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

Table 1

Fuel consumption for the maneuvers to correct the eccentricity.

Δ𝑒	Impulse 1 (m/s)	Impulse 2 (m/s)	Total impulse for Δ𝑒 (m/s)	Fuel consumed (kg)	LT with 1 arc (kg)	Arc 1 LT (kg)	Arc 2 LT (kg)	Total LT with 2 arcs (kg)
0.0005	0.388	0.380	0.769	0.231	0.067	0.030	0.030	0.060
0.0010	0.777	0.761	1.537	0.461	0.135	0.060	0.060	0.120
0.0050	3.889	3.793	7.682	2.308	0.687	0.301	0.300	0.601
0.0100	7.793	7.563	15.356	4.619	1.350	0.605	0.605	1.210
0.0200	15.644	15.033	30.677	9.249	2.714	1.210	1.210	2.421
0.0500	39.547	36.904	76.451	23.210	6.779	3.040	3.040	6.080