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

Table 2

Small and moderate amplitude maneuvers.

𝑎𝑒/𝑎0	𝑇=𝑡𝑓−𝑡0	Orbital elements of initial orbit	𝜌=𝑦𝑓/𝑦0
0.975	100	𝑎=1.0	1.05	1.10
	150	𝑒=0.0025	1.15	1.20
	200	𝐼=30.00^∘	1.25	1.30
	250	Ω=30.00^∘	1.35	1.40
	—	𝜔=60.00^∘	1.45	1.50