火箭增程乘波外形导弹弹道特性研究  

Trajectory Characteristics of Hypersonic Waverider Missile with Rocket Extended Range

作　　者：郭迪龙[1] 张杰[1] 康宏琳[2] 王发民[1] 

机构地区：[1]中国科学院力学研究所高温气动重点实验室,北京100080 [2]北京航空航天大学计算流体国家重点实验室,北京100083

出　　处：《弹道学报》2006年第4期1-3,20,共4页Journal of Ballistics

基　　金：国家自然科学基金项目(90405012)

摘　　要：基于椭圆锥相交流场,采用非轴对称设计方法生成了一种带火箭增程的乘波外形高超声速导弹,并在给定攻角条件下对乘波外形导弹的弹道进行了仿真.仿真结果表明:导弹的飞行轨迹为波浪形;在满足热防护的条件下,给定乘波外形和初始滑翔速度的导弹存在一个较优的初始滑翔高度;导弹自带增程火箭的点火时间越早,其飞行距离越远.Based on the flow field of intersecting elliptical cone, a hypersonic waverider missile with extended range rocket was designed by non-axissymmetric method, and the trajectory of the missile was also simulated under the conditions that angle of attack was given. The results indicate that the trajectory of the missile is wavy. Under the conditions that the thermal protection is satisfied, there is a optimal initial gliding attitude for a missile with given initial gliding speed and waverider configuration. The earlier the extending-range rocket starts up, the farther the missile flies.

关 键 词：火箭增程 乘波外形 高超声速导弹 升阻比 弹道仿真 

分 类 号：TJ012.3[兵器科学与技术—兵器发射理论与技术]