最终分析出发动机壳体的振动噪声特性。
Finally, acquaints the vibration and noise characteristic of the engine shell.
介绍某固体发动机壳体外防热涂层的研究情况。
This paper deals with the study of the external thermal insulation coating for a solid rocket motor (SRM) case.
这对提高火箭发动机壳体力学性能有很大的作用。
It can be very useful to promote the physical performance of rocket-engine-rind.
作为一个例子，计算了一个固体火箭发动机壳体的强度。
As an example, the strength of a solid fuel rocket engine shell is calculated.
推进剂的浇铸是通过从浇铸锅到发动机壳体的“插管”来进行的。
Casting the propellant is done through the "bayonets" from the casting pot to the case.
研究了基于遗传算法的固体发动机壳体工艺流程面向成本优化问题。
GA to resolve process route optimization of solid rocket motor shell is studied.
介绍了固体火箭发动机壳体裙的结构、用途及采用复合材料裙体的优点。
Both the structure and the use of solid rocket motor case skirts are presented. The advantages of the composite skirts are introduced.
发动机壳体为一个其一端为密封的钢铸圆柱缸体，另一端则为敞口的喉道及喷管。
The motor case is a steel cylinder closed tight at one end. the other end is the open throat and nozzle.
研究缠绕复合材料发动机壳体在内压载荷作用下，承受强度约束的优化设计方法。
Design optimization algorithm of winding composite motor cases under inner pressure and endure strength restrain is studied.
本文采用大变形有限元方法进行纤维缠绕固体火箭发动机壳体的应力及爆破分析。
In this paper we employed the nonlinear finite element method to calculate the stress and bursting pressure of filament wound rocket motor case.
用于固体火箭发动机壳体和工业贮罐的纤维缠绕压力容器，爆破压强是重要的设计参数。
The burst pressure of filament wound pressure vessels which is applied to solid rocket motor case and gas tank in industry is an important design parameter.
认为：用激光拦截助推段弹道导弹时，其液体贮箱壳体和固体燃料发动机壳体是最易损的，生存能力很低；
It is realized: when ballistic missile in boost phase is intercepted with CW Laser, its liquid storage and solid rocket engine shells are the brittlest, the survivability is very low;
VARTM工艺成型的固体火箭发动机壳体复合材料连接裙段构件纤维体积含量较低，复合材料力学性能不佳。
The composite skirts for solid rocket motor shells fabricated by VARTM (VacuumAssisted Resin Transfer Molding) had poor mechanical properties because the fiber volume fraction was very small.
VARTM工艺成型的固体火箭发动机壳体复合材料连接裙段构件纤维体积含量较低，复合材料力学性能不佳。
The composite skirts for solid rocket motor shells fabricated by VARTM (VacuumAssisted Resin Transfer Molding) had poor mechanical properties because the fiber volume fraction was very small.
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