CN102707548A - Integrated double-line-array spatial remote sensing and mapping camera - Google Patents
Integrated double-line-array spatial remote sensing and mapping camera Download PDFInfo
- Publication number
- CN102707548A CN102707548A CN2012101768137A CN201210176813A CN102707548A CN 102707548 A CN102707548 A CN 102707548A CN 2012101768137 A CN2012101768137 A CN 2012101768137A CN 201210176813 A CN201210176813 A CN 201210176813A CN 102707548 A CN102707548 A CN 102707548A
- Authority
- CN
- China
- Prior art keywords
- viewing
- camera
- assembly
- stravismus
- face
- 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.)
- Pending
Links
Images
Abstract
The invention relates to an integrated double-line-array spatial remote sensing and mapping camera, belonging to the field of an optical precision machine. The device comprises a hood, a forward-viewing off-axis three-mirror reflective camera, an oblique-viewing off-axis three-mirror reflective camera, a bearing cylinder, a rear framework and a front framework; the forward-viewing off-axis three-mirror reflective camera comprises a forward-viewing secondary mirror component, a forward-viewing focusing mechanism component, a forward-viewing primary mirror component, a forward-viewing third mirror component and a forward-viewing image plane component; and the oblique-viewing off-axis three-mirror reflective camera comprises an oblique-viewing image plane component, an oblique-viewing third mirror component, an oblique-viewing primary mirror component, an oblique-viewing focusing mechanism component and an oblique-viewing secondary mirror component. By adopting the integrated double-line-array spatial remote sensing and mapping camera, the stability of the intersection angle of the aerial remote sensing and mapping camera can be ensured by the camera instead of a camera bracket, the transfer procedures in the coordinate system of the optical system can be reduced, the accuracy can be ensured, and the size and mass can be decreased greatly. In addition, due to the design of the common light inlet, part of the size and weight are reduced, the cost of launching and satellite operation is reduced, and the effects of the payload are improved.
Description
Technical field
The invention belongs to space optics precision optical machinery field, relate to a kind of integrated two linear array space remote sensing mapping cameras.
Background technology
Along with developing rapidly of space remote sensing surveying and mapping technology; The engineer's scale of space remote sensing mapping camera is increasing, and the focal length of mapping camera, fabric width, volume and weight all significantly increase, and the precision of mapping camera is also increasingly high; This stability to camera imaging quality and camera internal position element, camera intersection angle has proposed stricter requirement; The present invention just to this technical barrier, has invented incorporate two linear array space remote sensing mapping cameras, has effectively solved the requirement of large scale spacer remote sensing mapping camera elements of interior orientation and camera intersection angle stability through the present invention; And the volume weight of camera greatly reduces, and is convenient to the engineering practical application.
According to the difference of structure as mode; Mapping camera can be divided into single line battle array, two linear arrays, three kinds of forms of three linear arrays; And need being fixed into certain angle with two to three camera lenses through a carrier-camera support, general large scale two linear arrays and three line-scan digital cameras are carried out to picture; Obtain stereogram, and fixing carrier angle relation stable between the camera need be guaranteed, otherwise mapping precision will be influenced.As depicted in figs. 1 and 2, the CARTOSAT-I of India (having another name called IRS P5) satellite all is to fix many cameras through camera support with the ALOS three linear array satellites of Japan.Need angle precision index between the rigidity height, good stability, camera of camera support at 1 second even higher through the camera support fixed camera, so cannot say for sure card.
Summary of the invention
In order to solve the problem that exists in the prior art; The invention provides a kind of integrated two linear array space remote sensing mapping cameras; This camera through two shared light inlets of optical system, is loaded in two relative arranged crosswise of optical systems difference in the airframe structure with two optical systems.
The technical scheme that technical solution problem of the present invention is adopted is following:
Integrated two linear array space remote sensing mapping cameras, this camera comprises: light shield, face from axle three anti-phase machines, stravismus from axle three anti-phase machines, loaded cylinder, afterframe and front baffle; Face from axle three anti-phase machines and comprise: face time mirror assembly, face the focus adjusting mechanism assembly, face the primary mirror assembly, face the 3rd mirror assembly, face the image planes assembly; Stravismus comprises from axle three anti-phase machines: stravismus image planes assembly, stravismus the 3rd mirror assembly, stravismus primary mirror assembly, stravismus focus adjusting mechanism assembly, stravismus time mirror assembly; Light shield is connected with front baffle, faces time mirror assembly, faces the focus adjusting mechanism assembly, looks side ways the focus adjusting mechanism assembly and look side ways time mirror assembly to be fixed on the front baffle; Front baffle be buckled in loaded cylinder above; Face the primary mirror assembly, face the 3rd mirror assembly, face the image planes assembly, stravismus image planes assembly, stravismus the 3rd mirror assembly and stravismus primary mirror assembly be fixed on the afterframe, afterframe is fixed on the bottom surface of loaded cylinder.
Inventive principle: the characteristics that axle three anti-phase facility have off-axis angle are left in utilization of the present invention, two relative arranged crosswise of optical systems difference, through two shared light inlets of optical system, two optical systems are loaded in the airframe structure.
The invention has the beneficial effects as follows: the integrated space remote sensing camera airframe structure of the present invention device, make the intersection angle stability of spacer remote sensing mapping camera guarantee to become camera body self assurance by camera support, reduced the transmission link of optical system coordinate system; Precision is able to guarantee, and owing to reduced this assembly of camera support, and volume and quality lower greatly that (general camera support need account for 1/4 of volume; Quality about 1/5); In addition because light inlet design altogether reduces a part of volume and weight again, through this invention; Reduce the cost of emission and satellite transit, improved the effect of useful load.
Description of drawings
The CARTOSAT-I satellite of India in Fig. 1 background technology.
The ALOS three linear array satellites of Japan in Fig. 2 background technology.
The integrated space remote sensing camera airframe structure of Fig. 3 the present invention device embodiment device structural drawing.
The integrated space remote sensing camera airframe structure of Fig. 4 the present invention device embodiment front baffle vertical view.
The integrated space remote sensing camera airframe structure of Fig. 5 the present invention device embodiment afterframe upward view.
Among the figure: 1, light shield, 2, face the camera light path, 3, face time mirror assembly, 4, face the focus adjusting mechanism assembly; 5, loaded cylinder, 6, face the primary mirror assembly, 7, face the 3rd mirror assembly, 8, face the image planes assembly; 9, afterframe, 10, stravismus image planes assembly, 11, stravismus the 3rd mirror assembly, 12, stravismus primary mirror assembly; 13, diaphragm assembly, 14, the diaphragm reinforcement, 15, stravismus focus adjusting mechanism assembly; 16, stravismus time mirror assembly, 17, stravismus camera light path, 18, front baffle and 19, lightweight hole.
Embodiment
Below in conjunction with accompanying drawing and embodiment the present invention is explained further details.
As shown in Figure 3, integrated two linear array space remote sensing mapping cameras, this device comprises: light shield 1, face from axle three anti-phase machines, stravismus from axle three anti-phase machines, loaded cylinder 5, afterframe 9 and front baffle 18; Face from axle three anti-phase machines and comprise: face time mirror assembly 3, face focus adjusting mechanism assembly 4, face primary mirror assembly 6, face the 3rd mirror assembly 7, face image planes assembly 8; Stravismus comprises from axle three anti-phase machines: stravismus image planes assembly 10, stravismus the 3rd mirror assembly 11, stravismus primary mirror assembly 12, stravismus focus adjusting mechanism assembly 15, stravismus time mirror assembly 16;
In the present embodiment; Fixing two groups of optical systems in loaded cylinder 5, afterframe 9 and front baffle 18: face from axle three anti-phase machines, stravismus and leave axle three anti-phase machines, diaphragm reinforcement 14 and diaphragm assembly 13, diaphragm assembly 13 is fixed on the camera through diaphragm reinforcement 14.Light shield 1 is connected with front baffle 18, faces time mirror assembly 3, faces focus adjusting mechanism assembly 4, looks side ways focus adjusting mechanism assembly 15 and look side ways time mirror assembly 16 to be fixed on the front baffle 18; Front baffle 18 be buckled in loaded cylinder 5 above; Face primary mirror assembly 6, face the 3rd mirror assembly 7, face image planes assembly 8, stravismus image planes assembly 10, stravismus the 3rd mirror assembly 11 and stravismus primary mirror assembly 12 be fixed on the afterframe 9, afterframe 9 is fixed on the bottom surface of loaded cylinder 5.Face time mirror assembly 3, face focus adjusting mechanism assembly 4 and stravismus focus adjusting mechanism assembly 15, stravismus time mirror assembly 16 are fixed on the front baffle 18; Face primary mirror assembly 6, face the 3rd mirror assembly 7, face image planes assembly 8 and stravismus image planes assembly 10, stravismus the 3rd mirror assembly 11, stravismus primary mirror assembly 12 be fixed on the afterframe 9; Diaphragm assembly 13 is fixed on the fuselage internal frame 14.Two groups of relative arranged crosswise of optical system difference; Through two groups of shared light shields 1 of optical system, face camera light path 2 successively through facing primary mirror assembly 6, face time mirror assembly 3, diaphragm assembly 13, face the 3rd mirror assembly 7, facing focus adjusting mechanism assembly 4 and face image planes assembly 8; Stravismus camera light path 17 comprises through stravismus camera optics system successively: stravismus primary mirror assembly 12, stravismus time mirror assembly 16, diaphragm assembly 13, stravismus the 3rd mirror assembly 16, stravismus focus adjusting mechanism assembly 15 and stravismus image planes assembly 10.
Like Fig. 4 and shown in Figure 5; The lightweight hole 19 of front baffle 18 and afterframe 9 surface distributed different shapes; The weight of airframe structure device is reduced greatly; The fuselage ring material all adopts the programmable M40J carbon fibre composite of high rigidity, high strength, low-density and thermal expansivity, the group parts of two optical systems is connected be fixed up.
Claims (4)
1. integrated two linear array space remote sensing mapping cameras is characterized in that this camera comprises: light shield (1), face from axle three anti-phase machines, stravismus from axle three anti-phase machines, loaded cylinder (5), afterframe (9) and front baffle (18); Face from axle three anti-phase machines and comprise: face time mirror assembly (3), face focus adjusting mechanism assembly (4), face primary mirror assembly (6), face the 3rd mirror assembly (7), face image planes assembly (8); Stravismus comprises from axle three anti-phase machines: stravismus image planes assemblies (10), stravismus the 3rd mirror assembly (11), stravismus primary mirror assembly (12), stravismus focus adjusting mechanism assembly (15), stravismus time mirror assembly (16); Said light shield (1) is connected with front baffle (18), faces time mirror assembly (3), faces focus adjusting mechanism assembly (4), looks side ways focus adjusting mechanism assembly (15) and look side ways time mirror assembly (16) to be fixed on the front baffle (18); Front baffle (18) be buckled in loaded cylinder (5) above; Face primary mirror assembly (6), face the 3rd mirror assembly (7), face image planes assembly (8), stravismus image planes assemblies (10), stravismus the 3rd mirror assembly (11) with look side ways primary mirror assembly (12) and be fixed on the afterframe (9), afterframe (9) is fixed on the bottom surface of loaded cylinder (5).
2. integrated two linear array space remote sensing mapping cameras as claimed in claim 1 is characterized in that; Said camera also comprises: diaphragm assembly (13) and diaphragm reinforcement (14); Diaphragm reinforcement (14) is fixed on the inside of loaded cylinder (5), and diaphragm assembly (13) is fixed on the camera through diaphragm reinforcement (14).
3. integrated two linear array space remote sensing mapping cameras as claimed in claim 1 is characterized in that; Lightweight hole (19) is distributing on said front baffle (18) and the afterframe (9).
4. integrated two linear array space remote sensing mapping cameras as claimed in claim 1 is characterized in that; Said this camera adopts the M40J carbon fibre composite to process.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012101768137A CN102707548A (en) | 2012-05-31 | 2012-05-31 | Integrated double-line-array spatial remote sensing and mapping camera |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012101768137A CN102707548A (en) | 2012-05-31 | 2012-05-31 | Integrated double-line-array spatial remote sensing and mapping camera |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102707548A true CN102707548A (en) | 2012-10-03 |
Family
ID=46900453
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012101768137A Pending CN102707548A (en) | 2012-05-31 | 2012-05-31 | Integrated double-line-array spatial remote sensing and mapping camera |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102707548A (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102879980A (en) * | 2012-10-12 | 2013-01-16 | 中国科学院长春光学精密机械与物理研究所 | Camera body structure for temperature adaptive space remote-sensing camera |
| CN103234528A (en) * | 2013-04-18 | 2013-08-07 | 中国科学院长春光学精密机械与物理研究所 | Two-linear array space mapping camera and laser altimeter integral device |
| CN104301590A (en) * | 2014-09-28 | 2015-01-21 | 中国科学院长春光学精密机械与物理研究所 | Three-lens detector array video acquisition device |
| CN105651261A (en) * | 2016-02-26 | 2016-06-08 | 中国科学院长春光学精密机械与物理研究所 | Double-planar-array three-dimensional plotting system based on minisatellite platform |
| CN105872334A (en) * | 2016-05-06 | 2016-08-17 | 上海航天测控通信研究所 | Aviation support integrated compact camera |
| CN108055503A (en) * | 2017-12-08 | 2018-05-18 | 中国科学院长春光学精密机械与物理研究所 | Satellite space self-timer |
| CN110529699A (en) * | 2019-08-29 | 2019-12-03 | 长光卫星技术有限公司 | The load cartridge type main supporting structure of large-scale off-axis three anti-space remote sensing camera |
| CN111929878A (en) * | 2020-07-10 | 2020-11-13 | 中国科学院西安光学精密机械研究所 | Off-axis three-mirror short-focus front objective lens system of hyperspectral imager |
| CN112255865A (en) * | 2020-10-30 | 2021-01-22 | 中国科学院长春光学精密机械与物理研究所 | Ultra-light carbon fiber remote sensing camera structure |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101303449A (en) * | 2008-07-10 | 2008-11-12 | 北京空间机电研究所 | Double-visual field off-axis three-mirror integrated type optical system for sharing primary and secondary lens |
-
2012
- 2012-05-31 CN CN2012101768137A patent/CN102707548A/en active Pending
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101303449A (en) * | 2008-07-10 | 2008-11-12 | 北京空间机电研究所 | Double-visual field off-axis three-mirror integrated type optical system for sharing primary and secondary lens |
Non-Patent Citations (2)
| Title |
|---|
| 郭疆: "离轴三反航天测绘相机研究", 《中国优秀硕士学位论文全文数据库工程科技第II辑》 * |
| 郭疆: "空间遥感相机碳纤维机身结构设计", 《光学精密工程》 * |
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102879980B (en) * | 2012-10-12 | 2015-09-09 | 中国科学院长春光学精密机械与物理研究所 | Temperature self-adaptation space remote sensing camera airframe structure |
| CN102879980A (en) * | 2012-10-12 | 2013-01-16 | 中国科学院长春光学精密机械与物理研究所 | Camera body structure for temperature adaptive space remote-sensing camera |
| CN103234528A (en) * | 2013-04-18 | 2013-08-07 | 中国科学院长春光学精密机械与物理研究所 | Two-linear array space mapping camera and laser altimeter integral device |
| CN103234528B (en) * | 2013-04-18 | 2015-04-22 | 中国科学院长春光学精密机械与物理研究所 | Two-linear array space mapping camera and laser altimeter integral device |
| CN104301590A (en) * | 2014-09-28 | 2015-01-21 | 中国科学院长春光学精密机械与物理研究所 | Three-lens detector array video acquisition device |
| CN104301590B (en) * | 2014-09-28 | 2017-06-09 | 中国科学院长春光学精密机械与物理研究所 | Three-lens detector array video acquisition device |
| CN105651261B (en) * | 2016-02-26 | 2018-03-13 | 中国科学院长春光学精密机械与物理研究所 | Two-sided battle array stereo mapping system based on small satellite platform |
| CN105651261A (en) * | 2016-02-26 | 2016-06-08 | 中国科学院长春光学精密机械与物理研究所 | Double-planar-array three-dimensional plotting system based on minisatellite platform |
| CN105872334A (en) * | 2016-05-06 | 2016-08-17 | 上海航天测控通信研究所 | Aviation support integrated compact camera |
| CN108055503A (en) * | 2017-12-08 | 2018-05-18 | 中国科学院长春光学精密机械与物理研究所 | Satellite space self-timer |
| CN110529699A (en) * | 2019-08-29 | 2019-12-03 | 长光卫星技术有限公司 | The load cartridge type main supporting structure of large-scale off-axis three anti-space remote sensing camera |
| CN110529699B (en) * | 2019-08-29 | 2021-06-29 | 长光卫星技术有限公司 | Bearing cylinder type main support structure of large off-axis three-mirror space remote sensing camera |
| CN111929878A (en) * | 2020-07-10 | 2020-11-13 | 中国科学院西安光学精密机械研究所 | Off-axis three-mirror short-focus front objective lens system of hyperspectral imager |
| CN111929878B (en) * | 2020-07-10 | 2021-07-27 | 中国科学院西安光学精密机械研究所 | Off-axis three-mirror short-focus front objective lens system of hyperspectral imager |
| CN112255865A (en) * | 2020-10-30 | 2021-01-22 | 中国科学院长春光学精密机械与物理研究所 | Ultra-light carbon fiber remote sensing camera structure |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102707548A (en) | Integrated double-line-array spatial remote sensing and mapping camera | |
| CN104635317A (en) | Light coaxial three-reflector spatial optical remote sensor structure | |
| CN103487920B (en) | Wide field image space telecentric optical system of three-line-array three-dimensional aerial survey camera | |
| JP2018531832A (en) | Satellite with imaging optics | |
| CN106516166B (en) | The isolated structure of satellite sound | |
| US3356002A (en) | Wide angle optical system | |
| CN103754378A (en) | Multi-lens aerial camera shooting stabilized platform | |
| Son et al. | A multiscale, wide field, gigapixel camera | |
| US20070152099A1 (en) | Onboard modular optronic system | |
| CN103487921B (en) | The three-dimensional aviation measuring camera optical system of Large visual angle high resolution three line scanner | |
| CN102890334A (en) | Day and night cat eye reconnaissance lens optical system | |
| CN105866936B (en) | A kind of airborne ultra-wide angle whole world face reflective optical system | |
| US8498055B2 (en) | Space telescope system | |
| JP6598405B2 (en) | Lens module | |
| US7145734B2 (en) | Windowed optical system having a tilted optical element to correct aberrations | |
| CN107783257B (en) | Large depth-of-field space radiation-resistant lens | |
| CN203681877U (en) | Camera fixing frame of multi-lens aerial photography stabilized platform | |
| CN213182265U (en) | Camera module for aerial photography instrument and aerial photography instrument | |
| Miravet et al. | Development status of the telescope for the Ingenio/SEOSAT mission primary payload | |
| CN109870805A (en) | A kind of Conformal Optical System and its design method based on multiple aperture | |
| CN213903945U (en) | Double fast reflecting mirror imaging system for compensating image motion | |
| CN101694539B (en) | Two-color optical system with ultra-large vision field and large aperture | |
| CN105243639B (en) | Image adjusting method, device and the system of the photoelectric nacelle of sleeping dress | |
| CN111025612B (en) | Low-cost and small-sized space remote sensing camera | |
| CN109856614B (en) | Satellite-borne laser radar optical axis pointing measurement system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20121003 |