Abstract The ZDPS-1A pico-satellite, developed by the Zhejiang University, is featured with a three-axis stabilizing capability. It is 15×15×15cm3 cube-shaped satellite with a total mass of 3.5kg. ZDPS-1A is the first pico-satellite that has been launched successfully in China. The mission of ZDPS-1A is on-orbit system verification of student-build pico-satellite and wide range earth observation with a micro panoramic camera. A miniature momentum wheel is employed to offer gyro stiffness stability in the pitch (orbit normal) axis. Magnetic coils are employed to generate control torques to achieve the three-axis stabilization of nadir-pointing. The attitude sensors employed in the design include two three-axis magnetometers (TAMs), a three-axis gyro, and two sun sensors. Both ground simulations and on-orbit testing are conducted to verify the feasibility of the given attitude determination and control system (ADCS).

    Highlights ► This paper introduces a pico-satellite ZDPS-1A developed from Zhejiang University. ► The performance of the pico-satellite ZDPS-1A was tested on orbit. ► The control accuracy of the pico-satellite ZDPS-1A has reached to within 2°. ► Clear earth image was transmitted by a panoramic CMOS camera. ► On-orbit results verify the realization of nadir pointing three-axis stabilization.


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    Titel :

    Design and on-orbit performance of the attitude determination and control system for the ZDPS-1A pico-satellite


    Beteiligte:
    Xiang, Tian (Autor:in) / Meng, Tao (Autor:in) / Wang, Hao (Autor:in) / Han, Ke (Autor:in) / Jin, Zhong-He (Autor:in)

    Erschienen in:

    Acta Astronautica ; 77 ; 182-196


    Erscheinungsdatum :

    2012-03-27


    Format / Umfang :

    15 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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