(Solved): how to do this The roll angle to aileron input transfer function can be modelled according to: ...

how to do this

The roll angle to aileron input transfer function can be modelled according to: $$\frac{?(s)}{{?}_a(s)}=\frac{L_{?a}}{s\left(s?L_p\right)}$$ Recommend a roll angle control design that capable to maintain a wings-level attitude. Consider the following stability derivatives for the control system design: $$\begin{array}{l}{L}_{?a}=2.5/{\mathrm{s}}^2\\ L_p=?0.5/{\mathrm{s}}^2\end{array}$$ The system performance is set to targeted to operate at damping ratio, $$?=0.5$$ and undamped natural frequency, $${?}_n=3\mathrm{rad}/\mathrm{s}$$. Consider the sensor used in the control system design to be a perfect device. (11 marks)