Hi,
In the UAV Fixed-Wing Guidance Model Equations, the pitch control variable is related to the altitude through the equation theta_c = -k_h*(h_c-h)+theta_trim, where theta_c is the commanded pitch angle, k_h is the altitude hold gain, h_c is the desired altitude, h is the current altitude, and theta_trim is the trimmed pitch angle. The altitude hold gain k_h is a tuning parameter that determines how strongly the aircraft should respond to deviations from the desired altitude.
The maximum threshold for the control command will depend on the specific control system being used and the physical limitations of the aircraft. It is important to ensure that the control command input is within the range of the physical capabilities of the aircraft. In general, it is recommended to use reasonable values for the control command input that are within the range of expected operating conditions for the aircraft being simulated.
To regulate the control command input to get reasonable simulation results, you can use a feedback control loop to adjust the control input based on the current state of the aircraft. This can be done using a proportional-integral-derivative (PID) controller or other control algorithms. The tuning parameters of the controller can be adjusted to achieve the desired performance of the control system.
