摘要
为获得舵面操纵、高度和质量变化引起的非线性动力学特性的变化情况,基于连续算法分别求取舵面、高度和质量与各个状态量所组成的平衡面。根据所求平衡面,基于岔理论对高超声速飞行器全局稳定性进行分析研究。分析结果表明,相较于传统的基于线性化方法对高超声速飞行器的稳定性所进行的研究,分岔理论能更全面地揭示高超声速飞行器的动力学本质特性,为气动布局设计和优化,以及飞行控制律设计提供有力的支撑。
To study the changes of nonlinear dynamics characteristics with different rudder, height and mass, thecontinuation algorithm is used to identify the equilibrium surfaces versus elevator, height and mass. According tothe equilibrium, the global stability of hypersonic vehicles is studied based on bifurcation theory. Compared toconventional linear method, the analysis results show that bifurcation theory can describe the dynamiccharacteristics more accurately, which can provide a powerful tool for the design of aerodynamic layout andcontrol laws of hypersonic vehicle.
作者
李晓刚
王玉惠
吴庆宪
LI Xiaogang WANG Yuhui WU Qingxian(College of Automation Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210006, China)
出处
《吉林大学学报(信息科学版)》
CAS
2016年第3期367-373,共7页
Journal of Jilin University(Information Science Edition)
基金
国家自然科学基金资助项目(61374212)
航空科学基金资助项目(20135152047)
中央高校基本科研业务费专项资金资助项目(NS2015031)
关键词
高超声速飞行器
全局稳定性
非线性动力学特性
分岔理论
hypersonic vehicles
global stability
nonlinear dynamic characteristics
bifurcation theory