基于声能共振仿真的固体发动机声不稳定趋势研究
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摘要
防空导弹发动机采用了大装填、大长径比、高压强等设计以提高性能,在复杂飞行条件下不稳定燃烧问题时有发生,致使发动机压强及推力振荡,对导弹的制导和控制造成了消极影响。针对防空导弹发动机出现的轴向声不稳定现象,从声能共振仿真角度出发,对发动机燃烧室声腔进行声学响应分析,根据发动机结构特性评估出现声不稳定的趋势,从而指导防空导弹发动机的设计。通过仿真计算,得到大长径比、锥体构型及工作后期更易出现声不稳定现象,与某型发动机的不稳定燃烧问题一致。
In order to improve the performance,the air defense missile motor adopts the design of large filling,large aspect and high pressure.The unstable combustion occurs in complex flight conditions,which causes the oscillation of pressure and thrust,and hence adversely affects the guidance and control of the missile.In order to solve the problem of axial acoustic instability,this paper analyzes the acoustic response of the combustion chamber from the perspective of acoustic resonance.Evaluate the trend of unstable combustion problems by the structural characteristics of motor and guide the design of motor.The conclusion obtained by simulation is that the large aspect ratio,the conical configuration and the late stage of working are prone to acoustic instability,which is in agreement with the unstable combustion problem of a motor.
In order to improve the performance,the air defense missile motor adopts the design of large filling,large aspect and high pressure.The unstable combustion occurs in complex flight conditions,which causes the oscillation of pressure and thrust,and hence adversely affects the guidance and control of the missile.In order to solve the problem of axial acoustic instability,this paper analyzes the acoustic response of the combustion chamber from the perspective of acoustic resonance.Evaluate the trend of unstable combustion problems by the structural characteristics of motor and guide the design of motor.The conclusion obtained by simulation is that the large aspect ratio,the conical configuration and the late stage of working are prone to acoustic instability,which is in agreement with the unstable combustion problem of a motor.
引文
[1]张翔宇,甘晓松,高波,等.导弹飞行过载对固体发动机不稳定燃烧的影响研究[C]//中国宇航学会固体火箭推进专业委员会第33届学术年会论文集,2016.ZHANG Xiangyu,GAN Xiaosong,GAO Bo,et al.Research on the influence of the overload of the missile on the unstable combustion of SRM[C]//The 33th Session of the CSA,2016.
[2]胡松启.固体火箭发动机燃烧基础[M].北京:宇航出版社,2007.HU Songqi.The combustion foundation of SRM[M].Beijing:China Astronautic Publishing House,2007.
[3]French J C.Tangential mode instability of SRMs with even and odd numbers of slots[R].AIAA 2002-3612.
[4]Nicoud F,Benoit L,Sensiau C,et al.Acoustic modes in combustors with complex impedances and multidimensional active flames[R].AIAA 2007-426.
[5]操作,谢蔚民,周金仙.固体火箭发动机的声学分析及燃烧稳定性预估[J].推进技术,1992,13(3):8-15.CAO Z,XIE W M,ZHOU J X.A method of acoustic analysis and predication of the combustion stability for solid rocket motors[J].Journal of Propulsion Technology,1992,13(3):8-15.
[6]苏万兴,李世鹏,张峤,等.某固体火箭发动机工作末期不稳定燃烧[J].航空动力学报,2013,28(10):2376-2383.SU W X,LI S P,ZHANG Q,et al.Combustion instability at end of burning in a solid rocket motor[J].Journal of Aerospace Power,2013,28(10):2376-2383.
[7]李娟,王占利,王栋,等.某型固体火箭发动机不稳定燃烧仿真分析与试验.固体火箭技术,2018,41(2):151-155.LI Juan,WANG Zhanli,WANG Dong,et al.Simulation analysis and experiment on discontinuous combustion of a solid rocket motor[J].Journal of Solid Rocket Technology.2018,41(2):151-155.
[8]杨向明,刘佩进,陈晓龙.翼柱型装药固体火箭发动机燃烧室声场分析[J].宇航学报,2008,29(5):1593-1597.YANG Xiangming,LIU Peijin,CHEN Xiaolong.Analyse of acoustic property with complicated grain shape in combustion chamber of SRM[J].Joumal of Astronautics,2008,29(5):1593-1597.
[9]刘佩进,金秉宁,李强.战术导弹固体发动机燃烧不稳定研究概述[J].固体火箭技术,2012,35(4):446-449.LIU Peijin,JIN Bingning,LI Qiang.A survey of combustion instability in tactical SRM[J].Joumal of Solid Rocket Technology.2012,35(4):446-449.
[10]王治国.MSC.ACTRAN工程声学有限元分析理论与应用[M].北京:国防工业出版社,2007.WANG Zhiguo.The theory and application of the finite element analysis of engineering acoustic[M].National Defense Industry Press,2007.
[11]Anthoine J,Buchlin J M,Hirschberg A.Effect of nozzle cavity on resonance in large SRM:theoretical modeling[J].Joumal of Propulsion and Power,2002,18(2):304-311.
[12]苏万兴,李要建,陈升泽,等.潜入式喷管对固体火箭发动机工作稳定性影响[J].推进技术,2016,37(8):1529-1533.SU Wanxing,LI Yaojian,CHEN Shengze,et al.Effects of submerged nozzle on stability of solid rocket motor[J].Journal of Propulsion Technology,2016,37(8):1529-1533.
[13]Culick F E C.Nonlinear behavior of acoustic waves in combustion chambers[J].Acta Astronautica,1976(3):735-757.
[2]胡松启.固体火箭发动机燃烧基础[M].北京:宇航出版社,2007.HU Songqi.The combustion foundation of SRM[M].Beijing:China Astronautic Publishing House,2007.
[3]French J C.Tangential mode instability of SRMs with even and odd numbers of slots[R].AIAA 2002-3612.
[4]Nicoud F,Benoit L,Sensiau C,et al.Acoustic modes in combustors with complex impedances and multidimensional active flames[R].AIAA 2007-426.
[5]操作,谢蔚民,周金仙.固体火箭发动机的声学分析及燃烧稳定性预估[J].推进技术,1992,13(3):8-15.CAO Z,XIE W M,ZHOU J X.A method of acoustic analysis and predication of the combustion stability for solid rocket motors[J].Journal of Propulsion Technology,1992,13(3):8-15.
[6]苏万兴,李世鹏,张峤,等.某固体火箭发动机工作末期不稳定燃烧[J].航空动力学报,2013,28(10):2376-2383.SU W X,LI S P,ZHANG Q,et al.Combustion instability at end of burning in a solid rocket motor[J].Journal of Aerospace Power,2013,28(10):2376-2383.
[7]李娟,王占利,王栋,等.某型固体火箭发动机不稳定燃烧仿真分析与试验.固体火箭技术,2018,41(2):151-155.LI Juan,WANG Zhanli,WANG Dong,et al.Simulation analysis and experiment on discontinuous combustion of a solid rocket motor[J].Journal of Solid Rocket Technology.2018,41(2):151-155.
[8]杨向明,刘佩进,陈晓龙.翼柱型装药固体火箭发动机燃烧室声场分析[J].宇航学报,2008,29(5):1593-1597.YANG Xiangming,LIU Peijin,CHEN Xiaolong.Analyse of acoustic property with complicated grain shape in combustion chamber of SRM[J].Joumal of Astronautics,2008,29(5):1593-1597.
[9]刘佩进,金秉宁,李强.战术导弹固体发动机燃烧不稳定研究概述[J].固体火箭技术,2012,35(4):446-449.LIU Peijin,JIN Bingning,LI Qiang.A survey of combustion instability in tactical SRM[J].Joumal of Solid Rocket Technology.2012,35(4):446-449.
[10]王治国.MSC.ACTRAN工程声学有限元分析理论与应用[M].北京:国防工业出版社,2007.WANG Zhiguo.The theory and application of the finite element analysis of engineering acoustic[M].National Defense Industry Press,2007.
[11]Anthoine J,Buchlin J M,Hirschberg A.Effect of nozzle cavity on resonance in large SRM:theoretical modeling[J].Joumal of Propulsion and Power,2002,18(2):304-311.
[12]苏万兴,李要建,陈升泽,等.潜入式喷管对固体火箭发动机工作稳定性影响[J].推进技术,2016,37(8):1529-1533.SU Wanxing,LI Yaojian,CHEN Shengze,et al.Effects of submerged nozzle on stability of solid rocket motor[J].Journal of Propulsion Technology,2016,37(8):1529-1533.
[13]Culick F E C.Nonlinear behavior of acoustic waves in combustion chambers[J].Acta Astronautica,1976(3):735-757.