Path: SpacecraftEstimation/DemoFuns
% Point mass gravity model.
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Form:
d = RHSEarthOrbitUKF;
xDot = RHSEarthOrbitUKF( x, t, d )
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Inputs
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x (6,1) State vector [r;v]
t (1,1) Time (unused)
d (.) Data structure
.mu (1,1) Gravitational constant (default earth)
.a (3,1) Acceleration vector in ECI Frame
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Outputs
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x (6,1) State vector derivative d[r;v]/dt
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Math: Linear/Mag
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