固体火箭发动机喷管阻尼特性的数值仿真

发布时间：2018-01-11 07:38

本文关键词：固体火箭发动机喷管阻尼特性的数值仿真　出处：《航空动力学报》2016年09期 　论文类型：期刊论文

【摘要】：为了探究影响固体火箭发动机喷管阻尼特性的关键因素,基于典型柱状装药固体火箭发动机二维简化模型,利用脉冲衰减法,开展喷管阻尼特性数值仿真计算,研究了喉通比和燃烧室长度对喷管阻尼常数的影响规律,结果发现数值模拟结果与经验公式理论预估结果有较好的一致性,证实了该数值方法的有效性;在此基础上,进一步探讨了无法由经验公式直接获知的诸如喷管收敛半角以及收敛型面对喷管阻尼常数的影响规律,结果表明:收敛半角对喷管阻尼常数有很大的影响,在设计范围内,较小的收敛角有益于提高喷管阻尼特性;收敛段型面对喷管阻尼也有一定的影响,凸型型面阻尼特性优于锥型型面,锥形型面优于凹形型面.
[Abstract]:In order to explore the impact of key factors of damping characteristics of solid rocket motor nozzle, the typical column charge of solid rocket motor based on the simplified two-dimensional model, using the pulse decay method, carry out numerical simulation of nozzle damping calculation of combustion chamber length on the throat area and the nozzle of the damping constant, the results show that the numerical results and theory formula the prediction results are in good agreement, confirming the validity of the numerical methods; on this basis, to further explore the empirical formula cannot be directly obtained and convergent nozzle face influence such as convergent nozzle, the damping constant of the results show that the convergence angle has a great influence on the nozzle damping constant, in the scope of design in the smaller the convergence angle is beneficial to improve the damping characteristics of nozzle convergent section; with nozzle damping has a certain impact, convex surface resistance The property of the conical type is superior to the conical type, and the conical surface is superior to the concave shape.

【作者单位】：北京理工大学宇航学院;中国航天科技集团公司中国运载火箭技术研究院研究与发展中心;
【分类号】：V435
【正文快照】： 不稳定燃烧固体火箭是发动机研制过程中经常遇到的棘手问题之一[1-2].自20世纪中叶以来,国内外学者先后花费了大量的人力、物力和财力来研究该问题.但是该问题仍是发动机研制过程中常遇到的棘手问题之一,轻则引起内弹道曲线异常,重则引起发动机爆炸,导致灾难性后果.从线性理论

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