Application of Robust Control Design Techniques to the Aeroservoelastic Design Optimization of a Very Flexible UAV Wing

摘要

A multidisciplinary design optimization framework is developed to integrate control system design and aerostructural design of an aircraft in the conceptual design phase. The aircraft's wings are very flexible and the aircraft's aeroservoelastic equations of motion are derived and integrated with the aerostructural analysis and control system design. A two degree of freedom multi-objective control architecture capable of structural load alleviation is proposed. The linear matrix inequalities technique is used to express the control design process as a convex optimization problem. Time-domain analysis of the aircraft encountering an atmospheric gust is included in the design process. The optimal trade-off between aerodynamics, structures and control systems is found by maximizing the endurance subjected to stress constraints.