Path: AC/ACCoord
% Compute angle of attack and sideslip.
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Form:
[alpha, beta, alphaDot, betaDot, vT, vTDot] = AlphBeta( vB, vBDot )
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Inputs
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vB (3,1) Velocity in the body frame
vBDot (3,1) Acceleration in the body frame
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Outputs
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alpha (1,1) Angle of attack (rad)
beta (1,1) Sideslip angle (rad)
alphaDot (1,1) Derivative of angle of attack (rad)
betaDot (1,1) Derivative of sideslip angle (rad)
vT (1,1) Total velocity
vTDot (1,1) Derivative of total velocity
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Reference: Stevens, B.L., Lewis, F.L. , "Aircraft Control and
Simulation," John Wiley & Sons, 1992, p. 64, 82.
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Math: Linear/Mag
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