Technique to Optimize for Engine Shutoff Constraints in Electric-Propulsion Trajectories

Nomenclature a = semimajor axis, km E = eccentric anomaly, rad e = eccentricity f = acceleration magnitude due to thrust on the spacecraft, m∕s i = inclination, rad p = semilatus rectum, km r = distance from the spacecraft to the central body, km T = thrusting vector angle, N u = true latitude, rad weff = efficiency-based weighting wposition = position-based weighting α = in-plane thrusting angle, rad β = out-of-plane thrusting angle, rad η = maneuver efficiency ν = true anomaly, rad Ω = right ascension of the ascending node, rad ω = argument of perigee, rad