论文:2013,Vol:31,Issue(5):810-815
引用本文:
胡巍, 杨智春, 谷迎松. 带操纵面机翼气动弹性地面试验仿真系统中的气动力降阶方法[J]. 西北工业大学
Hu Wei, Yang Zhichun, Gu Yingsong. A New and Effective Method for Reducing Order of Aerodynamics of a Wing with Control Surface for Ground Flutter Test[J]. Northwestern polytechnical university

带操纵面机翼气动弹性地面试验仿真系统中的气动力降阶方法
胡巍, 杨智春, 谷迎松
西北工业大学 航空学院, 陕西 西安 710072
摘要:
对带操纵面三元机翼的地面颤振试验中非定常气动力降阶模型进行了研究,提出了一种气动力模型的二次降阶方法。该方法采用对气动力先进行频域降阶、再时域拟合的方法,分别确定主翼面、操纵面上激振点和拾振点的位置,从而获得气动力降阶模型。为进一步减少操纵面上所需激振点的个数,提出了以操纵面气动力、铰链力矩等效为前提,气动力降阶前后对应结构的动态气动弹性响应差异最小为目标函数,采用遗传算法进行激振点位置优化的方法。结果表明,对带操纵面三元机翼,采用文中提出的气动力二次降阶方法,可以有效地减少操纵面上激振点的个数,进而降低激振器控制系统的设计难度。
关键词:    颤振试验    地面模拟    气动弹性    带操纵面机翼    非定常气动力降阶   
A New and Effective Method for Reducing Order of Aerodynamics of a Wing with Control Surface for Ground Flutter Test
Hu Wei, Yang Zhichun, Gu Yingsong
College of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China
Abstract:
A new experimental technique,named ground flutter test,is proposed recently to determine the critical flutter speed without a wind tunnel. In this technique,the reduced order model(ROM) of unsteady aerodynamics is numerically simulated,the aircraft structure being exerted on by several electromagnetic shakers in real-time.We,aiming at the ground flutter test for aircraft wing with control surface,present a new approach,called secondary reduced order model(SROM),to obtain a reduced order model of unsteady aerodynamics in frequency-domain,by which measuring/ exciting points on the main surface and the control surface are obtained and then the reduced order model of frequency aerodynamics is transformed into that of time-domain. To minimize the number of exciting points on the control surface,a secondary model reduction is implemented based on the principle of force equivalence for the control surface and the minimum difference of aeroelastic response of wing structure. Results and their analysis show preliminarily that the presented SROM approach can improve the efficiency of generating the ROM of aerodynamics in time-domain and decrease the number of exciting points on the control surface,thus reducing the design difficulty of the control system of shakers.
Key words:    aeroelasticity    computer simulation    control    control surfaces    efficiency    experiments    flutter (aerodynamics)    mathematical models    optimization    wings    flutter test    ground simulation    reduced order model (ROM)   
收稿日期: 2012-11-13     修回日期:
DOI:
基金项目: 国家自然科学基金(11972198);111计划(B07050)资助
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作者简介: 胡巍(1988-),西北工业大学博士研究生,主要从事气动弹性研究。
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