摘要
针对冲压推进高超声速飞行器飞行高度和飞行马赫数跨度范围大,飞行环境非常复杂,而其飞行过程中各种复杂的力学过程不可能完全精确地考虑在用于控制设计的飞行器控制模型中,且飞行过程中往往又会受到各种事先无法完全预知的扰动,采用μ分析方法设计了高超声速飞行器鲁棒控制系统,设计结果表明μ分析方法可以较理想的解决高超声速飞行器飞行控制系统在多种不确定因素情况下的建模误差难题。
Air-breathing vehicles traverse a broad flight envelope in altitude and velocity. Large variations in vehicle static and dynamic characteristics and in mass properties, result in the continuously changing of static stability margins of vehicles throughout the flight envelope. Furthermore, an additional source of uncertainty arises from the accuracy of mathematical dynamic models used to describe the vehicle in control system design. A robust control system is designed for hypersonic vehicles using μ - analysis. The results illustrated that μ -analysis is ideal for addressing the problem of multiple uncertainty sources present in flight control system.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2008年第5期1526-1530,共5页
Journal of Astronautics
基金
航天支撑技术基金项目(2008-HT-XGD)
