Influence of Different Velocities on Muzzle Flow Field
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摘要
A two?dimensional axisymmetric numerical simulation was successfully carried out on the muzzle flow field of a 300 mm?caliber counter?mass propelling gun. Based on the FLUENT software,using the finite volume method(FVM)and the realizable k?ε turbulence model,we adopted the holistic movement of a partitioned mesh processing method coupled with the intermediate ballistic model and the six degree?of?freedom model(6?DOF). We compared the flow field characteristics at the velocity of 1 730.4,978.3,and 323.4 m/s. The results indicate that the pressure of the hypersonic initial flow field is much higher than that of the subsonic and supersonic initial flow fields. In the case of the subsonic(323.4 m/s)flow field,the tiny disturbance spreads throughout the whole domain. But in the cases of the supersonic(978.3 m/s) and the hypersonic(1 730.4 m/s) flow fields,it cannot spread to the upstream disturbance source,and the disturbance domain of the supersonic flow field is wider than that of the hypersonic. It is noted that the subsonic flow field has a rounded shock wave before the projectile. However,in the supersonic and hypersonic flow fields,a shear layer is formed which begins from the head of the projectile and extends outward from the side of the projectile. Then a multi?layer shock wave is formed composed of coronal shock waves,bottom shock waves,reflected shock waves,and Mach disk.
A two?dimensional axisymmetric numerical simulation was successfully carried out on the muzzle flow field of a 300 mm?caliber counter?mass propelling gun. Based on the FLUENT software,using the finite volume method(FVM)and the realizable k?ε turbulence model,we adopted the holistic movement of a partitioned mesh processing method coupled with the intermediate ballistic model and the six degree?of?freedom model(6?DOF). We compared the flow field characteristics at the velocity of 1 730.4,978.3,and 323.4 m/s. The results indicate that the pressure of the hypersonic initial flow field is much higher than that of the subsonic and supersonic initial flow fields. In the case of the subsonic(323.4 m/s)flow field,the tiny disturbance spreads throughout the whole domain. But in the cases of the supersonic(978.3 m/s) and the hypersonic(1 730.4 m/s) flow fields,it cannot spread to the upstream disturbance source,and the disturbance domain of the supersonic flow field is wider than that of the hypersonic. It is noted that the subsonic flow field has a rounded shock wave before the projectile. However,in the supersonic and hypersonic flow fields,a shear layer is formed which begins from the head of the projectile and extends outward from the side of the projectile. Then a multi?layer shock wave is formed composed of coronal shock waves,bottom shock waves,reflected shock waves,and Mach disk.
A two?dimensional axisymmetric numerical simulation was successfully carried out on the muzzle flow field of a 300 mm?caliber counter?mass propelling gun. Based on the FLUENT software,using the finite volume method(FVM)and the realizable k?ε turbulence model,we adopted the holistic movement of a partitioned mesh processing method coupled with the intermediate ballistic model and the six degree?of?freedom model(6?DOF). We compared the flow field characteristics at the velocity of 1 730.4,978.3,and 323.4 m/s. The results indicate that the pressure of the hypersonic initial flow field is much higher than that of the subsonic and supersonic initial flow fields. In the case of the subsonic(323.4 m/s)flow field,the tiny disturbance spreads throughout the whole domain. But in the cases of the supersonic(978.3 m/s) and the hypersonic(1 730.4 m/s) flow fields,it cannot spread to the upstream disturbance source,and the disturbance domain of the supersonic flow field is wider than that of the hypersonic. It is noted that the subsonic flow field has a rounded shock wave before the projectile. However,in the supersonic and hypersonic flow fields,a shear layer is formed which begins from the head of the projectile and extends outward from the side of the projectile. Then a multi?layer shock wave is formed composed of coronal shock waves,bottom shock waves,reflected shock waves,and Mach disk.
引文
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[15]DAI S L,XU H Q,SUN L.Numerical simulation of gun muzzle flow field including movable boundary[J].Journal of Ballistics,2009,21(4):84?87.(in Chi?nese)
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[18]FLORIO L A.Effect of vent opening area and arrange?ment on gas flow field as gas propelled cylinder exits a flow tube[J].Mechanic,2009,45(4):475?501.
[19]ZHANG H H,CHEN Z H,JIANG X H,et al.In?vestigations on the exterior flow field and the efficiency of the muzzle brake[J].Journal of Mechanical Science and Technology,2013,27(2):95?101.
[20]ZHANG H H,CHEN Z H,JIANG X H,et al.Investi?gation on the blast wave structures of a high?speed pro?jectile flying through different muzzle brakes[J].Acta Armamentarii,2012,33(5):563?567.(in Chinese)
[21]LIU X,LIN Z X,WAN C.Simulation study of super?sonic flow instability mechanism[J].Chinese Journal of Theoretical and Applied Mechanics,2008,40(5):577?584.(in Chinese)
[22]ZHANG H,TAN J J,CUI D M.Numerical simula?tion method of flow field with muzzle attachments[J].Journal of Gun Launch&Control,2007(2):48?51.(in Chinese)
[23]WENG C S,WANG H.Computing interior ballistics[M].Beijing:National Defense Industry Press,2006.
[24]CAI G B,WANG H Y.Numerical simulation of 3?Dflow field of solid rocket motor chamber[J].Journal of Propulsion Technology,1995(5):59?64.
[25]BAO T Y,QIU W J.Internal ballistics[M].Beijing:Beijing Institute of Technology Press,1995:214?218.
[26]JIN Z M,WENG C S.Advanced interior ballistics[M].Beijing:Higher Education Press,2003.(in Chi?nese)
[27]JIANG X H,FAN BC,LI H Z.Numerical investiga?tion on the muzzle flow with dynamic mesh based on ALE equation[J].Chinese Journal of Computational Mechanics,2008,25(4):563?567.(in Chinese)
[2]JIANG X H,CHEN Z H,FAN B C,et al.Numeri?cal simulation of blast flow fields induced by a high?speed projectile[J].Shock Waves,2008(18):205?212.(in Chinese)
[3]WANG Y W,HUANG C G,FANG X,et al.Cloud cavitating flow over a submerged axisymmetric projec?tile and comparison between two?dimensional RANSand three?dimensional large?eddy simulation methods[J].Journal of Fluids Engineering,2016,138(6):1246?1256.(in Chinese)
[4]SU X P,QIAN L F,DAI J S.Muzzle flow field simu?lation of gun with a muzzle attachment[J].Computer Simulation,2009,26(9):15?18.(in Chinese)
[5]SUN D C,CAI T M.Effecting parameters of super?sonic flow field with secondary injection[J].Journal of Propulsion Technology,2001,22(2):147?150.(in Chinese)
[6]LIU X,LIN Z X,WAN C.Simulation study of super?sonic flow instability mechanism[J].Chinese Journal of Theoretical and Applied Mechanics,2008,40(5):577?584.(in Chinese)
[7]TAN L B,HOU B L,CHEN W M.Gun recoil force reduction technology[J].Journal of Gun Launch&Control,2006(4):69?72.(in Chinese)
[8]VIRE A,SPINNEKEN J,PIGGOTT M D,et al.Application of the immersed?body method to simulate wave?structure interactions[J].European Journal of Mechanics B/Fluids,2016(55):330?339.
[9]YOU G Z,XU H Q,YANG Q R.Intermediate Bal?listic[M].Beijing:National Defence Industry Press,2003:1?3.(in Chinese)
[10]HE F,XIE J S,HAO P F,et al.Computation of axi?symmetric jet flow with Spalart?Allmaras turbulence model[J].Journal of Propulsion Technology,2001,22(1):43?46.(in Chinese)
[11]WATANABE R,FUJII K,HIGASHINO F.Three?dimensional flow computation around a projec?tile overtaking a preceding shock wave[J].Journal of Spacecraft and Rockets,1998,35(5):619?625.
[12]MERLEN A,DYMENT A.Similarity and asymptot?ic analysis for gun?firing aerodynamics[J].Journal of Fluid Mechanics,1991,225(225):497?528.
[13]WANG Y,JIANG X H,Yang X P,et al.Numerical simulation on jet noise induced by complex flows dis?charging from small caliber muzzle[J].Explosion and Shock Waves,2014,34(4):508?512.(in Chinese)
[14]JIANG K,WANG H.Numerical simulation of muzzle flow field based on dynamic meshing technique[J].Journal of Gun Launch&Control,2010(3):1?4.(in Chinese)
[15]DAI S L,XU H Q,SUN L.Numerical simulation of gun muzzle flow field including movable boundary[J].Journal of Ballistics,2009,21(4):84?87.(in Chi?nese)
[16]WANG S S,ZHENG J,JIA C Z,et al.Numerical sim?ulation of muzzle blast flow field with muzzle brake[J].Fire Control&Command Control,2011,36(2):148?151.(in Chinese)
[17]GAO S Z,ZHAO R X,MA D W.Cannon computa?tional fluid dynamics[M].Beijing:Weapons Industry Press,1995:165?172.
[18]FLORIO L A.Effect of vent opening area and arrange?ment on gas flow field as gas propelled cylinder exits a flow tube[J].Mechanic,2009,45(4):475?501.
[19]ZHANG H H,CHEN Z H,JIANG X H,et al.In?vestigations on the exterior flow field and the efficiency of the muzzle brake[J].Journal of Mechanical Science and Technology,2013,27(2):95?101.
[20]ZHANG H H,CHEN Z H,JIANG X H,et al.Investi?gation on the blast wave structures of a high?speed pro?jectile flying through different muzzle brakes[J].Acta Armamentarii,2012,33(5):563?567.(in Chinese)
[21]LIU X,LIN Z X,WAN C.Simulation study of super?sonic flow instability mechanism[J].Chinese Journal of Theoretical and Applied Mechanics,2008,40(5):577?584.(in Chinese)
[22]ZHANG H,TAN J J,CUI D M.Numerical simula?tion method of flow field with muzzle attachments[J].Journal of Gun Launch&Control,2007(2):48?51.(in Chinese)
[23]WENG C S,WANG H.Computing interior ballistics[M].Beijing:National Defense Industry Press,2006.
[24]CAI G B,WANG H Y.Numerical simulation of 3?Dflow field of solid rocket motor chamber[J].Journal of Propulsion Technology,1995(5):59?64.
[25]BAO T Y,QIU W J.Internal ballistics[M].Beijing:Beijing Institute of Technology Press,1995:214?218.
[26]JIN Z M,WENG C S.Advanced interior ballistics[M].Beijing:Higher Education Press,2003.(in Chi?nese)
[27]JIANG X H,FAN BC,LI H Z.Numerical investiga?tion on the muzzle flow with dynamic mesh based on ALE equation[J].Chinese Journal of Computational Mechanics,2008,25(4):563?567.(in Chinese)