Development of low cost CCD camera for microsatellites

被引:0
|
作者
Zhou J. [1 ]
Chen X. [1 ]
Chen Y. [1 ]
Zhou W. [1 ]
Shen W. [1 ]
机构
[1] Jiangsu Key Laboratory of Modern Optical Technology, Institute of Modern Optical Technology, Soochow University, Suzhou
来源
Zhongguo Jiguang/Chinese Journal of Lasers | 2010年 / 37卷 / SUPPL. 1期
关键词
Catadioptric optical system; Commercial-off-the-sheft components; Microsatellite CCD camera; Reliability; Remote sensing;
D O I
10.3788/CJL201037s1.0120
中图分类号
学科分类号
摘要
The microsatellite has many advantages, such as shorter development cycle, higher mobility and lower cost than those of conventional satellites. It becomes a hot area of the remote sensing. The developing CCD camera is one of the most important payloads of the microsatellite and it has 0.98/0.5 year reliability rate at a low cost. The optical system adopts catadioptric structure with wide working temperature range and uses spherical-surfaces components which are fabricated and assembled easily. Stray light reduction and environmental adaptation design can further improve imaging capability of the system. The electric circuit system applies many new technologies such as frame transfer CCD, field programmable gate array (FPGA), correlated double sampling (CDS), low-voltage differential transferring (LVDS) and buck/boost voltage conversion, so the system has low cost, low power consumption and good stability. The commercial-off-the-sheft (COTS) components are screened by destructive physical analysis (DPA), additional screening, boarding tests and so on. The reasonable reliability methods are used in the developing process of the CCD camera. The CCD camera maintains good imaging performance in the environmental tests, calibration experiment and imaging capability tests.
引用
收藏
页码:120 / 125
页数:5
相关论文
共 10 条
  • [1] Sweeting M.N., Space at surrey: micro-mini-satellites for affordable access to space, Air & Space Europe, 2, 1, pp. 38-52, (2000)
  • [2] Fouquet M., Ward F., Cost-driven design of small satellite remote sensing systerm, J. Reducing Space Mission Cost, 2, 1, pp. 159-175, (1998)
  • [3] Teverovsky A., Sahu K., Instructions for plastic encapsulated microcircuit (PEM) selection, screening and qualification, pp. 212-244, (2003)
  • [4] Chen H., Zhu Z., Fu B., Et al., Design of companion microsat for observing the space target, J. Astronautics, 31, 2, pp. 229-334, (2010)
  • [5] You Z., Gong K., Butlin T., Et al., Tsinghua-1 microsatellite-demonstration of EO and disaster monitoring network, Proceedings of the International Symposium on Digital Earth (ISDE), (1999)
  • [6] Reliability prediction handbook for electronic equipment
  • [7] Wu G., Zhang X., Han C., Et al., Radiometric calibration of the space CCD camera, J. Test and Measurement Technology, 18, 4, pp. 325-329, (2004)
  • [8] Chen S., Space Camera Design and Test, pp. 329-331, (2003)
  • [9] Fan C., Yi H., Li Y., On the test target of MTF for the space camera, Electronics of Optics & Control, 14, 4, pp. 174-176, (2007)
  • [10] Wang J., Yu P., Yan C., Et al., Space optical remote sensor image motion velocity vector computation modeling, Acta Optica Sinica, 24, 12, pp. 1586-1589, (2004)