Abstract
The aim of this article was to address the de-orbit behaviors of space-based laser driving small scale space debris in low earth orbit (LEO) based on different orbit and laser parameters in coplanar/non-coplanar conditions. The de-orbit model of space-based laser irradiating small scale space debris was established, the de-orbit rules of irradiation angle and irradiation distance with action time in different orbital inclination and right ascension of the ascending node (RAAN) were investigated by numerical simulations, and the change rules of the perigee altitude with the number of laser pulses were discussed in different orbital inclination and RAAN. As a result, the clearance window of removing small scale space debris was described in detail. These results of numerical simulations will provide theoretical guide for designing clear schemes and selecting efficient parameters.
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