I want to simulate the Equations of Motions for F/A-18 Hornet (12 states & 6 DOF) on MATLAB using Simulink. I have the Aerodynamic model, from which I will get CL, CD, CY, Cl, Cn, Cm that are flight conditions dependent.
Now, the forces and moments calculated from these coefficients will be in Wind Axes because these coefficients are defined in that coordinate system only (correct me if I am wrong). For using these Aerodynamic Forces and Moments in Body Axes, do I need to convert them into body axes by multiplying a Direction Cosine Matrix, that converts vectors from Wind Axes to Body Axes? Or should I use the Wind Axes computation?
Assume, I took the first option and converted the forces and moments into Body Frame. But, there are terms like $p$, $q$, and $r$ in the computation of the coefficients mentioned above. These terms are defined in the body frame. So, should I use these values of $p$, $q$, $r$ that are in body axes and compute coefficients in wind axes? Or should I convert them also into wind axes before using them in the computation?
PS: Reference for the Aerodynamic Model of F/A-18 Hornet:
- A. Chakraborty, P. Seiler, and G. J. Balas, Susceptibility of F/A-18 flight controllers to the falling-leaf mode: linear analysis, Journal of Guidance, Control, and Dynamics, Vol. 34, No. 1, pp. 57–72, 2011.