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气压变化对续航发动机推力的影响研究

A Research of the Influence on Thrust of Sustained Motor Caused by Pressure Change
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摘要 针对某型续航发动机在高海拔地区试验中出现的推力不足问题,分析其设计中存在的缺陷,发现问题在于:喷管出口静压与环境气压压差匹配特性随着海拔的增高发生剧变,从而造成燃气流场的改变。通过数字仿真及模拟试验验证该观点的正确性。提出通过调整续航发动机喷管的扩张比的方法,改善发动机喷口静压与高原大气压的压差,从而保证续航发动机的高原性能。经试验验证,该方案简单易行,具有工程应用性。 The article deeply analyzes the design of sustained motor to solve the problem of insufficient thrust which occurred in a test on high altitude localities.As the article points out,the press reduced as the altitude raised,which cause the changed of the matching between the nozzle outlet pressure and atmospheric pressure and the change of the gas flow field.Digital simulation and experiment proved the validity of the theory.Besides,the article also proposes improved methods.By adjusting the expansion ratio of engine nozzle,we improve the difference of the engine nozzle outlet pressure of and the atmospheric pressure,and ensure the performance of the cruising engine on the plateau.As prove in test,the improve scheme is simple and practical.
作者 刘佳文 王兴平 王龙 LIU Jiawen;WANG Xingping;WANG Long(No.63961 Unit,Beijing 100000,China;Xi’an Modern Control Technology Research Institute,Xi’an 710065,China)
出处 《弹箭与制导学报》 北大核心 2021年第1期32-35,共4页 Journal of Projectiles,Rockets,Missiles and Guidance
关键词 续航发动机 燃气流场 低压环境 推力损失 sustained motor gas flow field low pressure thrust loss
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  • 1祖国君,蔡国,朱定强.喷管流场和羽流场的N-S数值模拟[J].推进技术,1995,16(5):1-6. 被引量:7
  • 2李东霞,徐旭,蔡国飙,张振鹏.火箭发动机气体-颗粒两相流双流体模型研究[J].固体火箭技术,2005,28(4):238-243. 被引量:15
  • 3Issa R I.Solution of the implicit discretized fluid flow equations by operators-splitting[J].Compt Phys,1985,62(1):40-65.
  • 4Issa R I.Solution of the implicit discretized reacting flow equations by operator-splitting[J].Compt Phys,1991,93:388-410.
  • 5Peric M,Kessler R,Scheuerer G..Comparison of finite-volume numerical methods with staggered and collocated grids[J].Comput Fluids,1988,16:265-281.
  • 6Yakhot V,Orszag S A.Renormalization group analysis of turbulence-I:Basic theory[J].Scientific Computing,1986,1:1-51.
  • 7Reed R A. Review of aluminum oxide rocket exhaust particles[ R]. AIAA-93-2819.
  • 8Shih T H. A new k-e Eddy-viscosity model for high reynolds number turbulent flows-model development and validation [ J]. Computers Fluids, 1995,24(3) :227-238.
  • 9http://kinetics, nist. gov/kinetics/index, jsp. Standard Reference Database 17 [ DBIOL] , Version 7.0. @ NIST 2000.
  • 10Troyes J, Boischot A. Multi-phase reactive numerical simulations of a model solid rocket motor exhaust jet [ R ]. AIAA- 2006-4414.

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