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Nonlinear aeroservoelastic analysis of a supersonic aircraft with control fin free-play by component mode synthesis technique
Journal of Sound and Vibration ( IF 4.7 ) Pub Date : 2021-02-01 , DOI: 10.1016/j.jsv.2020.115835
Wei Tian , Yingsong Gu , Hao Liu , Xiaochen Wang , Zhichun Yang , Yueming Li , Ping Li

Abstract To investigate the nonlinear aeroservoelastic behaviors of a three-dimensional supersonic aircraft with control fin free-play, a modeling method based on the component-mode synthesis technique is utilized. The most distinctive feature of this method is that the structural nonlinearity can be expressed explicitly in the reduced-order aeroservoelastic model. The unsteady aerodynamic model with discrete gust loads is formulated using the supersonic lifting surface theory and the minimum state approximation. The results validate the feasibility of the reduced-order aeroelastic model for gust response analysis. A hybrid adaptive feedback control algorithm is proposed for the gust load alleviation by integrating the positive position feedback (PPF) and the filtered-x least-mean-square (FxLMS) algorithm. The comparative study demonstrates that the designed PPF-FxLMS algorithm has a better control performance for the alleviation of the pitch attitude angle induced by the gust loads, and it remains effective in the post-flutter regime. Moreover, the effects of free-play nonlinearity on the dynamic behaviors of the aeroservoelastic system are also studied, and numerical results show that the presence of free-play can lead to a larger peak value of gust response. The nonlinear vibration of the control fin induces the aircraft pitch attitude to produce stable limit cycle oscillations with high frequency, and variation in the free-play magnitude significantly influences the gust responses of the nonlinear aeroservoelastic system.

中文翻译:

基于分量模态合成技术的带控制尾翼自由游隙超音速飞机非线性气动伺服弹性分析

摘要 为了研究具有控制尾翼自由间隙的三维超音速飞行器的非线性气动伺服弹性行为,采用了一种基于分量模态合成技术的建模方法。这种方法最显着的特点是结构非线性可以在降阶气动伺服弹性模型中明确表达。使用超音速升力面理论和最小状态近似来制定具有离散阵风载荷的非定常空气动力学模型。结果验证了降阶气动弹性模型用于阵风响应分析的可行性。提出了一种混合自适应反馈控制算法,通过集成正位置反馈(PPF)和滤波x最小均方(FxLMS)算法来缓解阵风载荷。对比研究表明,所设计的 PPF-FxLMS 算法对于缓解阵风载荷引起的俯仰姿态角具有更好的控制性能,并且在后颤振状态下仍然有效。此外,还研究了自由游隙非线性对气动伺服弹性系统动力学行为的影响,数值结果表明,自由游隙的存在会导致阵风响应的峰值更大。控制鳍的非线性振动导致飞机俯仰姿态产生稳定的高频极限循环振荡,自由游隙幅度的变化显着影响非线性气动伺服弹性系统的阵风响应。
更新日期:2021-02-01
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