Path: AC/ACCoord
% Convert from the body axes to stability axes.
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Form:
b = BToS( alpha, opt )
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Inputs
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alpha (1,1) Angle of attack (rad)
opt (1,:) 'matrix' or 'quaternion'
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Outputs
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b (3,3) Transformation matrix
(4,1) Quaternion
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Reference: Stevens, B.L., Lewis, F.L. , Aircraft Control and Simulation,
John Wiley & Sons, 1992, p. 63.
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Common: Quaternion/Mat2Q
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