21) in central authorities' coupling mirror (2) is track type；
Described inserted airborne photoelectric capstan head is contained within the first reflecting mirror (3), the second reflecting mirror (121), the 3rd reflecting mirror (122) and the 4th reflecting mirror (123), first reflecting mirror (3) is parallel with the second reflecting mirror (121), 3rd reflecting mirror (122) is parallel with the 4th reflecting mirror (123), angle between second reflecting mirror (121) and the 3rd reflecting mirror (122) is 90 °, and the angle between the 4th reflecting mirror (123) and central authorities' coupling mirror (2) is 90 °；
Light can enter described inserted airborne photoelectric capstan head from the window (19) of trousers (16) bottom and sequentially pass through the first reflecting mirror (3), the second reflecting mirror (121), the 3rd reflecting mirror (122) and the 4th reflecting mirror (123) back reflection extremely central authorities' coupling mirror (2)；
Trousers (16) is contained within pitching slew gear, this pitching slew gear includes the pitching mirror unit (4) for installing the first reflecting mirror (3) and is used for the pitching motor driving the first reflecting mirror (3) to rotate, and this pitching motor can drive the first reflecting mirror (3) to rotate for axle with horizontal direction through the optical axis of the first reflecting mirror (3)；
This pitching slew gear includes hollow gyroaxis (6), hollow gyroaxis (6) is tubular, first reflecting mirror (3) and pitching mirror unit (4) are arranged in hollow gyroaxis (6), and described pitching motor can drive the first reflecting mirror (3), pitching mirror unit (4) and hollow gyroaxis (6) together to rotate；
The barrel of hollow gyroaxis (6) is provided with the planar wave window mirror (5) corresponding with window (19), and light can sequentially pass through window (19) and plane optical window mirror (5) directive the first reflecting mirror (3)；
Trousers (16) is contained within orientation slew gear, this orientation slew gear includes the orientation mirror unit (13) for installing the second reflecting mirror (121), the 3rd reflecting mirror (122) and the 4th reflecting mirror (123), this orientation slew gear also includes azimuth-drive motor, and this azimuth-drive motor can drive the second reflecting mirror (121) on orientation mirror unit (13), the 3rd reflecting mirror (122), the 4th reflecting mirror (123) and described pitching slew gear together to rotate for axle with vertical direction through the optical axis of central authorities' coupling mirror (2)；
The bottom of trousers (16) be shaped as spherical crown, the height of this spherical crown is less than the radius of this spherical crown place spheroid.
2. an aircraft, it is characterized in that: this aircraft contains the inserted airborne photoelectric capstan head described in claim 1, the capstan head body (1) of this inserted airborne photoelectric capstan head is arranged in this aircraft, the bottom-exposed of trousers (16) this aircraft wallboard (20) outward.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410103099.8A CN103847975B (en) | 2014-03-19 | 2014-03-19 | A kind of inserted airborne photoelectric capstan head and aircraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410103099.8A CN103847975B (en) | 2014-03-19 | 2014-03-19 | A kind of inserted airborne photoelectric capstan head and aircraft |
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| CN103847975A CN103847975A (en) | 2014-06-11 |
| CN103847975B true CN103847975B (en) | 2016-07-27 |
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| CN201410103099.8A Active CN103847975B (en) | 2014-03-19 | 2014-03-19 | A kind of inserted airborne photoelectric capstan head and aircraft |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105484616B (en) * | 2015-12-07 | 2017-11-14 | 中国航空工业集团公司洛阳电光设备研究所 | A kind of capstan head optical window |
| CN105700131B (en) * | 2016-04-13 | 2017-12-19 | 北醒（北京）光子科技有限公司 | A kind of backsight optical scanner for robot |
| CN110068923B (en) * | 2019-04-24 | 2022-05-13 | 合肥鑫晟光电科技有限公司 | Dimming device, control method thereof and display system |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4729071A (en) * | 1986-11-03 | 1988-03-01 | Altman Stage Lighting Co. | Low-inertial beam direction lighting system |
| US5696637A (en) * | 1994-08-08 | 1997-12-09 | Reliance Electric Industrial Company | Apparatus for positioning an optical line of sight within a hemispheric region |
| CN101860684A (en) * | 2010-06-21 | 2010-10-13 | 福建福光数码科技有限公司 | Airborne turret with in-built CCD camera and forward looking infrared device and control system thereof |
| CN203259248U (en) * | 2013-03-07 | 2013-10-30 | 中国计量学院 | Portable colorimeter |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2863584B1 (en) * | 2003-12-12 | 2007-01-26 | Thales Sa | MODULAR OPTRONIC SYSTEM EMBARABLE ON A BEARER |
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2014
- 2014-03-19 CN CN201410103099.8A patent/CN103847975B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4729071A (en) * | 1986-11-03 | 1988-03-01 | Altman Stage Lighting Co. | Low-inertial beam direction lighting system |
| US5696637A (en) * | 1994-08-08 | 1997-12-09 | Reliance Electric Industrial Company | Apparatus for positioning an optical line of sight within a hemispheric region |
| CN101860684A (en) * | 2010-06-21 | 2010-10-13 | 福建福光数码科技有限公司 | Airborne turret with in-built CCD camera and forward looking infrared device and control system thereof |
| CN203259248U (en) * | 2013-03-07 | 2013-10-30 | 中国计量学院 | Portable colorimeter |
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Address after: 100024 North East military villa, eight Li bridge, Chaoyang District, Beijing Patentee after: China Institute of Aeronautical Manufacturing Technology Address before: 100024 North East military villa, eight Li bridge, Chaoyang District, Beijing Patentee before: Beijing Aviation Manufacturing Engineering Institute of China Aviation Industry Group Company |
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