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.
Includes 1995 IGRF coefficients as of Jan. 1999.
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, c )
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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)
c (.) Coefficients for field model
.coeff (3,1) Base coefficents
.dCoeff (3,1) Deltas
.jD0 (1,1) Epoch
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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.
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AerospaceUtils: Coord/ECIToEF SC: BasicOrbit/Period SC: BasicOrbit/RVFromKepler SC: Ephem/EarthRte SC: Ephem/MSidDay Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/DeBlankLT Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/Plot3D Common: Graphics/PltStyle Common: Graphics/TimeLabl Common: Graphics/XLabelS Common: Graphics/YLabelS Common: Graphics/ZLabelS Common: Time/DTSToDTA Common: Time/Date2JD Common: Time/JD2000 Common: Time/JD2T Common: Time/T2JD Math: Linear/Mag Math: Linear/Skew Math: MathUtils/R2P5
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