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Path: SC/Environs
% Computes the geocentric magnetic field based on a tilted dipole model.
The output is in geocentric inertial coordinates (ECI). This function includes
the effect of dipole motion on the earth.
Type BDipole for a demonstration of a satellite in a low earth inclined orbit.
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Form:
[b, bDot] = BDipole( r, jD, v )
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Inputs
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r (3,:) Position vector in the ECI frame (km)
jD (1,:) Julian days
v (3,:) Velocity (km/s)
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Outputs
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b (3,:) Magnetic field in the ECI frame (T)
bDot (3,:) Derivative of b in the ECI frame (T/s)
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Reference: Wertz, J., ed. "Spacecraft Attitude Determination and
Control," Kluwer, 1976, 783-784.
Includes 1995 IGRF coefficients as of Jan. 1999
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AeroUtils: Coord/ECIToEF Common: Graphics/Plot2D Common: Time/JD2000 Common: Time/JD2T Math: Linear/Mag Math: Linear/Skew OrbitMiniToolbox: Support/EarthRte SC: BasicOrbit/Period SC: BasicOrbit/RVFromKepler
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