遭毁伤巡航导弹气动特性风洞实验研究  

A Study on Aerodynamic Characteristics of Damaged Cruise Missile

作　　者：李向荣[1] 王海福[1] 贺金丽[1] 

机构地区：[1]北京理工大学爆炸科学与技术国家重点实验室,北京100081

出　　处：《弹道学报》2006年第1期6-9,共4页Journal of Ballistics

基　　金：国家973资助项目(51309)

摘　　要：通过对“战斧”多用途巡航导弹风洞实验模型的设计和不同马赫数、攻角及侧滑角下气动特性参数的测试,得到弹翼折弯角对侧向力系数、偏航力矩系数、升力系数以及前部阻力系数的影响规律.结果表明,随着弹翼折弯角的增大,侧向力系数和偏航力矩系数近似呈线性增长,这种影响随马赫数增大而增强,但对升力系数、前部阻力系数、滚转力矩系数、俯仰力矩系数等特性参数的影响并不显著.Wind tunnel tests were performed on damaged ＂Tomahawk＂ multipurpose cruise missile to g Mach numb lateral force et aerodynamic er, attack angle characteristics and side slip a coefficient, yawing moment c parameters under the conditions of the different ngle. The effect rules of bend angle of the wing on oefficient, lift force coefficient and frontal drag coefficient were obtained. The results show that lateral force coefficient and yawing moment coefficient increase linearly with the bend angle of the wing, and the higher flight Mach number, the more notablely the effect becomes. Lift force coefficient, frontal drag coefficient, rolling moment coefficient and pitching moment coefficient aren＇t affected significantly.

关 键 词：巡航导弹 风洞实验 气动特性 

分 类 号：TJ413.9[兵器科学与技术—火炮、自动武器与弹药工程]