基于机翼前缘绕流速度的大气参数测量方法

doi:10.16182/j.issn1004731x.joss.201704004

系统仿真学报 ›› 2017, Vol. 29 ›› Issue (4): 723-729.doi: 10.16182/j.issn1004731x.joss.201704004

基于机翼前缘绕流速度的大气参数测量方法

钱立林¹, 陶建武¹, 杨越明², 虞飞¹

1.空军航空大学飞行器控制系,长春 130022;
2.空军航空大学航空理论系,长春 130022

收稿日期:2015-06-16 修回日期:2015-09-20 出版日期:2017-04-08 发布日期:2020-06-03
作者简介:钱立林(1989-),男,江苏,博士生,研究方向为传感器测量技术。
基金资助:
国家自然科学基金(61172126),吉林省自然科学基金(20140101073JC)

Estimation of Atmospheric Parameter Based on Airflow Velocity Over Wing Leading Edge

Qian Lilin¹, Tao Jianwu¹, Yang Yueming², Yu Fei¹

1. Department of Flight Vehicle Control, Aviation University of Air Force, Changchun 130022, China;
2. Department of Aviation Theory, Aviation University of Air Force, Changchun 130022, China

Received:2015-06-16 Revised:2015-09-20 Online:2017-04-08 Published:2020-06-03

摘要/Abstract

摘要： 利用安装在机翼前缘的声矢量传感器,给出了一种新型大气参数的估计方法。基于声矢量传感器敏感翼部绕流分布,建立大气参数求解模型。根据机翼后掠、对称的特点,对速度矢量进行分解来对模型的非线性方程进行解耦,从而求解了侧滑角、攻角和自由流速度的表达式。通过Fluent对机翼绕流进行仿真,验证了方法的可行性。

关键词: 机翼前缘, 气流速度, 大气参数, Fluent, 流分离

Abstract: A new method measuring the atmospheric parameters was proposed based on acoustic vector sensors located at the wing leading edge, and the atmospheric parameters model was set up based on the airflow velocity distribution sensed by acoustic vector sensor over wing leading edge. According to the symmetric, swept character of wings, velocity vector was decomposed to solve the non-linear equation of model. The expressions of angle of sideslip, angle of attack and free stream velocity were derived. The feasibility of the expressions was verified by wing simulation data from Fluent.

Key words: wing leading edge, airflow velocity, atmospheric parameters, Fluent, flow separation

中图分类号:

V119
TP331

钱立林, 陶建武, 杨越明, 虞飞. 基于机翼前缘绕流速度的大气参数测量方法[J]. 系统仿真学报, 2017, 29(4): 723-729.

Qian Lilin, Tao Jianwu, Yang Yueming, Yu Fei. Estimation of Atmospheric Parameter Based on Airflow Velocity Over Wing Leading Edge[J]. Journal of System Simulation, 2017, 29(4): 723-729.

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基于机翼前缘绕流速度的大气参数测量方法

Estimation of Atmospheric Parameter Based on Airflow Velocity Over Wing Leading Edge

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