Night vision imaging system design, integration and verification in spacecraft vacuum thermal test

Yonghong Shang D.D.S.; Jing Wang; Zhe Gong; Xiyuan Li; Yifei Pei; Tingzhu Bai; Haijing Zhen

doi:10.1117/12.2190815

5 August 2015 Night vision imaging system design, integration and verification in spacecraft vacuum thermal test

Yonghong Shang D.D.S., Jing Wang, Zhe Gong, Xiyuan Li, Yifei Pei, Tingzhu Bai, Haijing Zhen

Proceedings Volume 9622, 2015 International Conference on Optical Instruments and Technology: Optoelectronic Imaging and Processing Technology; 96220I (2015) https://doi.org/10.1117/12.2190815
Event: International Conference on Optical Instruments and Technology 2015, 2015, Beijing, China

Abstract

The purposes of spacecraft vacuum thermal test are to characterize the thermal control systems of the spacecraft and its component in its cruise configuration and to allow for early retirement of risks associated with mission-specific and novel thermal designs. The orbit heat flux is simulating by infrared lamp, infrared cage or electric heater. As infrared cage and electric heater do not emit visible light, or infrared lamp just emits limited visible light test, ordinary camera could not operate due to low luminous density in test. Moreover, some special instruments such as satellite-borne infrared sensors are sensitive to visible light and it couldn’t compensate light during test. For improving the ability of fine monitoring on spacecraft and exhibition of test progress in condition of ultra-low luminous density, night vision imaging system is designed and integrated by BISEE. System is consist of high-gain image intensifier ICCD camera, assistant luminance system, glare protect system, thermal control system and computer control system. The multi-frame accumulation target detect technology is adopted for high quality image recognition in captive test. Optical system, mechanical system and electrical system are designed and integrated highly adaptable to vacuum environment. Molybdenum/Polyimide thin film electrical heater controls the temperature of ICCD camera. The results of performance validation test shown that system could operate under vacuum thermal environment of 1.33×10^-3Pa vacuum degree and 100K shroud temperature in the space environment simulator, and its working temperature is maintains at 5℃ during two-day test. The night vision imaging system could obtain video quality of 60lp/mm resolving power.

Citation Download Citation

Yonghong Shang D.D.S., Jing Wang, Zhe Gong, Xiyuan Li, Yifei Pei, Tingzhu Bai, and Haijing Zhen "Night vision imaging system design, integration and verification in spacecraft vacuum thermal test", Proc. SPIE 9622, 2015 International Conference on Optical Instruments and Technology: Optoelectronic Imaging and Processing Technology, 96220I (5 August 2015); https://doi.org/10.1117/12.2190815

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KEYWORDS

Imaging systems

Control systems

Night vision

Cameras

Space operations

Infrared radiation

Computing systems

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