巡飞航弹高度控制系统参数空间设计方法  

Parameter Space Design Method of Altitude Control System for Loitering Munitions Released by Aircraft

作　　者：沈坚平 于会江 赵日[2] 孙瑞胜[2] 史立新 

机构地区：[1]解放军95856部队 [2]南京理工大学能源与动力工程学院

出　　处：《火力与指挥控制》2013年第9期129-132,共4页Fire Control & Command Control

基　　金：国家部委预研基金(102080403);南京理工大学自主科研专项基金资助项目(2010ZYTS045;2010GJPY022)

摘　　要：研究了一种巡飞航弹高度控制系统的计算机辅助设计方法。针对巡飞航弹在巡飞过程中参数时变特征,采用参数空间方法对巡飞航弹俯仰角稳定回路和高度稳定回路参数进行设计。由于高度稳定回路阶次较高,不利于参数空间方法实现,提出对角稳定回路降阶的办法来选取高度控制参数,并在时域和频域里对控制系统的品质进行了分析。仿真结果表明控制系统满足巡飞航弹等高巡飞的指标要求。研究结果有较好的理论和工程实用价值,可以为巡飞弹控制系统的深入研究提供参考。It is studied computer-aided-design method of altitude control system for loitering munitions based on parameter space method. According to parameter time-vary characteristics of loitering munitions released by aircraft,pitching stabilization loop and altitude stabilization loop are designed by using parameter space method. Since the order number of altitude stabilization loop is high, which is not realized conveniently by using parameter space method, it is put forward to select altitude loop parameter by deducing the order number of pitching stabilization loop. And quality of control system of close-loop is analyzed in time and frequency region. The simulation results are presented to reveal that the designed control system meet the index for flight with the same height of loitering munitions, which can afford the reference to the deep study for loitering munitions.

关 键 词：控制系统 巡飞航弹 等高巡飞 参数空间法 

分 类 号：TJ765.2[兵器科学与技术—武器系统与运用工程]