AEROELASTIC MODEL OF REDUCED-ORDER FOR A SLENDER MISSILE
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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。
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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. -
图 3 BACT机翼模型的气动力训练信号
Figure 3. Training signal of aerodynamic load on the BACT wing model
图 4 BACT机翼模型的气动力验证信号
Figure 4. Verification signal of aerodynamic load on the BACT wing model
图 6 BACT机翼模型的极限环颤振幅值
Figure 6. Amplitude of the limit cycle flutter of the BACT wing model
图 8 导弹模型表面压力分布系数
Figure 8. Surface pressure distribution coefficient on the slender missile model
图 9 不同尾舵偏转时导弹模型表面的CFD网格
Figure 9. CFD grid on the missile model for different deflections of a tail fin
图 11 导弹模型的气动力验证信号
Figure 11. Verification signal of aerodynamic load on the missile model
图 13 导弹模型的一阶模态位移频谱
Figure 13. The frequency spectrum of the first-order modal displacement of the missile model
图 14 导弹模型的二阶模态位移频谱
Figure 14. The frequency spectrum of the second-order modal displacement of the missile model
表 1 导弹模型气动弹性响应计算时间
Table 1. Computation time for aeroelastic responses of the missile model
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