大空域导弹下降转平飞段控制器设计  

Controller Design for Large Airspace Missile from Descend to Level Flight Section

作　　者：史莹晶[1] 马广富[1] 马洪忠[1] 

机构地区：[1]哈尔滨工业大学航天学院,黑龙江哈尔滨150001

出　　处：《控制工程》2008年第4期371-373,377,共4页Control Engineering of China

基　　金：国家自然科学基金资助项目(60674101);教育部高校博士点基金资助项目(20050213010)

摘　　要：在导弹大空域变化的下降段,通过在导航计算机中预装分段常数的俯仰舵变化规律,在保证导弹大空域变化的快速性的同时,使导弹下降段末端不至于过冲太大而入水;针对下降转低空巡航的过渡段表现出的强机动及难预知特点,设计了模糊增益控制器,从而使过渡段弹道比较平滑,拉起过程仅出现一个超调,平飞过程平稳。比较了采用模糊增益控制器进行过渡段控制与采用固定参数控制器进行过渡段控制时俯仰舵偏角及飞行攻角的变化规律。仿真结果表明,采用该控制方案所得到的飞行弹道符合方案弹道,各项指标满足设计要求。During the descend stage of the large airspace change of cruise missile,by pre-installing subsection constant pitch rudder changing law in navigation computer,the celerity of the large airspace change of the missile is kept,as well as the descend tail end of the missile can not rush too much to enter the water.For the strong maneuvering and unpredictability of the missile happening at stage from descend to low level cruise,a fuzzy gain controller is designed to make the transition stage smooth and possessing only one overshoot,and the flight process is stable.The changing law of pitching rudder deflection and angle of attack is compared by using fuzzy gain controller and fixed parameter controllers in transition stage respectively.The simulation results show that the flight trajectory obtained through the proposed method accords with the project trajectory and fulfill all indices of the design demands.

关 键 词：巡航导弹 大空域机动 模糊控制器 方案弹道 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]