An Optimal Trim Configuration Optimization Framework for Highly Flexible Aircraft

In this paper, a set of flight configuration optimization framework for high-altitude long-endurance aircraft is formed by optimizing the level flight configuration. The intrinsic beam model is used to model the formula of the whole highly flexible aircraft, coupled with unsteady aerodynamics and six-degree-of-freedom rigid body motion. The interior point method is used for optimization calculation by balancing the initial points first and optimizing the sequence of multiple initial points later. The optimal calculation results of the aircraft with wing layout studied in the literature are given and compared with the trim configuration in the literature. The results show that the proposed optimization framework can converge quickly in relatively few steps, and can significantly improve the whole plane resistance during the trim process of flexible aircraft.