高速稀薄流域防热减阻概念构型气动性能  

Conceptual configuration aerodynamic performance of heat flux and drag reduction in high speed rarefied flow

作　　者：张帅 ZHANG Shuai(Beijing Aerospace Technology Institute,China Aerospace Science and Industry Corporation Limited,Beijing 100074,China)

机构地区：[1]中国航天科工集团有限公司北京空天技术研究所,北京100074

出　　处：《航空动力学报》2022年第1期124-141,共18页Journal of Aerospace Power

基　　金：国家重点研发计划(2019YFA0405304)。

摘　　要：为探究高速稀薄流流域凹腔槽道的气动特性,采用直接模拟蒙特卡罗(DSMC)方法,建立了凹腔深宽比为1,槽道高度分别为0、10、20、30、40 mm以及基准高度为20 mm的唇口钝化半径为2~20 mm的凹腔槽道构型,获得了不同算例的气动热系数和气动力系数的变化情况,分析了不同槽道高度以及不同唇口钝化半径的凹腔槽道构型对气动热与气动力性能的影响。数值结果表明:稀薄流流域中凹腔槽道构型能够达到预期的防热减阻效果,较优构型(槽道高度为20 mm)的防热率与减阻率分别达到6.99%和4.44%;槽道高度越高,减阻效果越好,但防热效率降低甚至出现防热反作用;凹腔腔体内部气体由稀薄流转化为连续流,凹腔内气体压力不断振荡;唇口钝化处理可以在保证阻力系数增加不大的情况下显著降低峰值传热。To investigate the heat flux and drag reduction characteristics of the space vehicle combining the forward-facing cavity and the channel in high speed rarefied flow,numerical study of aerodynamic and aerothermodynamics performance on the space vehicle was conducted via direct simulation Monte Carlo(DSMC)method. Two groups of combinations were established.The aspect ratio of forward-facing cavity was set as 1. The first series of channel with channel heights of 0,10,20,30,40 mm,and the second series of lip bluntness with lip passivation radius of 2-20 mm and the baseline channel height with constant 20 mm had been taken into consideration. Results of the work for applying the cavity-channel concept to space vehicle showed a proposing heating and drag reduction performance. Compared with the original blunt cone, the cavity-channel configuration with channel height of 20 mm had the optimal performance within the range considered, and the heat flux and drag reduction rates reached approximately 6. 99% and4. 44%,respectively. Higher channel height indicated better drag reduction,but the heat protection effectiveness was weakened. The gas inside the cavity changed from rarefied flow to continuous flow and the gas pressure oscillated. There could bring about apparent advantages of heat reduction without any drag increment penalty by employing cavity lip bluntness.

关 键 词：高速稀薄流 凹腔槽道构型 直接模拟蒙特卡罗(DSMC)方法 气动防热 气动减阻 

分 类 号：V423.6[航空宇航科学与技术—飞行器设计]