Effects of the Eccentricity of a Perturbing Third Body on the Orbital Correction Maneuvers of a Spacecraft
Table 6
Times when the limits are reached and average yearly fuel consumption for the mission.
Eccentricity of the perturbing body
Time to reach the Δe and Δi limits (year)
Yearly consumption for impulsive maneuvers (kg)
For
full model = 5.50 single averaged model = 5.75 double averaged model = 5.76 full model = 7.63 single averaged model = 8.23 double averaged model = 8.24 full model = 18.11 single averaged model = 20.12 double averaged model = 20.13 full model = 28.0 single averaged model = 31.30 double averaged model = 31.30 full model = 0.012 single averaged model = 0.10 double averaged model = 22.92
full model = 8.77 single averaged model = 5.68 double averaged model = 5.67 full model = 12.84 single averaged model = 8.11 double averaged model = 8.11 full model = 30.98 single averaged model = 19.82 double averaged model = 19.83 single averaged model = 30.82 double averaged model = 30.84 full model = 0.012 single averaged model = 0.083 double averaged model = 25.58
full model = 13.64 single averaged model = 5.31 double averaged model = 5.41 full model = 21.10 single averaged model = 7.62 double averaged model = 7.75 single averaged model = 18.59 double averaged model = 18.94 single averaged model = 28.98 double averaged model = 29.45 full model = 0.012 single averaged model = 0.071 double averaged model = 21.57 single averaged model = 13.03 single averaged model = 22.62
