摘要
针对高超声速飞行器绕流与反作用控制系统(RCS)喷流相互干扰过程中高温气体非平衡效应的影响问题,基于高温空气及喷流燃气物理化学模型,通过数值求解三维非平衡雷诺平均Navier-Stokes(RANS)方程,开展了典型外形喷流干扰非平衡流场的数值模拟,研究了绕流空气非平衡效应、喷流燃气非平衡效应及其综合的流场高温非平衡效应的影响,分析了不同飞行条件下流场高温气体非平衡效应对流场结构及飞行器气动力热特性影响的变化规律。研究表明:绕流空气非平衡效应在高马赫数下影响显著,表现为减小喷流附加推力、降低干扰区热流峰值,随着马赫数升高,其影响逐渐增大;喷流燃气非平衡效应在不同状态下的影响存在差别,在低空状态下,燃气组分主要发生复燃/复合反应,导致喷流附加推力增大、干扰区热流峰值升高,在高空状态下,燃气组分主要发生离解反应,导致喷流附加推力减小、干扰区热流峰值降低,沿弹道高度升高,喷流燃气的复合反应减弱而离解反应增强;为了更加真实地模拟高超声速飞行器RCS喷流干扰流场特性,有必要全面地考虑流场中的高温气体非平衡效应。
The non-equilibrium effect of high temperature gas in hypersonic vehicle reaction control system’s(RCS)jet interaction flow field was studied.Based on high temperature air and jet gas’s physical and chemical reaction model and by solving three-dimensional non-equilibrium Reynolds-averaged NavierStokes(RANS)equations,numerical simulation of typical configuration’s jet interaction non-equilibrium flow field was conducted,the influences of air and jet gas’s non-equilibrium effect were analyzed,and the influences under various flight conditions were also discussed.The results showed that:air’s nonequilibrium effect was significant when flight Mach number was high,which can reduce the additional thrust produced by jet interaction,and decrease the heat flux in jet interaction area;high flight velocity could enhance this effect.Jet gas’s non-equilibrium effect varied under different conditions;when flight altitude was low,jet gas’s components mainly involved in afterburning/recombination reactions,which can increase additional thrust and the heat flux in jet interaction area;when flight altitude was high,jet gas’s components mainly involved in dissociation reactions,which can decrease additional thrust and the heat flux;as the flight altitude increased through the trajectory,jet gas’s dissociation reactions were enhanced and recombination reactions were weakened.To simulate hypersonic vehicle’s jet interaction flow field more precisely,it is necessary to consider high temperature gas non-equilibrium effect.
作者
傅杨奥骁
高铁锁
丁明松
刘庆宗
江涛
董维中
FU Yang’aoxiao;GAO Tiesuo;DING Mingsong;LIU Qingzong;JIANG Tao;DONG Weizhong(Computational Aerodynamics Institute,China Aerodynamics Research and Development Center,Mianyang Sichuan 621000,China)
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2024年第3期102-114,共13页
Journal of Aerospace Power
基金
基础加强计划重点基础研究项目(2019-JCJQ-ZD-047)
国家重点研发计划项目(2019YFA0405203)。
关键词
高超声速飞行器
反作用控制系统(RCS)
喷流干扰
高温气体非平衡效应
复燃反应
离解反应
hypersonic vehicle
reaction control system(RCS)
jet interaction
non-equilibrium effect of high temperature gas
afterburning reaction
dissociation reaction
