| 一种分析横向静不稳定导弹飞行攻角边界值的方法 |
| |
| 引用本文： | 李友年,陈星阳,杨育荣.一种分析横向静不稳定导弹飞行攻角边界值的方法[J].弹箭与制导学报,2010,30(2). |
| |
| 作者姓名： | 李友年 陈星阳 杨育荣 |
| |
| 作者单位： | 中国空空导弹研究院,河南洛阳,471009 |
| |
| 摘 要： | 工程设计初期,控制系统设计人员需要对气动特性进行快速分析,判定导弹能否满足制导控制系统的性能要求。文中以常见的几种横滚控制结构为基础,分析了横向静稳定性对控制系统的影响,并给出了控制系统最大稳定边界的计算方法。该方法物理概念清楚,计算简单,经数字仿真验证,所得到的飞行攻角边界值准确,可用于对气动外形和控制系统性能的评估。
|
| 关 键 词： | 自动驾驶仪 通道耦合 横向静不稳定性 空间稳定性 |
An Approach of Lateral Static Unstable Missile's Angle of Attack Boundary Analysis |
| |
| Abstract: | During initial phase of engineering design, control system designers should analyze pneumatic features to quickly judge if guidance and control system performance can meet the requirements. Based on some kinds of raw control structure, in the paper, the influences of lateral static stabilization were analyzed, and calculation method of the maximum stable range was given. Its physical concept is clear and easy to calculate. The simulation result shows the flight angle of attack boundary value can be used for evaluating aerodynamic outline and estimating the guidance and control system's performance. |
| |
| Keywords: | autopilot channels coupling lateral static instability space stability |
| 本文献已被 CNKI 万方数据 等数据库收录！ |
|
