The purpose is to use Simulink to simulate a much simplified model of the longitudinal motion of a fighter aircraftThe angle of attack is the angle between the direction a plane is pointing and the di

The transfer function for the pitch rate, q, is given by:

q(s)/d(s) = Kq/(Ts + 1)

where d(s) is the input control signal (angle of the front fins), Kq is the gain, and T is the time constant.

When a step change is applied to the input control signal, the pitch rate responds as shown in the sketch below:

The response starts from zero and rises quickly to reach a steady-state value, which is proportional to the magnitude of the input control signal. The rise time and settling time depend on the time constant T, with a larger T resulting in a slower response.

Overall, the response is a first-order system with a characteristic exponential decay, and the steady-state gain reflects the sensitivity of the pitch rate to changes in the input control signal