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摘要炮射导弹就是将精确制导技术与常规火炮系统进行有机结合，在保留了原有系统反应快、火力猛等特点的前提下，增加了其作战半径，提高了导弹的命中精度。炮射导弹是一种高新技术炮弹，它使火炮这类间接瞄准杀伤武器具备远距离精确打击能力，成为当前兵器领域的重点研究方向。制导技术在弹体上的应用，使得炮射导弹对于外界自然因素有着较强的抗干扰性，从而提高了弹丸的命中概率和杀伤效果。采用过载控制技术，设计炮射导弹自动驾驶仪，采用牛顿力学方法建立了飞行器动力学建模，采用“小扰动”假设得到了线性化模型，建立了基于过载的飞行器控制回路数学模型，采用PID设计过载跟踪控制回路，并进行了仿真，仿真结果上升时间小于0.1秒，超调量小于10%，跟踪误差小于5%，满足性能指标。9014
- 上一篇：matlab微后坐力自动炮的内弹道仿真研究
- 下一篇：基于GPS数据的炮射导弹比例导引方法研究
关键词 炮射导弹 纵向过载 PID控制
毕业设计说明书（论文）外文摘要
Title Design And Simulation On Controller Of Vertical Overload Of Artillery Missile
Abstract
Artillery missile is the combination of precision-guided systems and conventional artillery systems. In this way, not only retain the original system’s fast response and fierce fire, but also increase the long-range of resistance capability and the accuracy of the missile. Artillery missiles are a high-tech projectile. It give long-range precision strike capability to the indirect targeting anti-personnel weapons and becomes the focus of the weapons-research.It is the Guidance technology on the missile makes that artillery missiles have a strong anti-interference against the external natural factors, thereby increasing the hit probability and the killing effect of the projectile.
Overload control technology is used to design artillery missile autopilot instrument. Newtonian mechanics is used to build a vehicle dynamics model. "Disturbance" is the linear model’s assuming. Above all, a mathematical model of the control loop based on the aircraft overload can be established.Overload tracking control loop is designed by PID, and a simulation is completed. The simulation results show that the rise time is less than 0.1 seconds, the overshoot is less than 10% and the tracking error is less than 5 %. The overload tracking control loop suffices the performance indicators.
Keywords Artillery Missile Normal Overload PID Controller
目 次
1 绪论 1
1．1 炮射导弹的战略地位 1
1．2 炮射导弹的研究历史和发展现状以及未来的发展趋势 1
1.2.1 炮射导弹的研究历史 1
1.2.2 炮射导弹的发展趋势 2
1．3 控制理论在炮射导弹上的应用 4
1．4 研究的目的及意义 4
2 飞行器运动方程建立及仿真 5
2．1 常用坐标系和坐标系间的转换 5
2.1.1 坐标系的定义 5
2.1.2 各坐标系之间的关系及其转换 7
2．2 作用在导弹上的力和力矩 10
2．3 导弹动力学方程的建立 11
2.3.1 导弹质心运动的动力学方程 11
2.3.2 导弹绕质心转动的动力学方程 15
3 动力学模型的简化及仿真 18
4 低速滚转导弹的传递函数 23
5 飞行器过载跟踪自动驾驶仪的设计 25
5．1 PID控制 25