北京航空航天大学学报 ›› 2021, Vol. 47 ›› Issue (4): 853-862.doi: 10.13700/j.bh.1001-5965.2017.0804

• 论文 • 上一篇    下一篇

飞机风扰响应特性的模拟与评定方法

徐王强1,2, 王立新1, 乐挺1, 张喆3   

  1. 1. 北京航空航天大学 航空科学与工程学院, 北京 100083;
    2. 航空工业江西洪都航空工业集团飞机设计所, 南昌 330024;
    3. 中国飞行试验研究院 试飞员学院, 西安 710089
  • 收稿日期:2017-12-26 发布日期:2021-04-30
  • 通讯作者: 乐挺 E-mail:yueting_buaa@163.com
  • 作者简介:徐王强,男,博士研究生。主要研究方向:飞机设计、飞行安全;王立新,男,博士,教授,博士生导师。主要研究方向:飞机设计、飞行动力学与控制、飞行安全等;乐挺,男,博士,讲师,硕士生导师。主要研究方向:飞行动力学与飞行控制。
  • 基金资助:
    航空科学基金(20141351018)

Simulation and evaluation method of aircraft response characteristics under wind disturbance

XU Wangqiang1,2, WANG Lixin1, YUE Ting1, ZHANG Zhe3   

  1. 1. School of Aeronautic Science and Engineering, Beihang University, Beijing 100083, China;
    2. Aircraft Design Institute, AVIC Hongdu Aviation Industry Group, Nanchang 330024, China;
    3. Test Pilot Institute, Chinese Flight Test Establishment, Xi'an 710089, China
  • Received:2017-12-26 Published:2021-04-30
  • Supported by:
    Aeronautical Science Foundation of China (20141351018)

摘要: 针对飞行试验研究飞机风扰响应特性时存在的安全性与经济性问题,提出了一种在平静大气中模拟及量化评定飞机风扰响应特性的方法。通过设计舵面输入指令来激励飞机,使其产生能够模拟受到风扰的运动响应,进而完成飞机风扰响应特性的评定。以某型飞机为算例,基于PID控制方法设计了激励指令信号,模拟了飞机遭遇垂直突风与侧风后的响应特性,并基于时域峰值法评定了飞机的稳定特性。采用低阶等效拟配的方法对基于风扰响应数据评定所得的稳定特性结果进行了对比验证,结果表明,所建立的模拟风扰响应的控制指令设计与稳定特性评定方法是正确合理的。研究方法与结果对于飞机风扰响应特性的飞行试验评定等具有一定的参考价值。

关键词: 激励指令, 风扰响应, 稳定特性, 飞行试验, PID控制

Abstract: Aimed at economic and safety problems of investigating response characteristics of aircraft under wind disturbance by flight test, this paper presents a method of stimulating aircraft by designing input command of control surface in a calm atmosphere, to make it simulate motion response under wind disturbance and then complete the evaluation of aircraft characteristics under wind disturbance. Taking a certain aircraft as an example, stimulation command signals were designed based on PID control method. Response characteristics of aircraft that encountered vertical gust and cross wind were simulated, and the stability of aircraft was evaluated based on time-domain peak value. The stability characteristics, based on response data under wind disturbance, were compared and validated by adoption of low-order equivalent matching method. The results show that the design method of input command of control surface to simulate wind disturbance response and the evaluation method of stability characteristics are correct and reasonable. The research methods and results provide valuable reference for the evaluation of motion characteristics of aircraft by flight test.

Key words: stimulating signal, response under wind disturbance, stability characteristic, flight test, PID control

中图分类号: 


版权所有 © 《北京航空航天大学学报》编辑部
通讯地址:北京市海淀区学院路37号 北京航空航天大学学报编辑部 邮编:100191 E-mail:jbuaa@buaa.edu.cn
本系统由北京玛格泰克科技发展有限公司设计开发