Effects of the Eccentricity of a Perturbing Third Body on the Orbital Correction Maneuvers of a Spacecraft
Table 8
Times when the limits are reached and the fuel consumption per year of mission using the value of 0.1 for the eccentricity of the orbit of the perturbing body.
Limit reached
Time to reach the limit (year)
Yearly consumption for impulsive maneuvers (kg)
Full model = 3.29 Single-averaged model = 3.58 Double-averaged model = 3.58
0.0702 0.0645 0.0645
Full model = 4.61 Single-averaged model = 5.08 Double-averaged model = 5.08
0.1000 0.0907 0.0907
Full model = 10.38 Single-averaged model = 11.44 Double-averaged model = 11.46
0.2224 0.2017 0.2014
Full model = 14.68 Single-averaged model = 16.14 double-averaged model = 16.15
0.3146 0.2862 0.2860
Full model = 20.46 Single-averaged model = 22.35 Double-averaged model = 22.37
0.4521 0.4138 0.4135
Full model = 30.22 Single-averaged model = 32.68 Double-averaged model = 32.71
0.7680 0.7102 0.7096
Full model = 0.012 Single-averaged model = 0.009 Double-averaged model = 29.56
