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Path: AC/ACCoord
% Euler rates.
Since version 2 (ACT)
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Form:
eDot = EulRate( e, w )
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Inputs
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e (3,1) Euler angles [phi;theta;psi]
w (3,1) Angular rates wrt NED [p;q;r]
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Outputs
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eDot (3,1) Euler rates d[phi;theta;psi]/dt
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Reference: Stevens, B.L., Lewis, F.L. , Aircraft Control and Simulation,
John Wiley & Sons, 1992, p. 38.
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