Active Control Law Design for Flutter/LCO Suppression Based on Reduced Order Model Method

• Published in: Chinese journal of aeronautics 2010-12, Vol.23 (6), p.639-646
• Main Authors: Gang, Chen, Yueming, Li, Guirong, Yan
• Format: Article
• Language: English
• Subjects: Active control; active control law; aeroelasticity; Design engineering; Flutter; Law; limit cycle oscillation; Limit cycle oscillations; Mathematical models; Panels; reduced order model; Reduced order models; static output feedback; Vibration; Volterra; 主动控制; 控制律设计; 设计模型; 降阶方法; 非定常空气动力学
• ISSN: 1000-9361
• DOI: 10.1016/S1000-9361(09)60265-X

Active stability augmentation system is an attractive and promising technology to suppress flutter and limit cycle oscillation （LCO）. In order to design a good active control law, the control plant model with low order and high accuracy must be provided, which is one of the most important key points. The traditional model is based on low fidelity aerodynamics model such as panel method, which is unsuitable for transonic flight regime. The physics-based high fidelity tools, reduced order model （ROM） and CFD/CSD coupled aeroservoelastic solver are used to design the active control law. The Volterra/ROM is applied to constructing the low order state space model for the nonlinear unsteady aerodynamics and static output feedback method is used to active control law design. The detail of the new method is demonstrated by the Goland＋ wing/store system. The simulation results show that the effectiveness of the designed active augmentation system, which can suppress the flutter and LCO successfully.