低轨道轻质星载一体化空间光学遥感器的热设计

江帆; 吴清文; 刘巨; 李志来; 杨献伟; 于善猛

doi:10.3788/CO.20130602.0237

Volume 6 Issue 2

Apr. 2013

Turn off MathJax

Article Contents

Chinese Optics > 2013 > 6(2): 237-243.

JIANG Fan, WU Qing-wen, LIU Ju, LI Zhi-lai, YANG Xian-wei, YU Shan-meng. Thermal design of lightweight space remote sensor integrated with satellite in low earth orbit[J]. Chinese Optics, 2013, 6(2): 237-243. doi: 10.3788/CO.20130602.0237

Citation:

JIANG Fan, WU Qing-wen, LIU Ju, LI Zhi-lai, YANG Xian-wei, YU Shan-meng. Thermal design of lightweight space remote sensor integrated with satellite in low earth orbit[J]. Chinese Optics, 2013, 6(2): 237-243. doi: 10.3788/CO.20130602.0237

Citation:

PDF( 857 KB)

Thermal design of lightweight space remote sensor integrated with satellite in low earth orbit

doi: 10.3788/CO.20130602.0237

Changchun Institute of Optics, Fine mechanics and physics, Chinese Academy of Sciences, Changchun 130033, China

Received Date: 13 Nov 2012
Rev Recd Date: 17 Jan 2013
Publish Date: 10 Apr 2013

Abstract

Abstract

A thermal simulation was established according to sensor parameters and the mission requirements to accomplish the thermal design of a lightweight space remote sensor. Atomic oxygen resistant cloth was chosen as the outmost material to reduce the damage by the space environment approximating to the earth. For some satellite devices installed on the back frame of the remote sensor, the connections with high heat resistance were designed and heat insulators were used to eliminate the heat influence on the devices. The positions and powers of the heaters were distributed according to the remote sensor's structure characters. However, none radiator was set because of such small power and duty factor of the CCD components. Finally, the thermal design was certified by a thermal balance test. Three cases designed according to the orbit parameters and attitudes of the remote sensor were simulated and tested. The experiments show that the temperatures of frames and mirrors are (184) ℃ and (182) ℃, respectively, and the temperatures of the CCD components are lower than 30 ℃. The simulation analysis and the thermal balance test results both indicate that the thermal design is valid and content to the mission requirements.
- space remote sensor,
- Low Earth Orbit(LEO),
- thermal design

FullText(HTML)

References(1)

References

[1] 韩昌元.高分辨率空间相机的光学系统研究[J].光学精密工程,2008,16(11):2164-2172. HAN CH Y. Study on optical system of high resolution space camera[J]. Opt. Precision Eng.,2008,16(11):2164-2172.(in Chinese) [2] 杨献伟,吴清文,李书胜,等.低轨道低能量空间光学遥感器热设计[J].光学技术,2011,37(1):91-96. YANG X W,WU Q W,LI SH SH,et al.. Thermal design of a low-energy space optical remote sensor in LEO[J]. Optical Technique,2011,37(1):91-96.(in Chinese) [3] 闵桂荣,郭舜.航天器热控制[M].二版.北京:科学出版社,1998. MIN G R,GUO SH. Spacecraft Thermal Control[M]. 2nd ed. Beijing:Science Press,1998.(in Chinese) [4] 吴清文,卢泽生,卢锷.空间光学遥感器热分析[J].光学精密工程,2002,10(2):205-208. WU Q W,LU Z SH,LU E.Thermal analysis for a space optical remote sensor[J]. Opt. Precision Eng.,2002,10(2):205-208.(in Chinese) [5] 陈立恒,吴清文,卢锷,等.空间摄像机热设计[J].光学技术,2008,37(10):2039-2042. CHENG L H,WU Q W,LU E. Thermal design of space camera[J]. Optical Technique,2008,37(10):2039-2042.(in Chinese) [6] 吴雪峰,丁亚林,吴清文.临近空间光学遥感器热设计[J].光学精密工程,2010,18(5):1159-1164. WU X F,DING Y L,WU Q W. Thermal design for near space optical remote sensor[J]. Opt. Precision Eng.,2010,18(5):1159-1164.(in Chinese) [7] 于善猛,刘巨,杨劲松,等.离轴式空间光学遥感器的热设计及仿真研究[J].红外与激光工程,2011,40(8):1521-1525. YU S M,LIU J,YANG J S,et al..Thermal design and simulation for off-axis space optical remote sensor[J]. Infrared and Laser Eng.,2011,40(8):1521-1525.(in Chinese) [8] 贾学志,王栋,张雷,等.轻型空间相机调焦机构的优化设计与精度试验[J].光学精密工程,2011,19(8):1824-1831. JIA X ZH,WANG D,ZHANG L,et al.. Optimizing design and precision experiment of focusing mechanism in lightweight space camera[J]. Opt. Precision Eng.,2011,19(8):1824-1831.(in Chinese) [9] 杨献伟,吴清文,李书胜,等.空间光学遥感器设计[J].中国光学,2011,4(2):139-146. YANG X W,WU Q W,LI S S,et al.. Thermal design of space optical remote sensor[J]. Chinese Optics,2011,4(2):139-146.(in Chinese) [10] 贾阳,杨晓宁.飞船红外加热笼热设计方法研究[J].航天器工程,2004,13(2):52-56. JIA Y,YANG X N. A study of spacecraft infrared heating cage for[J]. Spacecraft Eng.,2004,13(2):52-56.(in Chinese)

Relative Articles

Supplements(0)

Cited By

Proportional views