摘要
针对高超声速飞行器大马赫数大迎角飞行状态下荷兰滚特性不稳、运动耦合严重的问题,对侧滑角变化率反馈在高超声速飞行器中的应用进行研究。研究侧滑角变化率反馈控制的机理,以横侧向线性小扰动方程为基础,推导侧滑角变化率增稳荷兰滚的机理和侧滑角变化率反馈消除运动耦合的机理,对侧滑角变化率信号作简单分析,并进行相关仿真验证。仿真结果表明:侧滑角变化率反馈能明显改变飞行器荷兰滚阻尼特性,削弱运动耦合的影响,抑制侧滑角的变化,改善侧滑角品质。
Research on application of sideslip angle change rate feedback in hypersonic vehicle because of unstable Dutch roll and severe kinematic coupling of the hypersonic vehicle at high angle of attack and Mach number. Research the mechanism of sideslip angle change rate change rate feedback control, based on lateral linear small perturbation equation, deduce mechanism of sideslip angle change rate increasing stability of the Dutch roll and the mechanism of sideslip angle change rate feedback eliminating the kinematic coupling, simply analyze sideslip change rate angle. Then carry out related simulation verification. The simulation results show that the sideslip change rate feedback can significantly change vehicle Dutch roll damping feature, restrain influence of kinematic coupling and improve sideslip angle quality.
出处
《兵工自动化》
2014年第3期72-76,共5页
Ordnance Industry Automation
基金
基本科研业务费专项研究基金(56XZA12008)
江苏高校优势学科建设工程资助项目
关键词
高超声速飞行器
荷兰滚
运动耦合
反馈控制
hypersonic vehicle
Dutch roll
kinematic coupling
feedback control
