典型高速飞行器滚转失稳特性研究

丛戎飞; 赵忠良; 叶友达; 马上; 李乾; 高昌; 卫锋

doi:10.7638/kqdlxxb-2024.0114

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典型高速飞行器滚转失稳特性研究

研究论文 | 更新时间：2026-05-28

- 典型高速飞行器滚转失稳特性研究
- Research on rolling instability of typical high-speed aircraft
- 空气动力学学报 2025年43卷第12期页码：90-98
- 作者机构：
  
  1. 跨域飞行交叉技术实验室,绵阳,621000
  2. 中国空气动力研究与发展中心高速空气动力研究所,绵阳,621000
  3. 北京流体动力科学研究中心,北京,100120
- 作者简介：
  
  丛戎飞（1992—），河南项城人，工程师，研究方向：飞行器动稳定性. E-mail：rfcong@sina.com
  赵忠良*，研究员，研究方向：试验空气动力学. E-mail：zhaozhongliang@cardc.cn
- 基金信息：
  
  省部级项目
- DOI：10.7638/kqdlxxb-2024.0114
  中图分类号： V212.1;V221.1+5;V221.3
- 纸质出版：2025
- 稿件说明：
移动端阅览
丛戎飞, 赵忠良, 叶友达, 等. 典型高速飞行器滚转失稳特性研究[J]. 空气动力学学报, 2025, 43(12): 90−98.

CONG Rongfei, ZHAO Zhongliang, YE Youda, et al. Research on rolling instability of typical high-speed aircraft[J]. 2025, 43(12): 90-98.
丛戎飞, 赵忠良, 叶友达, 等. 典型高速飞行器滚转失稳特性研究[J]. 空气动力学学报, 2025, 43(12): 90−98. DOI： 10.7638/kqdlxxb-2024.0114

CONG Rongfei, ZHAO Zhongliang, YE Youda, et al. Research on rolling instability of typical high-speed aircraft[J]. 2025, 43(12): 90-98. DOI： 10.7638/kqdlxxb-2024.0114.

摘要

高速飞行器的飞行环境以及机体构型与传统飞行器有较大差别，在运动稳定性研究中面临着诸多新问题。为了探究这一类飞行器的滚转失稳特性，设计了一种带有通流进气道的典型高速飞行器缩比模型，并发展了高速飞行器动态试验技术。通过自由滚转以及强迫俯仰/自由滚转动态试验，获得了进气道开/闭及俯仰运动频率对滚转稳定性的影响规律，探讨了强迫俯仰/自由滚转耦合运动失稳机理，并结合气动/运动耦合数值模拟方法开展了对比分析。研究表明：模型在进气道通流状态下具备单自由度滚转动稳定性，而进气道关闭会导致模型在10°攻角下滚转动稳定性变差，出现滚转失稳现象；在强迫俯仰/自由滚转工况下，随着俯仰频率增大，滚转运动出现单周期性吸引子、双周期性吸引子乃至无规律的滚转发散等失稳现象，说明强迫俯仰运动会导致滚转通道动稳定性变差；强迫俯仰/自由滚转数值模拟结果与动态试验结果的运动规律相近，初步验证了气动/运动耦合数值模拟方法的有效性。

Abstract

The flight environment and airframe configuration of high-speed aircraft are quite different from those of traditional flight vehicles

and there are many new problems in the study of their dynamic stability. In order to investigate the rolling stability of high-speed aircraft

a scaled model of typical high-speed aircraft with a through-flow inlet is designed

and the dynamic test technique of high-speed aircraft is developed. Through free rolling and forced pitching/free rolling dynamic tests

influence of the inlet opening/closing and the pitching motion frequency on the rolling stability is obtained

and the instability mechanism of forced pitching/free rolling coupling motion is discussed

with a comparative analysis using the aerodynamic/kinematic coupling numerical simulation method. The results show that the model with an open inlet has single-degree-of-freedom rolling stability

while the inlet closure will lead to a decrease in the rolling stability of the model at 10° angles of attack

resulting in rolling instability. Under the forced pitching/free rolling condition

as the pitching frequency increases

instability phenomenon such as single periodic attractors

double periodic attractors

and even irregular roll divergence appear during the rolling motion

indicating that forced pitching motions can lead to a decrease in the dynamic stability of the rolling channel. Numerical simulation results of the forced pitching/free rolling test show similar motion patterns to the dynamic test results

preliminarily verifying the effectiveness of the aerodynamic/kinematic coupling numerical simulation method.

关键词

Keywords

references

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