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

Table 7

Times when the limits are reached and the average yearly fuel consumption for the mission assuming a circular orbit for the perturbing body.

Limit reached	Time to reach the limit (year)	Yearly consumption for impulsive maneuvers (kg)
Δ𝑒=0.0005	Full model = 3.69; Single-averaged model = 3.65; Double-averaged model = 3.64	0.0626; 0.0633; 0.0635
Δ𝑒=0.001	Full model = 5.13; Single-averaged model = 5.16; Double-averaged model = 5.16	0.0899; 0.0893; 0.0893
Δ𝑒=0.005	Full model = 11.44; Single-averaged model = 11.63; Double-averaged model = 11.63	0.2017; 0.1985; 0.1985
Δ𝑒=0.01	Full model = 16.01; Single-averaged model = 16.40; Double-averaged model = 16.41	0.2885; 0.2816; 0.2815
Δ𝑒=0.02	Full model = 22.19; Single-averaged model = 22.70; Double-averaged model = 22.71	0.4168; 0.04074; 0.4073
Δ𝑒=0.05	Full model = 32.36; Single-averaged model = 33.20; Double-averaged model = 33.21	0.7172; 0.6991; 0.6989
Δ𝑖=0.0001	Full model = 0.012; Single-averaged model = 0.012; Double-averaged model = 30.013	7.7667; 7.7667; 0.0031
Δ𝑖=0.0005	Full model = 29.98; Single-averaged model = 32.15	0.0155; 0.0145