带分散式进气道SRM喷管扩张段补充燃烧研究
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摘要
基于Fluent平台,采用有限速率/涡破碎燃烧模型和组分输运模型对分布式进气道补充燃烧装置进行了数值仿真,研究了不同飞行攻角下发动机推力的变化,以及关闭进气道进行推力矢量控制的方法。结果表明,随着飞行攻角的增大,推力和进气道阻力先增大后减小,实际推力略大于标准推力且先增大后减小;关闭某个进气道后,该进气道出口下游二次燃烧区域消失,在喷管壁面上产生压力分布不均,产生侧向力。
Based on Fluent platform,the numerical simulation of distributed supplement combustion of diverted inlet was carried out by using the finite-rate/eddy-dissipation combustion model and the component transport model.The thrust variation of the engine at different flight angles of attack and the method of thrust vector control by closing the intake port were studied.The results show that with the increase of the angle of attack,the thrust and the resistance of the inlet increase first and then decrease,and the actual thrust is slightly larger than the standard thrust and increases first and then decreases.After closing an inlet,the secondary combustion area downstream of the inlet expansion disappears,resulting in uneven pressure distribution on the nozzle wall,resulting in lateral force
Based on Fluent platform,the numerical simulation of distributed supplement combustion of diverted inlet was carried out by using the finite-rate/eddy-dissipation combustion model and the component transport model.The thrust variation of the engine at different flight angles of attack and the method of thrust vector control by closing the intake port were studied.The results show that with the increase of the angle of attack,the thrust and the resistance of the inlet increase first and then decrease,and the actual thrust is slightly larger than the standard thrust and increases first and then decreases.After closing an inlet,the secondary combustion area downstream of the inlet expansion disappears,resulting in uneven pressure distribution on the nozzle wall,resulting in lateral force
引文
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[5]李洁,冯喜平,李进贤,等.二次进气角度对固冲发动机掺混燃烧的影响[J].科学技术与工程,2013(16):4757-4760.
[6]黄利亚,夏智勋,陈斌斌.固体火箭冲压发动机二次燃烧试验研究[J].固体火箭技术,2017,40(5):552-556.
[7]王革,肖雪峰,李垚.双孔燃气二次喷射推力矢量性能影响因素数值分析[J].固体火箭技术,2014(5):622-627.
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[2]LUX J,HAIDN O.Flame Stabilization in High-Pressure Liquid Oxygen/Methane Rocket Engine Combustion[J].Journal of Propulsion&Power,2009,25(1):15-23.
[3]BESSER H L.History of ducted rocket development at Bayern-Chemie[R].AIAA paper,2008,5261.
[4]金楠楠,严聪,李敏剑.空燃比对固冲发动机二次燃烧的影响研究[J].弹箭与制导学报,2010(5):133-136.
[5]李洁,冯喜平,李进贤,等.二次进气角度对固冲发动机掺混燃烧的影响[J].科学技术与工程,2013(16):4757-4760.
[6]黄利亚,夏智勋,陈斌斌.固体火箭冲压发动机二次燃烧试验研究[J].固体火箭技术,2017,40(5):552-556.
[7]王革,肖雪峰,李垚.双孔燃气二次喷射推力矢量性能影响因素数值分析[J].固体火箭技术,2014(5):622-627.
[8]GREEN C J.Liquid injection thrust vector control[J].AIAA J.1963,l(3):573-578.
[9]王根彬.空气二次喷射推力向量控制[J].国外导弹与宇航,1983(9):17-18,29.
[10]REGINALD G W,BAILY R V.Fluidic thrust vectoring and throat control exhaust nozzle[R].AIAA 2002-4060.