Aerospace Launc Vehicle Autopilot Design Based on H* Control Approach

Tracking of guidance commands in the presence of disturbances is performed for a real linear time-varying aerospace launch vehicle during the atmospheric flight using H∞ control theory. H∞ robust controller is first designed based on an operating point which guarantees the stability of the system. Resulted control is then employed to control the linear time-varying aerospace launch vehicle. Simulation results demonstrate the performance of the designed H∞ controller and tracking accuracy of the autopilot. Robustness of the system against disturbances is also evaluated and excellent performance is demonstrated.

کلیدواژه ها:

Aerospace launch vehicle ، H∞ control ، robust control