Path: AC/ACCoord
% Compute ECI to body quaternion from ECI position and Euler angles.
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Form:
qECIToB = QECI( r, e )
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Inputs
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r (3,1) ECI Position vector
e (3,1) Euler angles [phi;theta;psi]
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Outputs
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qECIToB (4,1) Quaternion from ECI to B
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See also ECIToNED
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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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AC: ACCoord/ECIToNED Common: Quaternion/Mat2Q Common: Quaternion/QMult Common: Transform/Eul2Q
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