Path: Orbit/OrbitManeuver
% Low-thrust transfer between two circular, nonplanar orbits Valid for inclination changes up to 114.6 degrees. The inputs may be all scalars, all vectors, or two scalars and one vector. Enter acceleration to get a trip time output. -------------------------------------------------------------------------- Form: [dV, dVRatio, t] = LTPlaneChange( a0, af, dI, accel, mu ) -------------------------------------------------------------------------- ------ Inputs ------ a0 (1,:) Initial semi-major axis (km) af (1,:) Final semi-major axis (km) dI (1,:) Inclination change (km) accel (1,1) Acceleration (km/s) mu (1,1) Gravitational parameter (km^3/sec^2) ------- Outputs ------- dV (1,:) Total delta-v dVRatio (1,:) Ratio of total delta-v to Hohmann Delta-V t (1,:) Maneuver duration (days) -------------------------------------------------------------------------- Reference: J. Kechichian, "Reformulation of Edelbaum?s Low-Thrust Transfer Problem Using Optimal Control Theory", Journal of Guidance, Control, and Dynamics Vol. 20, No. 5, September?October 1997 --------------------------------------------------------------------------
Orbit: OrbitManeuver/OptDIH Orbit: OrbitManeuver/OrbMnvrInclination SC: BasicOrbit/VOrbit Common: Graphics/Plot2D
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