The propellant grain structural parametric analysis is realized in primary level.
初步实现了装药结构的参数化分析。
The combustion characteristics of silver wire embeded fuel rich propellant grain are investigated.
系统研究了铝镁贫氧推进剂低压燃烧特性的表征方法。
The models of the spinning induced effects upon propellant grain stress and deformation, thermodynamics and gas dynamics were set up.
给出了旋转对推进剂应力应变的影响、产生的热力学方面的影响及旋转引起的气体动力学的影响等的分析计算模型。
The paper presents a novel technique to measure the stress strain response at the exposed surface of propellant grain using a miniature-testing device.
本文提出一种利用小型实验装置测量推进器药柱表面应力应变响应的技术。
During the molding and storing process, humidity is the foremost factor affecting the characteristics of HTPB propellant grain and adhesion strength between interfaces.
在成型及贮存过程中，湿度是影响丁羟推进剂药柱性能及各界面的联合粘接强度的首要因素。
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。
The results show that primary action of bonding agent improving RDX/HTPB propellant mechanical property was bonding agent improving interface adhesive effect of RDX grain to HTPB binder.
结果表明，键合剂改善RDX／HTPB推进剂力学性能的主要原因在于它们改善了RDX颗粒与HTPB粘结剂基体间的界面粘结效能。
Theoretical analysis emphasizes on heat transfer both inside propellant and between igniter exhaust and internal grain surface.
理论分析着重研究了点火燃气与推进剂表面传热及推进剂内瞬态热传导规律。
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 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。
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