Trajectory Design Combining Invariant Manifolds with Discrete Mechanics and Optimal Control
نویسندگان
چکیده
ai = normalized radius of body’s circularized orbit for i M;S, where M moon and S sun C = cost function Cd = discrete cost function D1 D2 = operator that denotes the derivative with respect to the first (second) argument dEO = distance of spacecraft from Earth, km dMO = distance of spacecraft from moon, km dp = altitude of elliptical orbit at perigee, km E = energy integral Ei = critical energy for point at rest at Lagrange point, Li e = eccentricity of elliptical orbit f = continuous force variable f k , f k = left and right discrete forces g0 = acceleration due to gravity, m=s 2
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