燃烧室壳体

大直径薄壁燃烧室壳体热处理变形研究

Research on Heat Treatment Deformation of Big Diameter Thin Wall Combustion Chamber Case

介绍一种固体火箭发动机燃烧室壳体纤维缠绕芯模的设计。

Dynamic modeling and model reduction order of controllable flow solid ducted rockets ;

边界元解析敏度分析在燃烧室壳体构件优化设计中的应用

The Use of Boundary-element Analytic Sensibility Analysis in the Optimized Design of Combustor-casing Structural Members

固体火箭发动机燃烧室壳体纤维缠绕模具设计

The Design of the Fibre Winding Mold of the Solid Rocket Motor Combustion Chamber Shells

在优化燃烧室壳体构件时，用加权求和法处理该构件的多目标问题，最后获得满意的结果。

In optimizing combustorcasing structural members a multi-objective problem was tackled by using a weighted summation method , and satisfactory results were finally achieved .

根据内绝热层的烧蚀机理，推导出内绝热层炭优厚度计算公式；根据燃烧室壳体对热防护的要求，给出了确定内绝热层设计厚度的方法。

The formulas to compute the charred thickness are derived based on its ablation mechanism and the methods to determine its design thickness arc given based on thermal protection for the chamber case .

很多零件不但具有薄壁结构，而且薄壁结构带有倾斜特征，燃烧室壳体就是其中的典型零件，使用传统方法加工费时费料、容易变形。

Many parts not only have thin-walled structures but also with the characteristic of inclination . Typically , the shell of combustion chamber is one of those parts . The combustion chamber shell which manufactured with traditional methods is time-consuming , material-wasting and easily deformed .

燃烧室壳体椭圆度及母线直线度主要受吊装方式、壳体焊接质量、油冷时壳体入油速度等工艺方法影响，采取专用工装，可以校正燃烧室壳体椭圆度及母线直线度。

The ovality and generatrix straightness of combustion chamber case are mainly affected by the technological methods such as lifting way , wilding quality and quenching speed during oil cooling . Special toolings can be used to correct the ovality and generatrix straightness of chamber case .

端面燃烧发动机燃烧室壳体的新型热防护方法

A new thermal protection method for motor chamber with end burning grain

固体火箭发动机是航天工程中重要的动力装备，粘贴在燃烧室（即发动机壳体）内壁的绝热层，对燃烧室壳体起到隔热、防止燃烧产物冲刷等作用。

Solid rocket motor is the most important space power equipment . The insulation pasted in the combustion chamber ( namely , the engine shell ) inner-wall plays an important role in thermal insulation and avoiding washing to shell by combustion products .

燃烧室壳壁沿平行其轴线方向的破裂以及燃烧室与点火器壳体螺纹连接处退刀槽根部的开裂是推力器结构强度的主要破坏形式。

And the major broken behaviors which parallel to the axis of the combustion chamber may appear at the roots of the technological grooves near the screw connetion between its chamber and igniter or and nozzle .