凹腔布局对高超声速飞行器气动-推进性能影响  

Effect of cavity flame holder's location on the aero-propulsive performance of hypersonic vehicles

作　　者：黄伟[1] 柳军[1] 罗世彬[1] 王振国[1] 

机构地区：[1]国防科技大学航天与材料工程学院,长沙410073

出　　处：《固体火箭技术》2010年第2期138-141,175,共5页Journal of Solid Rocket Technology

基　　金：国防科技大学优秀研究生创新资助项目(B070101);湖南省研究生创新资助项目

摘　　要：采用二维耦合隐式N-S方程和标准k-ε湍流模型,对高超声速飞行器在发动机通流状态下的内外流场进行了数值仿真,研究了超燃冲压发动机燃烧室中单凹腔和双凹腔串并联布局对飞行器气动-推进性能的影响。发现因粘性而产生的摩阻、摩升以及摩擦力引起的俯仰力矩较压阻、压升以及压力引起的俯仰力矩很小,对于飞行器整体性能而言,可忽略;凹腔之间距离的长短对飞行器气动-推进性能影响强烈,短距离凹腔并联使得燃烧室主流压力抬高得更大,短距离凹腔串联使得上游凹腔对下游凹腔流场影响更大;同时,性能高的凹腔组合在一起能显著提高飞行器整体性能。Two-dimensional coupled implicit N-S equations and standard k-ε turbulent flow models were used to simulate the inner and outer flow field of hypersonic vehicles working under the through-flow condition of motor,and the effects of serial-parallel layout of single cavity flame holder and double cavity flame holders in scramjet combustor on its aero-propulsive performance were investigated.It is found that the pitching moment resulted from frictional drag,frictional lift and frictional force is much less than that from pressure drag,pressure lift and pressure,and can be neglected for bulk performance of vehicle.The distance between cavity flame holders has great effects on the aero-propulsive performance of hypersonic vehicles,cavities in parallel and with shorter distance will make a higher increase of primary flow pressure in combustor,while those in tandem and with short distance will make the effect on flow field in up-stream cavity greater than that in down-stream cavity.Meanwhile,integral performance of vehicles can be improved if high-performance cavity flame holders are combined.

关 键 词：航天推进系统 凹腔 高超声速飞行器 气动-推进性能 

分 类 号：V47[航空宇航科学与技术—飞行器设计]