孙岩, 黄勇, 王运涛, 孟德虹, 王昊. TRIP软件的静气动弹性计算模块开发及精度验证[J]. 空气动力学学报, 2017, 35(5): 620-624. DOI: 10.7638/kqdlxxb-2015.0154
引用本文: 孙岩, 黄勇, 王运涛, 孟德虹, 王昊. TRIP软件的静气动弹性计算模块开发及精度验证[J]. 空气动力学学报, 2017, 35(5): 620-624. DOI: 10.7638/kqdlxxb-2015.0154
SUN Yan, HUANG Yong, WANG Yuntao, MENG Dehong, WANG Hao. Development and precision validation of static aeroelastic computational module on flow solver TRIP[J]. ACTA AERODYNAMICA SINICA, 2017, 35(5): 620-624. DOI: 10.7638/kqdlxxb-2015.0154
Citation: SUN Yan, HUANG Yong, WANG Yuntao, MENG Dehong, WANG Hao. Development and precision validation of static aeroelastic computational module on flow solver TRIP[J]. ACTA AERODYNAMICA SINICA, 2017, 35(5): 620-624. DOI: 10.7638/kqdlxxb-2015.0154

TRIP软件的静气动弹性计算模块开发及精度验证

Development and precision validation of static aeroelastic computational module on flow solver TRIP

  • 摘要: 在结构网格流场求解软件TRIP基础上,发展了一套静气动弹性计算模块。首先简要介绍了静气动弹性计算模块总体架构、构成单元和耦合策略,然后详细介绍了构成单元中采用的一些数值计算方法。最后利用大展弦比机翼、DLR-F6翼身组合体模型和HIRENASD机翼模型对静气动弹性计算模块进行了测试和精度验证。大展弦比机翼计算结果表明柔度矩阵、模态叠加和有限元数值求解在模态选取合适的情况下能够得到一致的变形计算结果。DLR-F6和HIRENASD模型不同计算软件的结果一致性表明本文静气动弹性计算模块采用了正确的算法流程,而计算与试验的结果一致性表明静气动弹性计算模块具有很好的预测精度。

     

    Abstract: A static aeroelastic computational module is developed on the flow solver TRIP. Firstly, the frame, main component units and coupling strategy of the static aeroelastic computational module are introduced briefly. Then numerical methods used in the component units are described in detail. Finally, the static aeroelastic computational module is tested and validated through three cases:high respect-ratio wing, DLR-F6 wing-body model and HIRENASD wing model. The computational results of high respect-ratio wing show that flexible matrix method, modal superposition method and finite element method can have same deformation results when the structure modes are selected properly. The result consistency of DLR-F6 or HIRENASD model among different solvers demonstrates that the static aeroelastic computational module has adopted a correct algorithm procedure. The results consistency of DLR-F6 or HIRENASD model between computations and tests shows that the present static aeroelastic computational module has a good prediction precision.

     

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