高超声速飞行器舵机间隙的影响及其抑制  

The Effects and Restriction of the Gap in the Actuator of Hypersonic Vehicles

作　　者：杨尧[1] 李立[1] 赵岳楼 闫杰[1] 

机构地区：[1]西北工业大学航天学院,西安710072 [2]西安机电信息技术研究所,西安710065

出　　处：《科学技术与工程》2014年第19期305-308,共4页Science Technology and Engineering

基　　金：国家自然科学基金(91216104)资助

摘　　要：高超声速飞行器非线性性影响飞行姿态控制,在某型轴对称高超声速飞行器俯仰通道数学仿真模型的基础上,利用描述函数法分析了舵机间隙环节对俯仰通道控制的影响。指出舵机间隙环节导致系统振荡,影响飞行姿态控制,然后在不改变原高超声速飞行器飞行控制参数的基础上,提出采用离散最速控制算法作为舵机控制算法抑制该间隙环节。仿真结果表明舵机应用该控制算法能显著削弱舵机间隙环节对飞行控制的影响。The nonlinearity of hypersonic vehicle can effects flight attitude control.On the basis of the longitudinal simulation of an axial symmetry hypersonic vehicle,the effects caused by the gap is analyzed to the longitudinal control using describing function and point out that the gap will lead to system oscillation.To restrain the bad influence,the time-optimal control theory is adopted as the steering engine control algorithm.The simulation result shows this control algorithm can significantly impair the effect caused by gap.

关 键 词：高超声速飞行器 间隙环节 最速控制 描述函数 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计]