自旋尾翼鸭式布局导弹的滚转特性  

Rolling Characteristics of Canard-Controlled Missiles with a Free-Spinning Tail

作　　者：雷娟棉 居贤铭[1] 吴甲生[1] 

机构地区：[1]北京理工大学机电工程学院,北京100081

出　　处：《北京理工大学学报》2004年第8期657-659,共3页Transactions of Beijing Institute of Technology

基　　金：国家部委预研项目(13.3.4)

摘　　要：分析鸭式布局导弹的滚转耦合机理,进行固定尾翼鸭式布局导弹和自旋尾翼鸭式布局导弹的风洞试验.实验结果表明,对固定尾翼鸭式布局导弹,当鸭舵做副翼偏转进行滚转控制时,在导弹上产生数值很大的反向诱导滚转力矩,使鸭舵难以进行滚转控制;尾翼自旋减小了鸭舵副翼偏转进行滚转控制时导弹上产生的反向诱导滚转力矩,使鸭舵能对导弹进行滚转控制.尾翼自旋是实现鸭舵/尾翼气动解耦,使鸭舵进行滚转控制的有效措施.The roll coupling mechanism of a canard missile is analyzed, and wind tunnel experiments were conducted to study the canard roll control authority of canard-configuration missiles installed with fixed- and free-spinning tails. Experimental results showed that canards were ineffective as roll control devices for canard-controlled missiles with fixed-tail, because noticeable reverse roll moments were induced when the canard have roll command deflection. Yet if the tail spins freely, the reverse induced roll moments could be much reduced, allowing the canard to execute the roll control. Thus, the free-spinning tail is an effective means of eliminating roll coupling and permitting the canard to execute roll control.

关 键 词：鸭式布局 气动特性 风洞实验 自旋尾翼 滚转控制特性 

分 类 号：V211.24[航空宇航科学与技术—航空宇航推进理论与工程]