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。
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.
作者
付增良
张石玉
周家检
梁彬
赵俊波
周平
孙玮琪
张宇航
FU Zengliang;ZHANG Shiyu;ZHOU Jiajian;LIANG Bin;ZHAO Junbo;ZHOU Ping;SUN Weiqi;ZHANG Yuhang(China Academy of Aerospace Aerodynamics,Beijing 100074,China)
出处
《空气动力学学报》
北大核心
2025年第1期53-60,I0002,共9页
Acta Aerodynamica Sinica
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
wind tunnel virtual flight test
control characteristic evaluation
control law
hypersonic vehicle
