Design Objective: Analyze open-loop longitudinal and lateral-directional stability dynamics of Lockheed C-5A and design a closed-loop control system for pitch altitude hold and heading angle hold using MATLAB and SIMULINK.
Roles
• Team leader, design the SIMULINK block diagram and write the code on MATLAB.
• Assisted in writing the report in AIAA format.
• Assisted in writing the report in AIAA format.
Project Requirements
• For the longitudinal system, a closed-loop pitch altitude hold control system and for the lateral system, a closed-loop heading angle hold control system to be chosen.
• The aircraft is at 20,000 ft above sea level.
• Constant mass of the aircraft to be assumed for the type of analysis.
• No steady-state lateral velocity.
• No steady-state plunge velocity.
• No steady-state roll angle.
• No steady-state angular velocities.
• The aircraft is at 20,000 ft above sea level.
• Constant mass of the aircraft to be assumed for the type of analysis.
• No steady-state lateral velocity.
• No steady-state plunge velocity.
• No steady-state roll angle.
• No steady-state angular velocities.
Results
• The result of this project showed that it would be better to use an LQR instead of the PID or the PI controller to get an accurate response.
