CN102262225A - Optical window used for space-optical remote-sensor thermal optical test - Google Patents
Optical window used for space-optical remote-sensor thermal optical test Download PDFInfo
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- CN102262225A CN102262225A CN2011101579179A CN201110157917A CN102262225A CN 102262225 A CN102262225 A CN 102262225A CN 2011101579179 A CN2011101579179 A CN 2011101579179A CN 201110157917 A CN201110157917 A CN 201110157917A CN 102262225 A CN102262225 A CN 102262225A
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Abstract
An optical window used for a space-optical remote-sensor thermal optical test belongs to the space-optical remote-sensor vacuum thermal test field. The optical window comprises: a base flange, a shell, an inner pressure plate, an outer pressure plate, inner window glass, outer window glass, a temperature measurement and control system, an electrical heating film, a temperature sensor, an air exhaust seat and a pressure gauge. By using the invention, a temperature of the optical window can be set according to different test temperatures so that the temperature of the optical window can be maintained in an ideal temperature range and influence of temperature fluctuation to the test can be effectively reduced. Inner and outer differential pressures of the window glasses can be changed at any time according to a demand. Window glass deformation caused by different air pressures can be furthest reduced. An electrical heating film is adopted in a heating device. Heat conductivity of a framework material is high and temperature uniformity is good. An automatic temperature control system is employed. After setting an object temperature before usage, people do not need to participate during a control process so that a function of automatic temperature adjustment can be realized.
Description
Technical field
The invention belongs to space optical remote sensor vacuum thermal test field, relate to optical detection optical window in a kind of space optical remote sensor thermal optical test.
Background technology
Space optical remote sensor is equipped on the spacecraft, usually is exposed to the outer space, is subjected to the effect of the various outer hot-fluids in space, and the space thermal environment is very abominable.In order to disclose the space thermal environment to the focus influence of coefficient, the hot spectrum relation of vacuum etc. of the hot optical performance parameter of optical sensor such as temperature, the examination space optical remote sensor is to the adaptive faculty of hot vacuum environment, promptly image planes inplace stability, focusing ability and image quality under hot vacuum environment need to carry out the ground level heat optical test before the complete machine emission.
Space simulator can provide comparatively really at the rail hot vacuum environment, is that optical sensor carries out the requisite test unit of ground level heat optical test.As the critical component on the space simulator, optical window is the essential passage of optical detection, and the machining precision of its optical glass and structural stability require all than higher.In thermal optical test, on the one hand optical window is directly in the face of space environmental simulation, when influenced by the simulator internal heat flows, also carries out heat interchange with participate in the experiment equipment, external environment condition etc. of inside.Optical window is bearing the stress that simulator external and internal pressure difference is brought on the other hand.Test shows, the not only Temperature Distribution of optical window in process of the test is uneven, and be subjected to the effect of inside and outside differential pressure, its variation in temperature distribution and pressure effect all can bring very important hot optical parallax to optical window, finally can influence the detection of optical sensor optical transfer function.
In sum, for the accuracy of detection that guarantees that thermal optical test can reach to be needed, optical window is to the influence of optical detection on the just necessary reduction space simulator.Therefore press for and a kind ofly can either satisfy purpose that the vacuum test space isolates, have enough good temperature stability simultaneously again to satisfy the optical window that optical transfer function detects.
Summary of the invention
To achieve these goals, the invention provides space optical remote sensor thermal optical test optical window.Be intended to solve in the thermal optical test optical window to the influence of optical detection, thereby provide technique guarantee for the reliability and the accuracy of space optical remote sensor thermal optical test.
Space optical remote sensor thermal optical test optical window comprises: basic flange, housing, clip plate, outer plate, interior window glass, outer window glass, temperature control system, electric heating film, temperature sensor, bleed seat, tensimeter; Described housing is connected with basic flange; The inner side end of described outer plate is connected with the outside end face of housing; Described outer window glass is connected with the inner side end of outer plate and the circumferential end surfaces of housing respectively; Window glass is connected with the inner side end of clip plate and the circumferential end surfaces of housing respectively in described; The inner side end of described clip plate is connected with the inner side end of housing; Described electric heating film and temperature sensor stick on housing and interior window glass, outer window is on glass is connected on the temperature control system; Described temperature control system is installed on the basic flange; The described seat of bleeding is installed on the housing, interior window glass and outside between the window glass; Described tensimeter is connected on the seat of bleeding.
In process of the test, the present invention can set the temperature of optical window according to the different tests temperature, and optical window is remained in the desirable temperature range, effectively reduces the influence of temperature fluctuation to detecting; Can change pressure reduction inside and outside the window glass at any time according to demand, reduce to greatest extent because the window glass distortion that the air pressure difference causes; Heating arrangement adopts electric heating film, frame material temperature conductivity height, and temperature homogeneity is good; Adopt the automatic temperature-adjusting control system, set target temperature before the use after, control procedure participates in without the people, has realized the function of automatic temperature-control.
Description of drawings
Fig. 1 is the front view of space optical remote sensor thermal optical test of the present invention with optical window.
Fig. 2 is space optical remote sensor thermal optical test of the present invention is installed outer cover with optical window a side cutaway view.
Fig. 3 is the main pseudosection of space optical remote sensor thermal optical test of the present invention with optical window.
As shown in the figure: 1, interior protective cover, 2, outer protective cover, 3, basic flange, 4, first sealing gasket; 5, multilayer insulation pad, 6, hoisting ring, 7, housing, 8, clip plate; 9, outer plate, 10, interior window glass, 11, outer window glass, 12, second sealing gasket; 13, temperature control system, 14, electric heating film, 15, temperature sensor, 16, the seat of bleeding; 17, the 3rd sealing gasket, 18, vacuum pump, 19, tensimeter; 20, gland, the 21, the 4th sealing gasket, 22, electric connector.
Embodiment
Space optical remote sensor thermal optical test optical window such as Fig. 1, Fig. 2 and shown in Figure 3, this device comprises: basic flange 3, housing 7, clip plate 8, outer plate 9, interior window glass 10, outer window glass 11, temperature control system 13, electric heating film 14, temperature sensor 15, bleed seat 16, tensimeter 19.
Interior protective cover 1 and outer protective cover 2 are installed on the two ends of housing 7 respectively; Basis flange 3 is connected with external device (ED) by first sealing gasket 4; The inner side end of outer plate 9 adopts screw to be connected with the outside end face of housing 7; Outer window glass 11 is connected with the inner side end of outer plate 9 and the circumferential end surfaces of housing 7 by second sealing gasket 12; Interior window glass 10 is connected with the inner side end of clip plate 8 and the circumferential end surfaces of housing 7 by second sealing gasket 12; The inner side end of clip plate 8 adopts screw to be connected with the inner side end of housing 7; Be connected by multilayer insulation pad 5 between housing 7 and the basic flange 3; Hoisting ring 6 is installed in respectively on basic flange 3 and the housing 7.
The seat 16 of bleeding is installed on the housing 7 by the 3rd sealing gasket 17, interior window glass 10 and outside between the window glass 11; Tensimeter 19 be connected to bleed the seat 16 on, gland 20 with bleed the seat 16 between the employing the 4th sealing gasket 21 be connected; Vacuum pump 18 is not connected with optical window, at first open gland 20 during use, remove the 4th sealing gasket 21 backs by the seat 16 of bleeding, confined space between the inside and outside window glass is full of the nitrogen of dry cleansing, then vacuum pump 18 is connected on the seat 16 of bleeding, indication by tensimeter 19 maintains ideal range with the air pressure in the optical window, at last the 4th sealing gasket 21 is recovered, compress gland 20, vacuum pump 18 is used to vacuumize, but vacuum pump is not directly installed on the optical window as the standing assembly of optical window.
In the process of the test, by temperature control system 13 the ideal temperature level and the thermograde desired value of optical window are set, take automated closed-loop control, entire test need not testing crew and gets involved.
Claims (10)
1. space optical remote sensor thermal optical test optical window, it is characterized in that this device comprises: basic flange (3), housing (7), clip plate (8), outer plate (9), interior window glass (10), outer window glass (11), temperature control system (13), electric heating film (14), temperature sensor (15), bleed seat (16), tensimeter (19); Described housing (7) is connected with basic flange (3); The inner side end of described outer plate (9) is connected with the outside end face of housing (7); Described outer window glass (11) is connected with the inner side end of outer plate (9) and the circumferential end surfaces of housing (7) respectively; Window glass (10) is connected with the inner side end of clip plate (8) and the circumferential end surfaces of housing (7) respectively in described; The inner side end of described clip plate (8) is connected with the inner side end of housing (7); Described electric heating film (14) and temperature sensor (15) stick on housing (7) and interior window glass (10), the outer window glass (11) and are connected on the temperature control system (13); Described temperature control system (13) is installed on the basic flange (3); The described seat (16) of bleeding is installed on the housing (7), is positioned between window glass (10) and the outer window glass (11); Described tensimeter (19) is connected on the seat (16) of bleeding.
2. space optical remote sensor thermal optical test optical window according to claim 1 is characterized in that, the two ends of described housing (7) are installed interior protective cover (1) and outer protective cover (2) respectively.
3. space optical remote sensor thermal optical test optical window according to claim 1 is characterized in that, described basic flange (3) is connected with external device (ED) by first sealing gasket (4).
4. space optical remote sensor thermal optical test optical window according to claim 1 is characterized in that, described outer window glass (11) is connected with the inner side end of outer plate (9) and the circumferential end surfaces of housing (7) by second sealing gasket (12).
5. space optical remote sensor thermal optical test optical window according to claim 1 is characterized in that, described interior window glass (10) is connected with the inner side end of clip plate (8) and the circumferential end surfaces of housing (7) by second sealing gasket (12).
6. space optical remote sensor thermal optical test optical window according to claim 1 is characterized in that, is connected by multilayer insulation pad (5) between described housing (7) and the basic flange (3).
7. space optical remote sensor thermal optical test optical window according to claim 1 is characterized in that, on described basic flange (3) and the housing (7) hoisting ring (6) is installed respectively.
8. space optical remote sensor thermal optical test optical window according to claim 1, it is characterized in that, described electric heating film (14) and temperature sensor (15) stick on housing (7) and interior window glass (10), the outer window glass (11), all are connected on the temperature control system (13) by electric connector (22).
9. space optical remote sensor thermal optical test optical window according to claim 1 is characterized in that, the described seat (16) of bleeding is gone up and connected vacuum pump (18), is installed on the housing (7) by the 3rd sealing gasket (17).
10. space optical remote sensor thermal optical test optical window according to claim 1 is characterized in that described optical window also comprises gland (20), and bleeding, employing the 4th sealing gasket (21) is connected between seat (16) and the gland (20).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011101579179A CN102262225A (en) | 2011-06-13 | 2011-06-13 | Optical window used for space-optical remote-sensor thermal optical test |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011101579179A CN102262225A (en) | 2011-06-13 | 2011-06-13 | Optical window used for space-optical remote-sensor thermal optical test |
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| CN102262225A true CN102262225A (en) | 2011-11-30 |
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| CN2011101579179A Pending CN102262225A (en) | 2011-06-13 | 2011-06-13 | Optical window used for space-optical remote-sensor thermal optical test |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103278904A (en) * | 2013-05-16 | 2013-09-04 | 中国科学院长春光学精密机械与物理研究所 | Method and device for implementing vacuum high-precision window |
| CN105675323A (en) * | 2016-01-15 | 2016-06-15 | 北京空间飞行器总体设计部 | Method for ground test of heat stability of satellite structure |
| CN107144936A (en) * | 2017-06-26 | 2017-09-08 | 中国科学院光电技术研究所 | Processing method of optical window in differential pressure environment |
| CN107782537A (en) * | 2017-12-01 | 2018-03-09 | 中国科学院长春光学精密机械与物理研究所 | A kind of vacuum Systems for optical inspection |
| CN108572152A (en) * | 2017-03-10 | 2018-09-25 | 罗伯特·博世有限公司 | Optical sensor with lining sensor |
| CN108760631A (en) * | 2018-05-24 | 2018-11-06 | 中国人民解放军陆军沈阳军事代表局驻长春地区军事代表室 | A kind of optical window with temperature self-adaptation function |
| CN108801594A (en) * | 2018-05-24 | 2018-11-13 | 中国人民解放军陆军沈阳军事代表局驻长春地区军事代表室 | A kind of boundary temperature condition photo electric imaging system image quality quantitative evaluation device |
| CN109041307A (en) * | 2018-06-25 | 2018-12-18 | 哈尔滨工程大学 | A kind of Multifunction infrared window camera lens |
| CN111405687A (en) * | 2020-03-30 | 2020-07-10 | 中国科学院西安光学精密机械研究所 | Temperature control device and method for optical window of space environment simulator |
| JP2020153924A (en) * | 2019-03-22 | 2020-09-24 | 株式会社デンソー | Range finder |
| CN113405773A (en) * | 2021-06-02 | 2021-09-17 | 中国科学院长春光学精密机械与物理研究所 | Space optical load outgassing test device and test method |
| CN114637092A (en) * | 2022-03-10 | 2022-06-17 | 西安应用光学研究所 | Defrosting and demisting multispectral optical window device for high-low temperature test chamber |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002066300A (en) * | 2000-08-30 | 2002-03-05 | Keio Gijuku | Simple vacuum window frame using quick coupling and vacuum device |
| CN101620315A (en) * | 2009-08-10 | 2010-01-06 | 浙江大学 | Electronic endoscope image pick-up device |
| CN101866039A (en) * | 2010-07-29 | 2010-10-20 | 哈尔滨工业大学 | High and low temperature resistant medium wave infrared optical window and manufacturing method thereof |
-
2011
- 2011-06-13 CN CN2011101579179A patent/CN102262225A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002066300A (en) * | 2000-08-30 | 2002-03-05 | Keio Gijuku | Simple vacuum window frame using quick coupling and vacuum device |
| CN101620315A (en) * | 2009-08-10 | 2010-01-06 | 浙江大学 | Electronic endoscope image pick-up device |
| CN101866039A (en) * | 2010-07-29 | 2010-10-20 | 哈尔滨工业大学 | High and low temperature resistant medium wave infrared optical window and manufacturing method thereof |
Non-Patent Citations (3)
| Title |
|---|
| 吴清文等: "空间光学遥感器热分析", 《光学精密工程》 * |
| 杨洪波: "航天密封窗口安全可靠性缩比实验计算机仿真", 《光学精密工程》 * |
| 王建设: "空间光学遥感器热平衡试验装置的设计", 《光学精密工程》 * |
Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103278904B (en) * | 2013-05-16 | 2016-01-20 | 中国科学院长春光学精密机械与物理研究所 | A kind of implementation method of vacuum high-precision window and device thereof |
| CN103278904A (en) * | 2013-05-16 | 2013-09-04 | 中国科学院长春光学精密机械与物理研究所 | Method and device for implementing vacuum high-precision window |
| CN105675323A (en) * | 2016-01-15 | 2016-06-15 | 北京空间飞行器总体设计部 | Method for ground test of heat stability of satellite structure |
| CN108572152A (en) * | 2017-03-10 | 2018-09-25 | 罗伯特·博世有限公司 | Optical sensor with lining sensor |
| CN107144936A (en) * | 2017-06-26 | 2017-09-08 | 中国科学院光电技术研究所 | Processing method of optical window in differential pressure environment |
| CN107144936B (en) * | 2017-06-26 | 2020-01-10 | 中国科学院光电技术研究所 | Processing method of optical window in differential pressure environment |
| CN107782537A (en) * | 2017-12-01 | 2018-03-09 | 中国科学院长春光学精密机械与物理研究所 | A kind of vacuum Systems for optical inspection |
| CN108760631B (en) * | 2018-05-24 | 2024-01-30 | 中国人民解放军陆军沈阳军事代表局驻长春地区军事代表室 | Optical window with temperature self-adaptation function |
| CN108760631A (en) * | 2018-05-24 | 2018-11-06 | 中国人民解放军陆军沈阳军事代表局驻长春地区军事代表室 | A kind of optical window with temperature self-adaptation function |
| CN108801594A (en) * | 2018-05-24 | 2018-11-13 | 中国人民解放军陆军沈阳军事代表局驻长春地区军事代表室 | A kind of boundary temperature condition photo electric imaging system image quality quantitative evaluation device |
| CN108801594B (en) * | 2018-05-24 | 2024-04-30 | 中国人民解放军陆军沈阳军事代表局驻长春地区军事代表室 | Quantitative evaluation device for image quality of boundary temperature condition photoelectric imaging system |
| CN109041307A (en) * | 2018-06-25 | 2018-12-18 | 哈尔滨工程大学 | A kind of Multifunction infrared window camera lens |
| WO2020195678A1 (en) * | 2019-03-22 | 2020-10-01 | 株式会社デンソー | Distance measurement device |
| JP2020153924A (en) * | 2019-03-22 | 2020-09-24 | 株式会社デンソー | Range finder |
| CN111405687A (en) * | 2020-03-30 | 2020-07-10 | 中国科学院西安光学精密机械研究所 | Temperature control device and method for optical window of space environment simulator |
| CN113405773A (en) * | 2021-06-02 | 2021-09-17 | 中国科学院长春光学精密机械与物理研究所 | Space optical load outgassing test device and test method |
| CN114637092A (en) * | 2022-03-10 | 2022-06-17 | 西安应用光学研究所 | Defrosting and demisting multispectral optical window device for high-low temperature test chamber |
| CN114637092B (en) * | 2022-03-10 | 2024-04-30 | 西安应用光学研究所 | Defrosting and demisting multispectral optical window device for high-low temperature test box |
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Application publication date: 20111130 |