面对称高速飞行器横航向控制特性风洞试验研究

付增良; 张石玉; 周家检; 梁彬; 赵俊波; 周平; 孙玮琪; 张宇航

doi:10.7638/kqdlxxb-2024.0039

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面对称高速飞行器横航向控制特性风洞试验研究

研究论文 | 更新时间：2026-05-28

- 面对称高速飞行器横航向控制特性风洞试验研究
- Wind tunnel test research of lateral-directional control effect of plane-symmetric hypersonic vehicles
- 空气动力学学报 2025年43卷第1期页码：53-60
- 作者机构：
  
  中国航天空气动力技术研究院,北京,100074
- 作者简介：
  
  付增良*（1981—），男，河南商丘人，研究员，研究方向：风洞动态试验技术. E-mail：fzl435@126.com
- 基金信息：
- DOI：10.7638/kqdlxxb-2024.0039
  中图分类号： V211.78
- 纸质出版：2025
- 稿件说明：
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付增良, 张石玉, 周家检, 等. 面对称高速飞行器横航向控制特性风洞试验研究[J]. 空气动力学学报, 2025, 43(1): 53−60.

FU Zengliang, ZHANG Shiyu, ZHOU Jiajian, et al. Wind tunnel test research of lateral-directional control effect of plane-symmetric hypersonic vehicles[J]. 2025, 43(1): 53-60.
付增良, 张石玉, 周家检, 等. 面对称高速飞行器横航向控制特性风洞试验研究[J]. 空气动力学学报, 2025, 43(1): 53−60. DOI： 10.7638/kqdlxxb-2024.0039

FU Zengliang, ZHANG Shiyu, ZHOU Jiajian, et al. Wind tunnel test research of lateral-directional control effect of plane-symmetric hypersonic vehicles[J]. 2025, 43(1): 53-60. DOI： 10.7638/kqdlxxb-2024.0039.

摘要

面对称高速飞行器在大攻角机动过程中存在气动耦合性强、稳定性弱及非线性、非定常特征显著的问题，这给飞行器气动特性研究、控制系统设计和地面验证提出了新的挑战。本文针对新型高速飞行器控制特性评估需求，以面对称高速飞行器模型为研究对象，在1 m量级高速风洞进行了虚拟飞行试验，设计了低阻尼滚转-偏航两自由度运动机构、小型化舵控装置和高性能无线测控系统，成功完成了多种控制策略下的倾斜转弯（bank-to-turn

BTT)机动试验，实现了控制特性评估与控制律对比、验证，为飞行器气动和飞控设计提供了可靠的试验依据和验证平台。

Abstract

Plane-symmetric hypersonic vehicles suffer from high aerodynamic coupling

weak stability and strong nonlinearity problems during large-angle-of-attack maneuvering flight

which poses a challenge to aerodynamic characteristics research

control system design and ground validation. To meet the coupling characteristic evaluation requirement of next-generation hypersonic vehicle

an innovative virtual flight test system was established for the first time in a 1-m-scale high-speed wind tunnel. The system incorporates customized components such as a low-damping rig

a compact helm gear

and a high-performance control module. Utilizing the bank-to-turn control strategy

the test system successfully simulated the vehicle's maneuvering flight under three control laws in the hypersonic wind tunnel. The test system offers a suitable solution for the coupling characteristics evaluation and control law validation

and provides a universal verification platform for aerodynamic design and flight control optimization.

关键词

Keywords

references

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