Abstract
Abstract Combined power aircraft often experience altitude and speed loss during the modal conversion phase due to mismatches in thrust and drag. To address this issue, a thrust-drag matching strategy using the interior-point method was developed, optimizing the objective function with throttle constraints to minimize these losses. A six-degree-of-freedom model was created on the MATLAB/Simulink platform to analyze the aircraft’s dynamics. To resolve longitudinal and lateral instability during conversion, a stabilizing control law using pitch rate, roll rate, and yaw rate was introduced. The reliability of this control law was verified through modal characteristic analysis. Monte Carlo simulations demonstrated that the proposed thrust-drag matching strategy ensures successful modal conversion even under disturbances, validating both the robustness of the control law and the rationality of the strategy.
Published Version
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call