Fig. 1. Prediction of space debris collisions based on LEGEND model^[5]

Fig. 2. The US LDEF project and the collision morphology due to space debris

Fig. 3. Schematics for the collision of space debris with satellite

Fig. 4. Starlink project and the number of on-orbit satellites^[9]

Fig. 5. Impact test of Whipple shield structure

Fig. 6. Schematics of JAXA’s electrodynamic tethers and ESA’s net attached deorbit plan (JAXA: Japan Aerospace Exploration Agency)

Fig. 7. Schematics of ESA’s solar sail deorbit plan

Fig. 8. The LODR project and its ability in space debris removal^[21]

Fig. 9. DLR’s design and plan of laser removal of space debris

Fig. 10. Laser removal of space debris in JEM-EUSO program

Fig. 11. A classic illustration of space-based laser removal system

Fig. 12. The interaction of laser with space debris material

Fig. 13. The laser parameters for obtaining optimum impulse coupling coefficient for aluminum^[49]

Fig. 14. The variation of impulse coupling coefficient for aluminum with different laser energy density

Fig. 15. The variation of impulse coupling coefficient for carbon fiber material with different laser energy density

Fig. 16. The influence of pressure to the impulse coupling coefficient

Fig. 17. Holographic of plasma plume during laser irradiation

Fig. 18. Simulation results of plasma plume development

Fig. 19. Structure of model-based evaluation of laser removal of space debris

Fig. 20. The logic of data flow in the evaluation system

Fig. 21. The output user-interface for the evaluation system of laser removal of space debris