Case-Study-Aircraft-Pitch-Control

Case study carried out to analyze longitudinal dynamics and longitudinal equations of motion for the aircraft are considered.

Case Study: Aircraft Pitch Control

• To analyse longitudinal dynamics.

• the longitudinal equations of motion for the aircraft are considered.

Assumptions:

• Aircraft is in steady-cruise at constant altitude and velocity; thus, the thrust, drag, weight and lift forces balance each other in the x- and y-directions • a change in pitch angle will not change the speed of the aircraft,

• input will be the elevator deflection angle ‘delta’ and putput is pitch angle ‘q’ of the aircraft.

Analysis Carried out:

• Open Loop Response, Closed loop response, PID Controller Design, Controller Design using root-locus approach, LQR Design, Controller Design Via. Pole placement techniques.

Tools Used to implement:

MATLAB, Simulink, Flightgear.

Source: Control Tutorials by Michigan Uniiversity https://ctms.engin.umich.edu/CTMS/index.php?example=AircraftPitch&section=ControlDigital

Root-Lcus Based Controller: https://youtu.be/3NLoPjOPmdU

PID Controller: https://youtu.be/vxDltsTVl0I

LQR Controller: https://youtu.be/lU_aUMX9794

Lead Compensator: https://youtu.be/ShmrshB9eOU

Interested to work on this?

Linked-in:

https://www.linkedin.com/in/gurunayk-nayak-09043390/