Smart camera design and in-orbit commissioning of “Pujiang-1” satellite

  • role: First author第一作者
  • Affiliation:

    Beijing Institute of Space Mechanics & Electricity, Beijing 100190, China

  • Email:huang.wo6@gmail.com
  • Introduction:于生全(1978— ),男,高级工程师,研究方向为可见光遥感总体技术研究。E-mail:huang.wo6@gmail.com
YU Shengquan,  
  • role: Corresponding author通信作者
  • Affiliation:

    Beijing Institute of Space Mechanics & Electricity, Beijing 100190, China

  • Email:wohuangwei@126.com
  • Introduction:黄伟(1982— ),男,高级工程师,研究方向为遥感图像实时处理研究。E-mail:wohuangwei@126.com
HUANG Wei*,  
  • Affiliation:

    Beijing Institute of Space Mechanics & Electricity, Beijing 100190, China

CHU Bei,  
  • Affiliation:

    Beijing Institute of Space Mechanics & Electricity, Beijing 100190, China

HUANG Ying,  
  • Affiliation:

    Beijing Institute of Space Mechanics & Electricity, Beijing 100190, China

ZHANG Chao,  
  • Affiliation:

    Beijing Institute of Space Mechanics & Electricity, Beijing 100190, China

YU Bo,  
  • Affiliation:

    Beijing Institute of Space Mechanics & Electricity, Beijing 100190, China

ZHANG Peng,  
  • Affiliation:

    Beijing Institute of Space Mechanics & Electricity, Beijing 100190, China

LEI Wenping

resumen

" Pujiang-1” satellite was successfully launched by the ChangZheng-11 vehicle from the JiuQuan Satellite Launch Center, China on September 25, 2015. The camera subsystem is one of the key payloads of the " Pujiang-1” satellite. The optical system, the pointer mirror mechanism, and the electronics of the camera were designed and produced under the concept of integration and miniaturization, which led to the compact, small, and light weight structure of the camera. With the novel design of the off-axis three-mirror reflective optical system, the camera includeda larger field of view and higher MTF value without a cover compared with the traditional coaxial system. By optimizing the layout of the optical elements, small volume was achieved. The difficulty of mechanical design and alignment was also reduced by optimizing the tolerance of the optical system. Additionally, this optical system was designed without a focusing mechanism but it could still address imaging needs because the back focal length was insensitive to the spacing change of the mirror. The camera used the pointer mirror mechanism to realize multi-target rapid pointing, enabling the capturemulti-target in each single imaging cycle, thereby shortening reaction time and improving imaging efficiency. The pointer mirror mechanism adopted the motor and gear set drive mode. The photoelectric encoder was installed coaxially with the mirror, with which the point angle can be precisely and accurately measured. In the electronic part, several functions, such as video imaging, image compression and coding, remote telemetry, temperature control, and power supply and distribution were integrated into one device. Standard plug-and-play 1553B communication and small-shape high-speed SpaceWire transmission interfaces were adopted to achieve rapid assembly and testing equipment in line with the modular design trend. The integrated circuit design reduced the number of devices, the overall system volume, system weight, and power consumption. After the satellite operating in-orbit, the in-orbit commissioning process was optimized combined with user needs. All the test and evaluation work were completed within one month.The camera normallyoperated with superior performance until today. The successful development of this camera and in-orbit stable operation provides a strong technical support for the follow-up high-performance light and smart cameras.

palabra clave

off-axis three-mirror reflective;pointer mirror mechanism;highly-integrated electronic device design;in-orbit commissioning

References

  1. 1.
    Chang X, Zhang P, Li K, Shi C H and Sun Q G. 2014. Design of high precision control of space camera temperature controlling. Computer Measurement and Control, 22(7): 2274–2276
  2. 2.
    Chen D Y, Wang K and Li T. 2010. The design and implementation of space high-speed bus Spacewire codec. Spacecraft Recovery and Remote Sensing, 31(4): 58–64
  3. 3.
    Guo J C. 2009. Technical analysis of high resolution commercial optical remote sensing satellite. Spacecraft Engineering, 18(2): 83–89
  4. 4.
    Huang W, Wang X M and Yu S Q. 2014. Highly-integrated video processing FPGA software design of a remote sensing camera. Acta Electronica Sinica, 42(11): 2303–2309
  5. 5.
    Liu J G, Zhen L F and Tong Q X. 1999. Estimation of signal to noise ratio of remote sensing images. Journal of Basic Science and Engineering, 7(4): 360–365
  6. 6.
    Yao N. 2010. Development status of fast response satallite: architecture and key technologies // Proceedings of the 23rd Proceeding of National Conference on Space Exploration. Xiamen: China Space Science Society: 55–62
  7. 7.
    Yao T Y. 2015. Changzhen-11 rocket launched. Space Exploration(11): 28
  8. 8.
    Zhao Z P, Fu X K, Huang Q L and Li Y Q. 2009. On orbit MTF test research of remote sensors based on knife-edge method. Spacecraft Recovery and Remote Sensing, 30(2): 37–43

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