The requirements for the internal insulation arc presented based on its functions in a solid rocket motor.
根据内绝热层在固体火箭发动机中的作用，对其提出了若干要求；
Finite element method is used in the study of nozzle damping of instable combustion in a solid rocket motor.
应用有限单元法研究固体火箭发动机不稳定燃烧中的喷管阻尼，并用波衰减对比法进行了试验研究。
This paper deals with the study of the external thermal insulation coating for a solid rocket motor (SRM) case.
介绍某固体发动机壳体外防热涂层的研究情况。
Its ignition transient process plays an important role in determining whether a solid rocket motor can work normally.
星形是固体火箭发动机常用的装药形式，而其点火瞬时过程对发动机能否正常工作起着极为重要的作用。
Then, the experiment of flow separation in the nozzle was done with a solid rocket motor, and the inside pressure data along the axis of the nozzle was gotten.
然后，利用某型号固体火箭发动机进行喷管分离流试验，测得了喷管壁面上沿轴向的压强分布数据。
Finite element method is used in the study of nozzle damping of instable combustion in a solid rocket motor. Wave decline method is used in the experimental research.
应用有限单元法研究固体火箭发动机不稳定燃烧中的喷管阻尼，并用波衰减对比法进行了试验研究。
NASA's Space Shuttle Program conducted the final test firing of a reusable solid rocket motor Feb. 25 in Promontory, Utah.
2月25日，美国航天局航天飞机组在犹他州海角对可回收的液态火箭引擎进行了最后的测试。
The liner is a polymeric elastomer coating between propellant and insulation layer or case. The liner-forming is a special step in production of solid rocket motor.
衬层是推进剂与绝热层或壳体之间的高分子弹性体涂层，衬层成型是固体火箭发动机生产中的一种特种工序。
A new type of dual-pulse solid rocket motor concept with an intermediate nozzle is presented and a test motor with changeable structural parameters was designed.
提出了一种带有中间喷管的新型双脉冲固体火箭发动机技术方案，设计了一台结构参数可调的试验发动机；
This article introduces a designing means of mold of the fibre winding solid rocket motor combustion chamber shell.
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。
Solid rocket motor design is a complicated systems engineering.
固体火箭发动机设计是一项复杂的系统工程。
A method of internal ballistic calculation for spinning solid rocket motor has been presented in this paper.
提出了一种旋转固体火箭发动机的内弹道计算方法。
A conception of adjustable solid propellant rocket motor was proposed.
本文提出了一种推力可调的固体火箭发动机的设想方案。
The ignition of the solid rocket motor (SRM) is a very complex physical and chemistry process, which is composed of three component phases: ignition delay, flame spreading and chamber filling.
固体火箭发动机的点火是一个十分复杂的物理化学过程，包括三个阶段：点火延迟、火焰传播和燃烧室气体充填。
A software system for solid rocket motor test data analysis and management is introduced.
介绍了一种固体火箭发动机试验数据分析处理及管理系统。
A practical method for predicating the pressure curve at the starting transient of solid rocket motor is presented.
介绍了一种预示固体发动机火箭压强曲线上升段的实用方法。
The ignition delay fault of solid rocket motor happening in a low temperature based on FTA is analyzed in the paper.
介绍了基于故障树分析法(FTA)进行的某固体火箭发动机低温下点火延迟故障的分析过程。
The nozzleless solid rocket motor is a new type of motor which differs from the traditional motor, refers to many subjects and has a very complex system process.
无喷管固体火箭发动机是一种区别于传统发动机的新型火箭发动机，它涉及到的基础知识面广，系统工作过程复杂。
According to the entire design requirements and restraints of a certain solid propellant rocket motor, design method of nozzle contour is put forward.
根据某型号固体火箭发动机总体设计要求及限制条件，给出了喷管型面设计方法。
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。
Based on a nozzle structure in solid rocket motor, a calculation model is developed. The vibration and mode analysis of the model using subspace iteration method are presented in the paper.
针对某固体发动机喷管结构，建立计算模型，给出了用大型特征值问题求解的子空间迭代法。
In this paper, a simple method for analysis of ground test data of the solid rocket motor with reversal nozzles is presented based on solving the reverse thrust at an altitude from ground test data.
文中介绍了根据地面实验数据分析反喷管在高空提供的反推力，为带反喷管发动机地面实验数据处理提供了简便的分析方法。
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。
And a more satisfied result is obtained by analysing the living example of the structure reliability for some solid rocket motor at the test sample stage.
通过对某型号发动机试样阶段结构可靠性实例分析，得出了较满意的结果。
The estimation of extend-range solid rocket motor in high speed rotation is a key technique.
高速旋转试验台是模拟底排一火箭复合增程炮弹内的固体火箭发动机实验设计的。
Furthermore, it builds a thrust model of the solid rocket motor, and presents the whole six-degree-of-freedom kinetic equations and motion equations.
并建立了固体发动机推力模型，以及完整的六自由度弹道动力学和运动学模型。
With a diameter of three meters, the solid-fuel rocket motor ran for 100 seconds after ignition.
中国已在西北部城市西安完成最大的固体燃料火箭发动机点火测试。
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。
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