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

Table 8

Debris removal sequence and timing for minimum Δ𝑉_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	6752.69	0.011	1	65	22.06	0.043	993.21
Nr. 3 reached	6978.16	0	−2	200	88.10	0.239	985.17
Nr. 3 de-orbited	6826.44	0.022	−2	200	25.96	0.084	980.63
Nr. 4 reached	7478.16	0	−1	90	66.71	0.476	964.88
Nr. 4 de-orbited	7055.54	0.053	−1	90	34.33	0.221	951.69
Nr. 5 reached	7178.16	0	0	45	55.89	0.241	943.91
Nr. 5 de-orbited	6912.18	0.034	0	45	30.77	0.144	931.48
Nr. 2 reached	7128.16	0	2	150	56.98	0.297	922.12
Nr. 2 de-orbited	6901.39	0.032	2	150	33.99	0.124	917.24