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