Effects of the Eccentricity of a Perturbing Third Body on the Orbital Correction Maneuvers of a Spacecraft

Table 2

Time required by the low thrust maneuvers to correct the eccentricity.

Limit reached for Δ𝑒	Thrusting time Arc 1 (min)	Thrusting time for Arc 2 (min)	Thrusting time with 2 arcs (min)	Thrusting time with 1 arc (min)
0.0005	0.094	0.094	0.188	0.210
0.0010	0.188	0.188	0.376	0.419
0.0050	0.940	0.938	1.878	2.091
0.0100	1.89	1.89	3.78	4.22
0.0200	3.781	3.781	7.562	8.439
0.0500	9.497	9.497	18.994	21.285