力学学报 ›› 2017, Vol. 49 ›› Issue (3): 517-527.doi: 10.6052/0459-1879-16-358

所属专题: 力学学报创刊60周年专栏(2017年)

• 创刊60周年专栏 • 上一篇    下一篇

大长细比导弹的气动弹性降阶模型

杨执钧1, 黄锐1, 刘豪杰1, 赵永辉1, 胡海岩1, 王乐2   

  1. 1. 南京航空航天大学机械结构力学及控制国家重点实验室, 南京 210016;
    2. 中国运载火箭技术研究院, 北京 100076
  • 收稿日期:2016-11-30 出版日期:2017-05-15 发布日期:2017-06-16
  • 通讯作者: 胡海岩,中国科学院院士,教授,主要研究方向:飞行器结构动力学与控制.E-mail:hhyae@nuaa.edu.cn E-mail:hhyae@nuaa.edu.cn
  • 基金资助:

    国家自然科学基金(11502106),航空科学基金(2015ZA52),江苏省自然科学基金(BK20150736),江苏省普通高校研究生科研创新计划(KYLX15 0251)资助项目

AEROELASTIC MODEL OF REDUCED-ORDER FOR A SLENDER MISSILE

Yang Zhijun1, Huang Rui1, Liu Haojie1, Zhao Yonghui1, Hu Haian1, Wang Le2   

  1. 1. College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
    2. China Academy of Launch Vehicle Technology, Beijing 100076, China
  • Received:2016-11-30 Online:2017-05-15 Published:2017-06-16
  • Contact: 10.6052/0459-1879-16-358 E-mail:hhyae@nuaa.edu.cn

摘要:

对于大长细比导弹,需要在设计阶段准确计算气动弹性/气动伺服弹性,但其复杂的气动力给计算带来困难,因此气动力降阶模型是突破大长细比导弹跨音速气动弹性分析与控制瓶颈的关键技术。虽然气动力模型降阶方法已在预测二维机翼结构的气动弹性方面取得重要进展,但几乎未见关于全机模型的气动力降阶模型研究报道。本文基于递归Wiener模型的气动力降阶方法,利用CFD计算的气动力作为模型辨识数据,用鲁棒子空间和Levenberg-Marquardt算法辨识降阶模型参数,建立了大长细比导弹气动力降阶模型。在此基础上与大长细比导弹有限元模型相结合,构造出气动弹性降阶模型,并在数值仿真中测试气动弹性降阶模型在不同马赫数下的适用性。数值仿真结果表明,该气动弹性降阶模型能够精确预测导弹模型在不同飞行条件下的非定常气动力和导弹模型的气动弹性频率响应特性。

关键词:

大长细比导弹|气动力降阶模型|递归Wiener模型|颤振边界|极限环颤振

Abstract:

In the design phase of slender missiles, it is essential to predict their aeroelastic/aeroservoelastic behaviors accurately. The accurate prediction, however, is faced with the tough problem of CFD for the aerodynamic loads on slender missiles. How to establish the aerodynamic models of reduced-order is the key technology to break through the bottleneck in the transonic aeroelastic analysis and control of the slender missiles. Although the aerodynamic reducedorder methods have made important progress in predicting the aerodynamic loads and aeroelastic response of the twodimensional airfoil, still there are few research reports about the aerodynamic reduced-order models of the more complex airplane models. In this study, the recursive Wiener model of reduced-order is constructed for the aerodynamic loads on a slender missile according to the training data of CFD, while the parameters of the model can be estimated via the predictorbased subspace identification algorithm and Levenberg-Marquardt algorithm. The recursive Wiener model of reducedorder can be integrated with the finite element model of the missile structure so that the aeroelastic/ aeroservoelastic model of reduced-order is established for the missile. The accuracy of the aeroelastic models of reduced-order is tested under different Mach number in the numerical simulations. The numerical simulations show that the aeroelastic models of reduced-order can accurately predict the unsteady aerodynamic loads and the aeroservoelastic frequency response of the slender missile model under different flight conditions.

Key words:

slender missile|aerodynamic model of reduced-order|recursive Wiener model|flutter boundary|limit cycle flutter

中图分类号: 

  • V211