论文部分内容阅读
针对某型反坦克导弹高海拔条件下的飞行稳定性问题,采用攻角曲线仿真与频域特性分析相结合的方法,研究控制系统性能。根据导弹控制系统的组成,建立其仿真模型,并对积分方法、仿真时间、步长、初值等问题进行探讨,实现飞行过程中的攻角、高度变化规律仿真。结果表明,在高海拔条件下,导弹攻角呈发散趋势,控制系统表现出不稳定。通过分析控制系统参数,不稳定由空气密度下降引起,为适应高原改进设计提供依据。
Aiming at the flight stability of a certain type of anti-tank missile under high altitude conditions, the performance of the control system is studied by combining the attack angle curve simulation and frequency domain characteristic analysis. According to the composition of the missile control system, the simulation model is established, and the integration method, simulation time, step length and initial value are discussed to realize the simulation of the angle of attack and altitude variation during the flight. The results show that under high altitude conditions, the missile’s attack angle is divergent and the control system shows instability. By analyzing the control system parameters, the instability is caused by the decrease of air density, which provides the basis for improving the design of plateau.