Three-dimension analysis of solid rocket motor grain was presented based on incompressible and nearly incompressible viscoelastic finite element method.
基于不可压和近似不可压粘弹性有限元法，对固体火箭发动机药柱进行了三维分析。
The 300mm diameter solid propellant rocket motor employs a composite propellant end burning grain.
直径300毫米的固体推进剂火箭发动机采用了复合推进剂端燃药柱。
The results of this paper are of practical significance to grain structural integrity analysis and computation of solid rocket engines.
该文的结果对固体火箭发动机装药结构完整性分析计算有重要的实用价值。
According to the thermal shielding model of solid rocket motor, an approach of ablation heat shield design of end-burning grain with embedded wire was put forward in this paper.
根据固体火箭发动机绝热防护模型，提出了一种嵌金属丝端燃装药绝热层设计方法。
In order to improve working reliability, increase grain mass, and achieve ignition and stage separation at the same time, a successful method is to apply an external igniter to solid rocket motor.
为了提高固体发动机工作可靠性，增加装药质量，同时实现二级点火和级间分离，应用体外点火器是一种成功的方法。
High overload yields great influence on the grain combustion of SRM (solid rocket motor) in working process.
大过载会对固体火箭发动机装药燃烧产生很大的影响。
The effect of radial vibration of the chamber structure composed of propellant grain and case on the internal ballistic property of solid rocket motor (SRM) was investigated.
研究了由推进剂药柱和壳体组成的燃烧室结构径向振动对发动机内弹道性能的影响。
Structural integrity analysis and storage life prediction of grain is a critical problem for the designers, manufacturers and users of Solid Rocket Motor (SRM).
固体火箭发动机药柱结构完整性分析及贮存寿命预估是设计、生产和使用部门非常关注的关键问题。
Structural integrity analysis and storage life prediction of grain is a critical problem for the designers, manufacturers and users of Solid Rocket Motor (SRM).
固体火箭发动机药柱结构完整性分析及贮存寿命预估是设计、生产和使用部门非常关注的关键问题。
应用推荐