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

Table 5

Times when the limits are reached and fuel consumption per year of mission.

Eccentricity of the perturbing body	Time to reach the Δ𝑒 and Δ𝑖 limits (year)	Yearly consumption for impulsive maneuvers (kg)
𝑒^′=0.0	Δ𝑒=0.0005  full model = 22.82	0.0101
	Δ𝑒=0.001   full model = 34.78	0.0133
𝑒^′=0.1	Δ𝑒=0.0005   full model = 19.93	0.0116
	Δ𝑒=0.001   full model = 29.95	0.0154
𝑒^′=0.2	Δ𝑒=0.0005 full model = 4.76	0.0485
	Δ𝑒=0.001   full model = 6.71	0.0687
	Δ𝑒=0.005  full model = 16.62	0.1389
	Δ𝑒=0.01  full model = 26.08	0.1771