空射火箭箭机分离过程气动特性仿真  

Aerodynamic Characteristics Simulation Study of Air-launched Launch Vehicle in the Process of Rocket Separating from Plane

作　　者：屈亮[1] 张登成[1] 张艳华[1] 胡孟权[1] 李达[1] 

机构地区：[1]空军工程大学航空航天工程学院,陕西西安710038

出　　处：《空军工程大学学报（自然科学版）》2013年第3期28-32,共5页Journal of Air Force Engineering University(Natural Science Edition)

基　　金：航空科学基金资助项目(20110596007)

摘　　要：为研究内装式空中发射运载火箭在箭机分离过程中的气动特性尤其是大迎角情况下的气动变化规律,应用计算流体力学(CFD)软件中的k-ω模型对火箭气动特性进行了仿真研究,得到火箭气动特性随马赫数和迎角的变化规律,同时对改进后的火箭模型进行气动特性分析。仿真结果表明:发现火箭尾部改进成收敛-扩张型喷管可使火箭下落初期有一个抬头力矩,有利于运载火箭初期快速调整姿态;当快到达预期点火姿态时,由于气动力作用点后移产生的与角速度方向相反的力矩,可迫使运载火箭稳定,从而更容易地捕捉到点火角度,并保证点火时的姿态稳定。For studying the aerodynamic characteristics of rocket in the process of the rocket separating from the plane internally carried air-launched launch vehicle, especially when the rocket is at high angle of at-tack, CFD is applied to the simulation of rocket aerodynamic characteristics. Based on the improvement of rocket shape, the rocket aerodynamic characteristics with Mach number and angle of attack can be ob-tained. The analysis of the aerodynamic characteristics of the improved rocket model shows that the rocket tail improved into a convergent nozzle is of great benefit to the attitude adjustment. These analyses provide a theoretical foundation for the further research on rocket attitude stabilization and track design.

关 键 词：空射火箭 箭机分离 大迎角 气动特性 非对称涡 

分 类 号：V475.1[航空宇航科学与技术—飞行器设计]