空气动力学学报2025，Vol.43Issue(1)：53-60,8.DOI:10.7638/kqdlxxb-2024.0039
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
付增良 1张石玉 1周家检 1梁彬 1赵俊波 1周平 1孙玮琪 1张宇航1
作者信息
- 1. 中国航天空气动力技术研究院,北京 100074
- 折叠
摘要
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
风洞虚拟飞行试验/控制特性评估/控制律/高速飞行器Key words
wind tunnel virtual flight test/control characteristic evaluation/control law/hypersonic vehicle引用本文复制引用
付增良,张石玉,周家检,梁彬,赵俊波,周平,孙玮琪,张宇航..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):53-60,8.
