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

Table 3

Fuel consumption for the maneuvers to correct the inclination.

Δ𝑖 (rad)	Impulse for Δ𝑖 (m/s)	Fuel consumed (kg)	LT with 1 arc (kg)
0.0001	0.310	0.0932	0.0244
0.0005	1.553	0.4660	0.1221
0.0010	3.106	0.9330	0.2443
0.0050	15.523	4.6700	1.2235