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 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。
Using three dimensional linear viscoelasticity finite element model, numerical simulation was performed. The deformation of solid propellant grain under axial acceleration was investigated.
并运用三维线性粘弹性有限元模型，对离心实验过程进行了数值模拟，以确定固体推进剂药柱在轴向过载作用下的变形问题。
Using three dimensional linear viscoelasticity finite element model, numerical simulation was performed. The deformation of solid propellant grain under axial acceleration was investigated.
并运用三维线性粘弹性有限元模型，对离心实验过程进行了数值模拟，以确定固体推进剂药柱在轴向过载作用下的变形问题。
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