NNW-FSI软件静气动弹性耦合加速策略设计与实现

孙岩; 王昊; 江盟; 岳皓; 孟德虹

doi:10.7527/S1000-6893.2021.25738

航空学报 >

2021 , Vol. 42 >Issue 9: 625738 - 625738

DOI: https://doi.org/10.7527/S1000-6893.2021.25738

国家数值风洞(NNW)进展及应用专栏

NNW-FSI软件静气动弹性耦合加速策略设计与实现

孙岩 ,
王昊 ,
江盟 ,
岳皓 ,
孟德虹

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中国空气动力研究与发展中心计算空气动力研究所, 绵阳 621000

收稿日期: 2021-03-30

修回日期: 2021-04-29

网络出版日期: 2021-05-26

基金资助

国家数值风洞工程；国家重点研究发展计划（2020YFB1506701）

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Design and implementation of coupling acceleration strategy in static aeroelastic module of NNW-FSI software

SUN Yan ,
WANG Hao ,
JIANG Meng ,
YUE Hao ,
MENG Dehong

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Computational Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China

Received date: 2021-03-30

Revised date: 2021-04-29

Online published: 2021-05-26

Supported by

National Numerical Windtunnel Project;National Key R&D Program of China (2020YFB1506701)

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摘要

在国家数值风洞（NNW）工程的资助下，依托NNW-FSI流固耦合模拟软件平台，从气动载荷作用下飞行器结构静变形大小与收敛过程无关的物理机制出发，基于变形增量叠加的方式，设计和实现了一种静气动弹性耦合加速策略，通过松弛因子对耦合迭代的收敛过程进行调整。结合超大展弦比无人机和CHN-T1模型两种不同外形，开展了不同松弛因子下的静气动弹性耦合数值模拟，对耦合加速策略的参数影响和加速效果进行了测试和评估。从计算误差控制角度对松弛因子加速耦合迭代收敛的作用机制进行了理论分析，弄清3种类型静气动弹性耦合模拟过程中松弛因子发挥的作用，并给出了松弛因子选取范围的建议。静气动弹性耦合模拟和理论分析结果表明，针对不同类型的静气动弹性耦合问题，选取合适的松弛因子，能够达到抑制振荡并加速收敛的效果。

关键词： 国家数值风洞(NNW)工程; NNW-FSI; 静气动弹性; 耦合加速; 松弛迭代; 误差控制

本文引用格式

孙岩 , 王昊 , 江盟 , 岳皓 , 孟德虹 . NNW-FSI软件静气动弹性耦合加速策略设计与实现[J]. 航空学报, 2021 , 42(9) : 625738 -625738 . DOI: 10.7527/S1000-6893.2021.25738

Abstract

A coupling acceleration strategy was designed and implemented in the static aeroelastic module of the fluid-structure interaction software platform, NNW-FSI, with the support of the National Numerical Windtunnel (NNW) Project. The strategy was achieved based on a scheme of deformation increment superposition and used the relaxation factor to adjust the convergence process, inspired by the fact that the static structure deformation of aircraft under aerodynamic loads is independent of the convergence process. Then the parameter influence and acceleration effect of the strategy were tested and evaluated through the static aeroelastic simulation of the ultra-high respect-ratio unmanned aerial vehicle and the CHN-T1 model with different values of the relaxation factor. Finally, the effect of the relaxation factor in three types of static aeroelastic coupling simulation was clarified based on the theoretical analysis of the acceleration mechanism from the perspective of computational error control, and suggestions for the selection of the relaxation factor value were also given. Both the static aeroelastic simulation results and the theoretical analysis demonstrate that an appropriate selection of the relaxation factor value can suppress oscillation and accelerate convergence for a special type of static aeroelastic simulation problem.

Key words： National Numerical Windtunnel (NNW) Project; NNW-FSI; static aeroelasticity; coupling acceleration; relaxation iteration; error control

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