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Path: Orbit/OrbitMechanics
% Finds the inclination rate and orbit normal vector.
Computes the inclination change rate and orbit normal vector. This
shows where in the orbit inclination changes fastest with a normal
acceleration.
Type InclinationRate for a demo.
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Form:
[dI, uN, dIMax] = InclinationRate( x, mu )
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Inputs
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x (6,:) [r;v]
mu (1,1) Gravitational potential (km^3/s^2)
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Outputs
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dI (1,:) Inclination rate (rad/sec)
uN (3,:) Orbit normal
dIMax (1,1) Maximum inclination rate (rad/sec)
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Reference: Robert Falck and Leon Gefert," A Method of Efficient
Inclination Changes for Low-Thrust Spacecraft,"
Astrodynamics Specialist Conference and Exhibit,
Monterey, CA, United States, 2002.
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Common: Graphics/Plot2D Common: Graphics/TimeLabl Math: Linear/Cross Math: Linear/Unit Orbit: OrbitMechanics/RVOrbGen SC: BasicOrbit/M2Nu SC: BasicOrbit/Period SC: BasicOrbit/RV2El
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