战斗机大迎角非定常气动力建模

doi:10.7527/S1000-6893.2019.23440

流体力学与飞行力学

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战斗机大迎角非定常气动力建模

沈霖¹, 黄达¹, 吴根兴¹, 展京霞²

1. 南京航空航天大学非定常空气动力学与流动控制工信部重点实验室, 南京 210016;
2. 中国航空工业成都飞机设计研究所, 成都 610091

收稿日期:2019-09-03 修回日期:2019-09-21 出版日期:2020-06-15 发布日期:2019-09-30
通讯作者: 黄达 E-mail:njdhcn@nuaa.edu.cn
基金资助:
国家自然科学基金（11872209）；江苏高校优势学科建设工程资助项目

Unsteady aerodynamic modeling for fighter configuration at high angles of attack

SHEN Lin¹, HUANG Da¹, WU Genxing¹, ZHAN Jingxia²

1. Key Laboratory of Unsteady Aerodynamics and Flow Control, Ministry of Industry and Information Technology, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
2. AVIC Chengdu Aircraft Design and Research Institute, Chengdu 610091, China

Received:2019-09-03 Revised:2019-09-21 Online:2020-06-15 Published:2019-09-30
Supported by:
National Natural Science Foundation of China (11872209); A Project Funded by the Priority Academic Program Development of Jiangsu Higher Education Institutions

摘要/Abstract

摘要： 针对目前大迎角非定常气动力模型大多基于单自由度风洞试验开展，且很难有效指导稳定性分析、控制律设计等工程实践的现状，基于偏航-滚转耦合运动风洞试验结果提出了一种大迎角非定常气动力???20200612???模型。该模型将非定常气动力分解为分别由旋转矢量的模和其引起的姿态变化???20200612???两部分贡献，具有清晰的物理意义和简洁的表达形式，同时还能准确反映横航向耦合效应对非定常气动力的影响。分别使用该模型和目前工程实践中常用的混合模型对不同运动形式中的横航向气动力进行计算，同时进行了尾旋仿真，与风洞试验结果对比验证了该模型对于飞机大迎角非定常气动特性的预测精度。通过将建模参数向体轴分解获得能与目前飞行动力学分析方法兼容的局部线性化形式，理论解释并仿真复现了F-16XL试飞中出现的侧向扰动现象，验证了该模型的工程适用性。

关键词: 大迎角, 非定常气动力, 偏航-滚转耦合, 气动力建模, 风洞试验

Abstract: The current studies of unsteady aerodynamic modeling at high angles of attack were mostly based on the wind tunnel tests with single degree of freedom oscillations, and are hard to be applied to the engineering applications such as stability analysis and control law design. In this investigation, an unsteady aerodynamic model called ???20200612??? model is proposed based on the yaw-roll coupled experimental data at high angles of attack. In the ???20200612??? model, the unsteady aerodynamic loads are considered as combinations of which produced by the module of rotation vector and variation of attitude (???20200612???). Therefore, the ???20200612??? model had a clear physical significance, and is simple in expression. Furthermore, the effects of lateral-directional coupling on the unsteady aerodynamic loads are accurately reflected in ???20200612??? model. Then both the ???20200612??? model and quasi-steady model, which is commonly used in engineering applications, are used for the calculation of lateral-directional aerodynamic loads in different motions and simulations of spin. The comparison between the simulation results and experimental data of spin verified that the ???20200612??? model is accurate in the prediction of unsteady aerodynamic characteristics of an aircraft at high angles of attack. Then ???20200612??? model are locally linearized by decomposing the modeling parameters onto body-axis, thus it could be compatible with current method of flight dynamics analysis. Hence the engineering applicability of ???20200612??? model is further verified by the theoretical explanation and simulation of the lateral disturbance phenomenon appeared in the flight test of F-16XL.

Key words: high angles of attack, unsteady aerodynamics, yaw-roll coupling, aerodynamic modeling, wind tunnel tests

中图分类号:

V211.7

沈霖, 黄达, 吴根兴, 展京霞. 战斗机大迎角非定常气动力建模[J]. 航空学报, 2020, 41(6): 523440-523440.

SHEN Lin, HUANG Da, WU Genxing, ZHAN Jingxia. Unsteady aerodynamic modeling for fighter configuration at high angles of attack[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2020, 41(6): 523440-523440.

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战斗机大迎角非定常气动力建模

Unsteady aerodynamic modeling for fighter configuration at high angles of attack

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