基于气动力降阶的弹性飞机阵风响应仿真分析及验证

师妍; 万志强; 吴志刚; 杨超

doi:10.7527/S1000-6893.2021.25474

航空学报 >

2022 , Vol. 43 >Issue 1: 125474 - 125474

DOI: https://doi.org/10.7527/S1000-6893.2021.25474

流体力学与飞行力学

基于气动力降阶的弹性飞机阵风响应仿真分析及验证

师妍 ,
万志强 ,
吴志刚 ,
杨超

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北京航空航天大学航空科学与工程学院, 北京 100083

收稿日期: 2021-03-12

修回日期: 2021-05-20

网络出版日期: 2021-05-20

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Gust response analysis and verification of elastic aircraft based on nonlinear aerodynamic reduced-order model

SHI Yan ,
WAN Zhiqiang ,
WU Zhigang ,
YANG Chao

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School of Aeronautic Science and Engineering, Beihang University, Beijing 100083, China

Received date: 2021-03-12

Revised date: 2021-05-20

Online published: 2021-05-20

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摘要

低速飞机在阵风作用下容易产生非线性气动力，从而引发非线性气动弹性效应，对飞行安全造成威胁。针对此类问题的分析，经典面元法无法满足计算精度要求，计算流体力学（CFD）/计算结构动力学（CSD）全阶耦合分析效率低下，因此需建立满足工程应用的高精度、高效率的飞行动力学仿真分析模型。针对以上问题提出了一种适用于工程的非线性气动力降阶模型（ROM）用以实现弹性飞机飞行动力学仿真，特别是低速飞机在遭遇大幅值阵风情况下的阵风响应仿真。以风洞试验飞翼飞机模型为对象，利用CFD方法获得了该模型的气动力数据，利用自回归移动平均（ARMA）方法和径向基函数（RBF）神经网络方法分别建立了该模型的线性气动力ROM和非线性修正气动力ROM。结合模型的刚弹耦合飞行动力学方程对模型遭遇阵风情况下的响应进行仿真分析，并将仿真结果和风洞试验结果及CFD/CSD计算结果进行对比。结果表明建立的基于非线性气动力ROM的弹性飞机仿真模型在气动力预测、稳定性分析及阵风响应分析方面的表现都优于基于线性气动力ROM的仿真模型，和试验结果及CFD/CSD分析结果一致性较好，且所建模型在相同工况下的仿真时间远低于CFD/CSD分析方法，可应用于工程实践。

关键词： 气动力降阶模型; 大攻角气动力; 刚弹耦合动力学模型; 飞行动力学仿真; 阵风响应

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师妍 , 万志强 , 吴志刚 , 杨超 . 基于气动力降阶的弹性飞机阵风响应仿真分析及验证[J]. 航空学报, 2022 , 43(1) : 125474 -125474 . DOI: 10.7527/S1000-6893.2021.25474

Abstract

For low-speed aircraft, gust is more likely to lead to the generation of nonlinear aerodynamic force and nonlinear aeroelastic response, consequently causing flight safety problems. To study these nonlinear problems, the classical panel method cannot meet the accuracy requirements, and the Computational Fluid Dynamics (CFD)/Computational Structure Dynamics (CSD) full order coupling analysis is inefficient. Therefore, it is necessary to establish a flight dynamics analysis model with high precision and high efficiency to satisfy the engineering requirements. A nonlinear aerodynamic Reduced-Order Model (ROM) is proposed in this paper to predict the nonlinear aerodynamic force of low-speed aircraft under high amplitude gusts. Taking a flying wing aircraft model in a wind tunnel test as an example, we obtain the aerodynamic data of the model with the CFD method. A linear aerodynamic ROM and a nonlinear aerodynamic correction ROM of the flying wing aircraft model are established by the Autoregressive Moving Average (ARMA) method and Radial Basis Function (RBF) neural network method, respectively. An elastic aircraft simulation model is then established and the response of the model under gusts is simulated and analyzed by combining the rigid-elastic coupling flight dynamics equation and the aerodynamic ROM. Comparison of the simulation results with the wind tunnel test results and the CFD/CSD calculation results shows that the performance of the elastic aircraft simulation model based on nonlinear aerodynamic ROM is better than that of the model based on linear aerodynamic ROM in aerodynamic prediction, stability analysis and gust response analysis, and that the analysis results are in good agreement with the test results and CFD/CSD analysis results. The time cost of the proposed simulation model based on ROM is much lower than that of the CFD/CSD analysis method under the same working conditions, indicating the applicability of the proposed model to the engineering practice.

Key words： aerodynamic reduced-order model; aerodynamic force with high angle of attack; rigid-elastic coupling dynamic model; flight dynamics simulation; gust response

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