流体力学与飞行力学

耦合POD重构舰面流场的直升机舰面起降数值模拟

  • 吉洪蕾 ,
  • 陈仁良 ,
  • 李攀
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  • 南京航空航天大学 航空宇航学院 直升机旋翼动力学国家级重点实验室, 南京 210016
吉洪蕾,男,博士研究生。主要研究方向:直升机飞行动力学。Tel:025-84892141,E-mail:jhl@nuaa.edu.cn;陈仁良,男,博士,教授,博士生导师。主要研究方向:直升机飞行动力学、空气动力学、多学科优化设计。Tel:025-84892141,E-mail:crlae@nuaa.edu.cn;李攀,男,博士,副教授。主要研究方向:直升机空气动力学与飞行动力学。Tel:025-84892141,E-mail:lipan@nuaa.edu.cn

收稿日期: 2015-03-31

  修回日期: 2015-09-14

  网络出版日期: 2015-09-23

基金资助

国家自然科学基金(51405227);中央高校基本科研业务费专项资金(NS2014011)

Numerical simulation of a helicopter operating in a reconstructed ship airwake based on POD method

  • JI Honglei ,
  • CHEN Renliang ,
  • LI Pan
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  • National Laboratory of Science and Technology on Rotorcraft Aeromechanics, College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Received date: 2015-03-31

  Revised date: 2015-09-14

  Online published: 2015-09-23

Supported by

National Natural Science Foundation of China(51405227);The Fundamental Research Funds for the Central Universities(NS2014011)

摘要

为解决舰面非定常流场数据量过大的问题,采用本征正交分解(POD)方法对舰面流场进行重构,发展了一种耦合POD重构流场的直升机舰面起降数值模拟方法。首先采用计算流体力学(CFD)方法计算舰面非定常流场,获得离散数据样本;然后提取流场的POD模态,并截取能够捕捉到原流场主要特征的少量模态对原流场进行重构;最后建立耦合重构舰面流场的直升机高阶飞行动力学模型。以直升机返航进场为例进行数值模拟,并将计算得到的操纵量和飞行状态与飞行试验结果进行对比。结果表明:使用POD方法重构后的舰面流场数据约为原始样本数据的8.5%,且重构流场与原始流场吻合良好,POD方法能够解决舰面非定常流场数据量过大的问题。与飞行试验数据的对比表明,本文方法捕捉到了舰面非定常流场对直升机的影响,可用于直升机舰面起降研究。

本文引用格式

吉洪蕾 , 陈仁良 , 李攀 . 耦合POD重构舰面流场的直升机舰面起降数值模拟[J]. 航空学报, 2016 , 37(3) : 771 -779 . DOI: 10.7527/S1000-6893.2015.0253

Abstract

The proper orthogonal decomposition(POD) method is used to reduce the large amount of ship airwake data and a simulation method of a helicopter operating in a reconstructed ship airwake based on the POD method is developed. Firstly, a commercial computational fluid dynamics(CFD) software is used to calculate and sample the unsteady ship airwake. Secondly, the POD mode functions of the sample data are extracted, and a small number of the mode functions can well capture the main characteristics of the original fluid field and are used to reconstruct the ship airwake. Finally, a higher-order helicopter flight dynamic model coupled with the reconstructed ship airwake is established. An example of a helicopter recovery task in an unsteady ship airwake is simulated, and the time histories of control stick inputs and helicopter states are compared with the flight test results. The results show that the reconstructed ship airwake data with the POD method is about 8.5% of the original sample data and the reconstructed fluid field agrees well with the original fluid field, so the POD method is useful for reducing the ship airwake data. The comparison between the simulation results and flight test data indicates that the impact of the unsteady ship airwake on helicopter is captured, therefore the simulation method is suitable for the research of a helicopter operating in an unsteady ship airwake.

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