Preliminary Design of Debris Removal Missions by Means of Simplified Models for Low-Thrust, Many-Revolution Transfers

Table 9

Debris removal sequence and timing for minimum TOF_Tot.

Phase	Final Keplerian elements				Duration (days)	Δ𝑉 (km/s)	Mass (kg)
	𝑎 (km)	𝑒	𝑖 (deg)	Ω (deg)
Departure	6628.16	0.010	1	65	—	—	1000
Nr. 1 reached	6828.16	0	1	65	5	0.115	996.11
Nr. 1 de-orbited	6685.24	0.001	1	65	4.04	0.081	990.61
Nr. 3 reached	6978.16	0	−2	200	8.59	0.312	980.14
Nr. 3 de-orbited	6701.87	0.004	−2	200	6.29	0.154	971.87
Nr. 4 reached	7478.16	0	−1	90	14.79	0.664	950.17
Nr. 4 de-orbited	6789.06	0.016	−1	90	17.13	0.362	928.76
Nr. 5 reached	7178.16	0	0	45	7.99	0.281	919.92
Nr. 5 de-orbited	6715.72	0.006	0	45	15.9	0.252	898.39
Nr. 2 reached	7128.16	0	2	150	9.87	0.466	884.28
Nr. 2 de-orbited	6725.90	0.007	2	150	6.75	0.221	875.87