Optimization of Low-Thrust Limited-Power Trajectories in a Noncentral Gravity Field—Transfers between Orbits with Small Eccentricities

Table 1

Maneuver of modification of all orbital elements.

𝑇=𝑡𝑓−𝑡0	𝑎𝑒/𝑎0		Maneuver of modification of all orbital elements
			Initial orbit	Final orbit	Orbital elements
100	0.950	0.900
	0.850	0.800
150	0.750	0.700	1.000	1.150	𝑎
	0.650	0.600	0.0025	0.0050	𝑒
200	0.550	0.500	30.00^∘	35.0^∘	𝐼
	0.450	0.400	30.00^∘	37.5^∘	Ω
250	0.350	0.300	60.00^∘	62.50^∘	𝜔
	0.250	0.200
—	0.150	0.100