The rocket is long and slender, and fatter on top because its second stage is thicker than its solid rocket motor-powered first stage.
火箭又长又细，上部有点粗，因为它的第二级比固体燃料火箭发动机驱动的第一级要厚。
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。
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 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。
It improved the measuring precision of the thickness of rocket motor cladding.
提高了火箭发动机包覆层厚度测量精度。
Good references for solid rocket motor nozzle design and research are provided.
可为固体火箭发动机喷管的设计与研究提供有效参考。
Phenolic resins have been applied in rocket motor to offer high properties and low cost.
酚醛树脂以其价格低廉、耐热性能优异，在火箭发动机上得到广泛应用。
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。
Study of suppression after-burning with some additive on rocket motor exhaust is introduced.
介绍了几种添加剂抑制火箭发动机喷焰二次燃烧的实验研究。
The upcoming test campaign will validate the system's rocket motor and thrust vector control.
即将到来的测试活动将验证系统的火箭马达和推力矢量控制。
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。
Ablation prediction of solid rocket motor nozzle is an important link for nozzle structure analysis.
固体火箭发动机喷管的烧蚀预示是喷管结构分析的重要一环。
The steady process of solid rocket motor modulated by the vortex valve is investigated theoretically.
对涡流阀调节固体火箭发动机压强的稳态过程进行了理论研究。
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；
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。
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。
The plume from the attitude controlling rocket motor nozzle has an obvious effect on the aircraft in vacuum.
姿态控制发动机真空环境下工作产生的羽流对航天器造成的影响非常明显。
There is a rocket motor on the satellite by which the direction of the satellite can be changed if necessary.
在卫星上还有一个火箭马达，必要时可以用它来改变卫星的方向。
The influence of structure axial vibration on the internal ballistics of solid rocket motor was investigated.
文中研究了固体发动机结构的轴向振动对燃烧室内弹道性能的影响。
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。
The safety demolding system is designed for main core demoulding from the NEPE high-energy rocket motor in safety.
安全脱模系统是为了解决NEPE推进剂装药发动机主芯棒脱模而研制的专用设备系统。
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。
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。
On the assumption of "Y", a three-dimensional model is obtained for the linear acoustic combustion in a rocket motor.
通过提出一个“Y假设”，本文求得了一个固体火箭发动机线性声振荡燃烧的三维理论模型。
The green destruction and reclamation technology of obsolete rocket motor charge in America and Russia is summarized.
综述美国和俄罗斯废弃火箭发动机装药绿色销毁与回收技术。
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。
Two phase flow in the solid rocket motor combustion chamber under overload condition is studied with numerical method.
对过载状态下固体火箭发动机燃烧室内二相流动进行了数值研究。
Rocket motor test shows that the new UDMH/NTO bipropellant can satisfy the requirement of gel propellant of rocket motor design.
发动机试验表明：新的UDMH/NTO双组元凝胶体系能够满足发动机设计对凝胶推进剂的要求。
Rocket motor test shows that the new UDMH/NTO bipropellant can satisfy the requirement of gel propellant of rocket motor design.
发动机试验表明：新的UDMH/NTO双组元凝胶体系能够满足发动机设计对凝胶推进剂的要求。
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