Effects of the Eccentricity of a Perturbing Third Body on the Orbital Correction Maneuvers of a Spacecraft
Table 9
Times when the limits are reached and the fuel consumption per year of mission assuming the value of 0.2 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 = 3.05 Single-averaged model = 3.37 Double-averaged model = 3.42
0.0757 0.0686 0.0675
Full model = 4.0 Single-averaged model = 4.78 Double-averaged model = 4.85
0.1153 0.0964 0.0951
Full model = 9.1 Single-averaged model = 10.77 Double-averaged model = 10.94
0.2536 0.2143 0.2110
Full model = 12.95 Single-averaged model = 15.18 Double-averaged model = 15.42
0.3567 0.3043 0.2995
Full model = 18.28 Single-averaged model = 21.01 Double-averaged model = 21.36
0.5060 0.4402 0.4330
Full model = 27.38 Single-averaged model = 30.74 Double-averaged model = 31.24
0.8477 0.7550 0.7430
Full model = 0.012 Single-averaged model = 0.008 Double-averaged model = 28.24
7.7667 11.650 0.0033
Full model = 27.5 Single-averaged model = 17.91 Double-averaged model = 35.71
