偏转弹头导弹气动方案设计研究  

Aerodynamic Design of Deflectable Nose Missile

作　　者：梁毅辰 

机构地区：[1]西安航空学院飞行器学院,西安710077

出　　处：《兵器装备工程学报》2016年第7期47-50,共4页Journal of Ordnance Equipment Engineering

摘　　要：在外军某型导弹的基础上,将偏转弹头控制方式引入导弹,重新设计了其气动方案;在设计的过程当中,针对偏转弹头导弹特有设计约束,对原准弹的设计进行了调整;新设计的方案综合考虑了各分系统之间的约束,解决了将这种新的控制方式引入导弹设计后所带来的一些问题;计算结果显示:该气动方案解决了一般偏转弹头导弹低速可用过载低的问题,与传统导弹相比具有包络小,阻力低,高速下可用过载大等特点。The aerodynamics and dynamics characteristics of the deflectable nose missile were analyzed and some constraint conditions were proposed, and according to the constraint conditions of it, a deflectable nose missile’s mission and aerodynamic configuration was designed based on a foreign short-range air-defense missile and the aerodynamic characteristics of the missile was analyzed. The result of the analysis shows that the low-available overload-problem in low velocity situation of the deflectable nose missile has been solved by the new design. And compared with the traditional missile,the deflectable nose missile has smaller envelop,lower drag and higher available overload in high speed.

关 键 词：航空宇航科学与技术 飞行器设计 导弹总体设计 偏转弹头导弹 

分 类 号：V421.1[航空宇航科学与技术—飞行器设计]