Problem 3. A model for an airplane's pitch loop is shown below. Find the range of gain, K, that will keep the system stable by using: a) the Routh-Hurwitz criterion and b) the sisotool. For both these two solutions use Python Pitch angle Aileron deflection up Commanded pitch angle + Controller K(+1) (s + 4.85) Aircraft dynamics 5+10 32 +0.65 +9 Pitch angle Ailetom deflection down Roll angle 1 Yaw angle Gyro