Dynamic De-Orbit Behaviors Of Nanosecond Laser Driving Small Scale Space Debris

The aim of this article was to address the dynamic de-orbit behaviors of space-based nanosecond laser driving small scale space debris based on different orbit and laser parameters. The de-orbit model of space-based laser irradiating small scale space debris was established. The dynamic de-orbit behaviors was simulated by analyzing two kinds of debris including aluminium alloy and carbon phenolic materials, and the effects of turn angle of main axis with laser pulse number were also discussed. Further, the rules of irradiating angle and irradiating distance with action time in different orbital inclination and right ascension of the ascending node (RAAN) were investigated for the carbon phenolic debris. Furthermore, the influences of the increment of perigee altitude with initial true anomaly were addressed in rotating or non-rotating state. Results shown that the de-orbit effect of carbon phenolic debris was better than that of aluminum alloy debris based on the same parameters, and the RAAN difference value between space-based platform and orbital plane of the debris was smaller, the less time it took for the laser to remove the debris. Especially, there is an optimal irradiation area when driving the debris in rotating and non-rotating state.