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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2015, Vol. 36 ›› Issue (3): 749-756.doi: 10.7527/S1000-6893.2014.0295

• Fluid Mechanics and Flight Mechanics • Previous Articles     Next Articles

Optimal direction and a process design of removing low Earth orbit debris with space-based laser

HAN Weihua1,2,3, GAN Qingbo1, HE Yang1, YANG Xin1   

  1. 1. Academy of Opto-Electronics, Chinese Academy of Sciences, Beijing 100094, China;
    2. University of Chinese Academy of Sciences, Beijing 100049, China;
    3. Beijing Aerospace Flight Control Center, Beijing 100094, China
  • Received:2014-03-21 Revised:2014-10-23 Online:2015-03-15 Published:2015-03-31
  • Supported by:

    National Natural Science Foundation of China (11303029); Innovation Fund Chuying Program for Postgraduate by Academy of Opto-Electronics, Chinese Academy of Sciences (Y30B02A18Y)

Abstract:

To address the problem of how to remove low Earth orbit (LEO) debris with space-based high-powered pulse laser, a combined model of high-powered pulse laser ablation and variation of the debris' orbit element is advanced. By theoretical analysis, an expression of the single laser pulse's optimal interaction direction about the LEO debris' orbit element is derived, and the single laser pulse's optimal removal is proved to be mirror symmetric about the orbit major axis of debris. In consequence, aimed at optimizing both flight time of space platform and lasing time of laser, a simplified method of designing the removal process rapidly and effectively is brought out. The typical simulation and outcomes demonstrate that the optimal interaction direction is more efficient than others, and based on the simplified method, the lasing time of laser can be reduced by 30% with a 10% increase in space platform's flight time.

Key words: space debris removal, space-based laser, low Earth orbit debris, interaction direction, process design

CLC Number: