摘要
通常控制系统由于惯性、滞后等原因,其输出信号必然落后于输入信号.控制系统传递函数分子阶次总是低于分母阶次,把它们颠倒过来(分子阶次高于分母阶次),现实系统认为是不可能的。但是,在原型加载系统实验中,输出力矩信号却出现了“超前效性”.为了研究这个异常情况,本文揭示了舵机加载系统耦合力矩的物理本质,分析伺服机构受力平衡关系与运动规律,对系统数学模型的细节进行描述.根据传递函数计算的伯德图与实验值比较,评估该系统数学模型的有用性和基本设计原理的有效性.
Because of inertia, time lag etc, in general the control system's output signal always falls behind its input command, and the order of the numerator is always lower than that of the denominator in transfer functions for any control system. It is inconceivable in real system that their relations are reversed(the order of numerator is that of ). B,'sureffect' arosed in the output ment command during the original loading system test The physical nature of opling moment of servo loading system has been revealed in this paper, and the force balance relations and the motion laws of servomechanism have been analysed. The mathematical model of the loading system is described circumstantially. The Bode diagram calculated through the transfer function is compared with the experimental data. the usefulness of the mathematical model for servo loading system and the effectiveness of the design fundamentals have been evaluated.
出处
《战术导弹技术》
1992年第3期37-46,共10页
Tactical Missile Technology
关键词
舵机
飞行模拟器
数学模型
导弹
Steing engine
Flight simulator
Aerodynamic binge moment
Mathematical model
