自由滚转尾翼试飞器滚转特性分析  

Analysis on rolling characteristics of test flight vehicle with free-rolling tail

作　　者：张晓旻[1] 李怀念[1] 程养民[1] 卢睿[1] 王永平[1] 

机构地区：[1]中国航天科技集团公司四院四十一所固体火箭发动机燃烧热结构与内流场国防科技重点实验室,西安710025

出　　处：《固体火箭技术》2008年第4期307-309,共3页Journal of Solid Rocket Technology

摘　　要：自由滚转尾翼是解决鸭式布局导弹的鸭式舵难以差动兼作副翼进行滚动控制的一种技术途径。为验证某鸭式布局试飞器采用自由滚转尾翼方案的可行性,进行了试飞器的固定尾翼和自由滚转尾翼两种模型的风洞试验。试验结果表明,固定尾翼试飞器,当鸭舵作副翼偏转进行滚控时,在尾翼上会产生很大的诱导滚动力矩,抵消鸭舵的控制力矩,致使鸭舵不能进行滚转控制;滚转尾翼可有效减小诱导滚动力矩,实现通过鸭舵进行全弹滚转控制的目的。A kind of technical approach （i. e. free-rolling tail） is used for solving the problem of canard configuration missile in which canard rudder cann＇t simuhaneously finish differential motion and rolling control as aileron. In order to verify the feasibility of free-rolling tail scheme for canard configuration test flight vehicle, two kinds of test-flight vehicle models with fixed-rolllng and free-rolling tail were tested by means of the wind tunnel experiment. The experimental results show that for test-flight vehicle with fixed-rolling tail,when canard rudder used as aileron deflects to conduct rolling control,a large induced rolling moment is produced on the tail to offset control moment of canard rudder, which may cause canard rudder unable to conduct rolling control. The free-rolling tail can effectively reduce induced rolling moment so as to realize rolling control of the missile by means of canard rudder.

关 键 词：鸭式布局 滚动控制 滚转尾翼 

分 类 号：V421.5[航空宇航科学与技术—飞行器设计]