CN203882072U - Spatial infrared camera with visible light landmark navigation channel - Google Patents
Spatial infrared camera with visible light landmark navigation channel Download PDFInfo
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- CN203882072U CN203882072U CN201420145289.1U CN201420145289U CN203882072U CN 203882072 U CN203882072 U CN 203882072U CN 201420145289 U CN201420145289 U CN 201420145289U CN 203882072 U CN203882072 U CN 203882072U
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- infrared camera
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- 230000003287 optical effect Effects 0.000 claims abstract description 16
- 230000005499 meniscus Effects 0.000 claims abstract description 11
- 238000003331 infrared imaging Methods 0.000 claims abstract description 8
- 239000003550 marker Substances 0.000 claims description 21
- 238000003384 imaging method Methods 0.000 claims description 5
- VMXUWOKSQNHOCA-UKTHLTGXSA-N ranitidine Chemical compound [O-][N+](=O)\C=C(/NC)NCCSCC1=CC=C(CN(C)C)O1 VMXUWOKSQNHOCA-UKTHLTGXSA-N 0.000 claims description 3
- 239000000463 material Substances 0.000 claims description 2
- 230000007306 turnover Effects 0.000 claims 1
- 238000005259 measurement Methods 0.000 abstract description 3
- 238000001514 detection method Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000000007 visual effect Effects 0.000 description 2
- 230000032683 aging Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
Abstract
The utility model discloses a spatial infrared camera with a visible light landmark navigation channel. The spatial infrared camera includes a spatial infrared camera main optical system module, an infrared imaging channel module and a visible light landmark navigation channel module. The spatial infrared camera is characterized in that light from a ground object passes through the main optical system module and thereafter is divided into two line-field-of-view light paths, wherein one path enters the infrared imaging channel module so as to be imaged, and the other path enters the visible light landmark navigation channel module so as to be imaged; and the light that enters the visible light landmark navigation channel module is further reflected to a meniscus lens through a visible light reflector, and is converged through the meniscus lens and then is imaged to a visible light detector. According to the spatial infrared camera of the utility model, the visible light landmark navigation channel has landmark, spatial visible target and star target observation functions and the like, and therefore, the spatial infrared camera can perform in-orbit regular measurement of the pointing accuracy of an optical axis, and the image registration accuracy of the spatial infrared camera can be improved, and the stability of a system can be improved.
Description
Technical field
This patent relates to a kind of space infrared camera, particularly a kind of space infrared camera with visible ray ground marker navigation passage, and it is to have ground marker navigation, star observation function, realizes the space infrared camera that inflight measurement system optical axis is pointed to.
Background technology
Remote sensing satellite in orbit during, due to many reasons such as thermal deformation, sun optical pressure, ageing equipment, apparatus installation errors, cause the attitude of satellite (pitching, roll and driftage) change, thereby remote sensing space phase of infrared camera scanning is pointed to change thereupon, cause remote sensing satellite image to produce geometric distortion in various degree, finally to the quantitative product inverting of remote sensing and the raising of application of satellitic remote sensing effect and the performance of satellite overall performance generation significant impact.
Space infrared camera infrared imaging channel module 2 is subject to the restriction of spatial resolution, image registration accuracy is not high, for further improving the image registration accuracy of space infrared camera, meet the demand that inflight measurement space infrared camera optical axis points to, and realize visible ray target detection, and increase a visible ray ground marker navigation channel module 3.
Summary of the invention
In order to overcome above-mentioned the deficiencies in the prior art, this patent provides a kind of space infrared camera with visible ray ground marker navigation passage.By increasing High Resolution Visible Light ground marker navigation channel module 3, adopt the method for ground marker navigation to improve image registration accuracy, during revising in orbit, the optical axis of space infrared camera optical system points to deviation, is conducive to the adjustment of the attitude of satellite, ensures space remote sensing positioning precision.
The technical scheme that this patent adopts is: after primary optical system module 1, be divided into two linear field light paths from the light of atural object, a road enters 2 imagings of infrared imaging channel module, and another road enters visible ground marker navigation channel module 3 imagings; Enter the light of visible ray ground marker navigation module 3, by the visible ray catoptron 3-1 meniscus lens 3-2 that transfers, after meniscus lens 3-2 converges, be imaged onto on visible-light detector 3-3.
The material of described meniscus lens 3-2 is BK7, and front surface and rear surface are sphere.
Described visible-light detector 3-3 is visible ray TDI detector.
The beneficial effect of this patent is to increase visible ground marker navigation channel module 3, has expanded the range of application of infrared camera, obtains the function to visible ray target imaging, has improved image registration accuracy, has realized space infrared camera on-orbit calibration optical axis and has pointed to.
Brief description of the drawings
Fig. 1 is the space infrared camera schematic diagram with visible ground marker navigation passage.
Fig. 2 is space infrared camera visible light wave range ground marker navigation process flow diagram.
Embodiment
Below in conjunction with accompanying drawing, this patent is further illustrated.
As shown in Figure 1, this system comprises red watt of space camera primary optical system module 1, infrared imaging channel module 2, visible ray ground marker navigation channel module 3, visible ray catoptron 3-1, meniscus lens 3-2, visible-light detector 3-3.
This patent embodiment: the primary optical system module 1 of space infrared camera is from axle three antistructures, and focal length is 1000mm, and F number is 2, visual field is 15 ° × 2 °; Infrared imaging channel module 2 separates with visible ground marker navigation channel module 3 visual fields, and field angle is 5 °; After primary optical system, enter visible ray ground marker navigation module 3 from the light of atural object, upper by the visible ray catoptron 3-1 meniscus lens 3-2 that transfers, after meniscus lens 3-2 converges, be imaged onto on visible-light detector 3-3.On visible detector 3-3, obtain after remote sensing satellite image data, carry out image-guidance, cloud detection, obtains the rear data of navigation and cloud detection data; Now, suppose that attitude angle is zero, according to installation relation and the satellite orbit parameter of the scan mode of space camera, space camera and satellite, obtained remote sensing satellite image is carried out to geo-location, obtain the geographical longitude and latitude of terrestrial reference, calculate the difference of the geographical longitude and latitude of itself and terrestrial reference template database, carry out terrestrial reference coupling.Carry out attitude misalignment calculating by terrestrial reference side-play amount, obtain attitude of satellite angle, the optical axis that obtains camera points to, and the attitude of satellite is navigated again.
Claims (3)
1. there is a space infrared camera for visible ray ground marker navigation passage, comprise the primary optical system module (1) of space infrared camera, infrared imaging channel module (2) and visible ray ground marker navigation channel module (3); It is characterized in that: after primary optical system module (1) module, be divided into two linear field light paths from the light of atural object, a road enters infrared imaging channel module (2) imaging, and another road enters visible ground marker navigation channel module (3) imaging; Enter the light of visible ray ground marker navigation module (3),,, after meniscus lens (3-2) converges, be imaged onto on visible-light detector (3-3) to meniscus lens (3-2) by visible ray catoptron (3-1) turnover.
2. a kind of space infrared camera with visible ray ground marker navigation passage according to claim 1, is characterized in that: the material of meniscus lens (3-2) is BK7, and front surface and rear surface are sphere.
3. a kind of space infrared camera with visible ray ground marker navigation passage according to claim 1, is characterized in that: visible-light detector (3-3) is visible ray TDI detector.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420145289.1U CN203882072U (en) | 2014-03-28 | 2014-03-28 | Spatial infrared camera with visible light landmark navigation channel |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201420145289.1U CN203882072U (en) | 2014-03-28 | 2014-03-28 | Spatial infrared camera with visible light landmark navigation channel |
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| CN203882072U true CN203882072U (en) | 2014-10-15 |
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| CN201420145289.1U Expired - Lifetime CN203882072U (en) | 2014-03-28 | 2014-03-28 | Spatial infrared camera with visible light landmark navigation channel |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103913932A (en) * | 2014-03-28 | 2014-07-09 | 中国科学院上海技术物理研究所 | Space infrared camera with visible light landmark navigation channel |
| CN107121124A (en) * | 2017-05-19 | 2017-09-01 | 上海宇航系统工程研究所 | A kind of mechanical pointing accuracy method for fast measuring of satellite antenna |
| CN109084963A (en) * | 2018-08-02 | 2018-12-25 | 北京空间机电研究所 | A kind of remote sensor on-orbit calibration light source emission system |
-
2014
- 2014-03-28 CN CN201420145289.1U patent/CN203882072U/en not_active Expired - Lifetime
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103913932A (en) * | 2014-03-28 | 2014-07-09 | 中国科学院上海技术物理研究所 | Space infrared camera with visible light landmark navigation channel |
| CN107121124A (en) * | 2017-05-19 | 2017-09-01 | 上海宇航系统工程研究所 | A kind of mechanical pointing accuracy method for fast measuring of satellite antenna |
| CN107121124B (en) * | 2017-05-19 | 2019-05-28 | 上海宇航系统工程研究所 | A kind of satellite antenna machinery pointing accuracy method for fast measuring |
| CN109084963A (en) * | 2018-08-02 | 2018-12-25 | 北京空间机电研究所 | A kind of remote sensor on-orbit calibration light source emission system |
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