Simulation on pressure cure of solid rocket motor grain

被引：5

作者：

Zong, Lu-Hang ^{[1
]}

Du, Cong ^{[1
]}

Lu, Shan ^{[1
]}

Yao, Dong ^{[1
]}

Gao, Jie ^{[1
]}

Sha, Bao-Lin ^{[1
]}

机构：

[1] National Key Laboratory of Combustion, Flow and Thermo-Structure, The 41st Institute of the Fourth Academy of CASC, Xi'an, China

来源：

Guti Huojian Jishu/Journal of Solid Rocket Technology | 2015年 / 38卷 / 05期

关键词：

Rocket engines - Reluctance motors - Curing - Propellants;

D O I：

10.7673/j.issn.1006-2793.2015.05.009

中图分类号：

学科分类号：

摘要：

For those case-bonded casting solid rocket motors (SRMs) with large outside/inside radius ratio of the grain, high thermal strain will be generated in the propellant grain subjected to thermal loading, which significantly limit the performance of SRM. Pressure cure is an effective method to reduce the thermal strain in the grain. In this paper, the theory of pressure cure was analyzed and the relationship between the desired pressure and the parameters of the SRM was deduced. Then, a finite element method (FEM) of pressure cure named two step method was proposed. Theoretical calculation and FEM simulation were carried out on a tube motor with four different material cases. The recommended pressure of pressure cure of four cases were given out. ©, 2015, Journal of Solid Rocket Technology. All right reserved.

引用

页码：653 / 656

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