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.
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Form:
LTPlaneChange; % demo
[dV, dVRatio, t] = LTPlaneChange( a0, af, dI, accel, mu )
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Inputs
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a0 (1,:) Initial semi-major axis (km)
af (1,:) Final semi-major axis (km)
dI (1,:) Inclination change (rad)
accel (1,1) Acceleration (km/s^2)
mu (1,1) Gravitational parameter (km^3/sec^2)*
* default, Earth
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Outputs
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dV (1,:) Total delta-v
dVRatio (1,:) Ratio of total delta-v to impulsive Delta-V
t (1,:) Maneuver duration (days)
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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
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Orbit: OrbitManeuver/OptDIH Orbit: OrbitManeuver/OrbMnvrInclination Orbit: OrbitMechanics/VOrbit Common: Graphics/Plot2D
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