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SUPPORT SITE |
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SUPPORT SITE |
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Path: AC/Aircraft
% Aerodynamic model.
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Form:
g = ACAero( alpha, beta, x, d, qBar, control, flex, rho )
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Inputs
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alpha Angle of attack (deg)
beta Sideslip (deg)
x State
d Aerodynamic data
qBar Dynamic pressure
control Controls
.aileron
.rudder
.elevator
flex Flex data structure
rho Atmospheric density
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Outputs
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g .torque (3,1) Core torques
.force (3,1) Core forces
.modal (:,1) Modal forces
.inertia (3,3) Delta inertia due to aerodynamics
.mass (3,3) Delta mass matrix due to aerodynamics
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Math: Analysis/IntExpR Math: Analysis/IntExt Math: Linear/Mag
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