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Optimal direction and a process design of removing low Earth orbit debris with space-based laser
Received date: 2014-03-21
Revised date: 2014-10-23
Online 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)
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.
HAN Weihua , GAN Qingbo , HE Yang , YANG Xin . Optimal direction and a process design of removing low Earth orbit debris with space-based laser[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015 , 36(3) : 749 -756 . DOI: 10.7527/S1000-6893.2014.0295
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