这架飞机是双发动机设计的。
固体火箭发动机设计是一项复杂的系统工程。
Solid rocket motor design is a complicated systems engineering.
为发动机设计者以及相关研究人员提供参考。
Offered reference to engine designer and correlative researcher.
为某微型涡喷发动机设计了一个蒸发管环形燃烧室。
An annular combustor with evaporation tubes was designed for certain micro-turbojet engine.
有关结论可以为高速旋转条件下发动机设计提供参考。
These conclusions can present some references to the rocket design.
膏体推进剂的点火和燃烧特性是发动机设计的重要参数。
The ignition and combustion characteristics of pasty propellant are important parameters for the motor design.
粗看之下，更有效的机翼与发动机设计保证了公司有效的实现他们的目标。
But at a glance, the efficient wing design and engines appear to be holding up their end of the deal.
此项设计技术对带反向喷管的固体火箭发动机设计具有参考作用。
This technique is available for the design of SRM with reverse nozzle.
这一成果可供航空发动机设计人员和工艺人员在新机研制和生产中借鉴。
The results can be used by engine designer and technician as reference in their new engine development and production.
强调了发掘老专家的智慧是提高《航空发动机设计手册》撰写质量的关键。
Finally, it has been stressed that the wisdom of experienced experts is a key factor to improve the quality of Aeroengine Design Manual.
设计高性能喷注器、提高发动机比冲性能是发动机设计者一直追求的目标。
To design a high performance injector and to improve engine impulse performance are the permanent goals of engine designers.
本文还完成了SFRJ实验发动机设计，提出了实验方案与数据处理方法。
An experimental SFRJ system is designed and scheme of experimental is provided.
作者针对发动机设计过程提出一种简单、灵活的设计规划工具——设计关联矩阵。
A simple, flexible process-planning mechanism for engine design, the design Relationship Matrix, is used to achieve it.
应用面向对象技术对单一知识进行封装，实现了面向对象的固体发动机设计案例表示。
Encapsulation of single knowledge representations are finished by Object-Oriented, and the case of SRM design is established.
结果表明：模拟实验技术可行，实验方法正确，模拟实验结果为发动机设计提供了依据。
The test results show that the technology and method of simulation test are correct and available. And the results of simulation test have served in the engine design.
涡轮导向器喉道面积值是燃气涡轮发动机设计和生产中的重要参数，必须加以严格的控制。
The throat area of turbine nozzle which is very important in gas turbine engine's design and manufacture must be controlled strictly.
以某大型固体火箭发动机设计为例，说明其在固体火箭发动机优化设计和参数敏感性分析中的应用。
Taking design of a large-size SRM for example, the application of this method in design optimization and parameter sensibility analysis was introduced.
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.
发动机曲轴是发动机中最重要的部件之一，它承受复杂、交变的冲击载荷，是发动机设计的重点和难点。
The crankshaft is one of the most important components of engine, it endures complex and alternate load and it is the key point and difficulty of the engine design.
随着发动机设计要求的不断提高，应用有限元方法在其主要零部件设计上，能够符合复杂结构的设计要求。
With the constant improvement of engine design demands, the finite element method may be used in the design of major parts of engine and can meet the design needs of complex structures.
依据膏体推进剂火箭发动机设计和膏体推进剂管道流动实验需求，提出了一种新型膏体推进剂供给系统方案。
According to the requirement of the pasty propellant rocket engine design and pasty propellant pipe flow experiment, a new type of pasty propellant supply system is proposed.
在发动机设计阶段和发动机实际使用中，可以应用这个公式，估计运动件质量变化所引起的比油耗的相对变化。
Thisformula can be used to evaluate the relative changes of engine specific fuel consumption caused by the relative changes of engine moving parts mass during engine design and practical operation.
为车辆设计人员和发动机设计人员分析发动机曲轴断裂问题和车辆设计过程中发动机匹配问题提供了参考数据。
It provided reference data to analyse the problems of engine crankshaft cracking and to solve the problems of engine matching in vehicle designing.
据《东方早报》报道，上海日前公布2009年毕业生工资价位报告，发动机设计人员月薪最高，为9549元；
Graduates working in engine design enjoyed the highest starting salaries up to RMB9549 a month in Shanghai, Oriental Morning Post reported.
贫氧推进剂燃速是固体火箭冲压发动机设计和性能分析的重要参数，也是对推进剂配方进行检验验收的主要指标。
The burning rate of the fuel-rich propellants is the parameter which is important for Ducted Rocket design and performance analysis and is main inspection criterions of propellant prescriptions.
根据航空发动机设计的实际需要，在大尺寸低速叶栅传热风洞中对涡轮叶片表面的气膜冷却进行了综合性实验研究。
Film cooling of the surface of a gas turbine blade was studied in a large-scale low-speed opening wind tunnel according to actual requirement of the design of aero-engine.
最后，论文还研究了某型压气机的过失速状态，确定了由发动机设计参数判断失稳后是发生喘振还是旋转失速的方法。
Post-stall behavior is simulated in the paper to estimate whether surge or rotating stall initiate with engine design parameters.
文中提供的计算方法具有较高预示精度，可推广到其它药四旋转发动机的内弹道计算，对旋转发动机设计具有指导作用。
The method has high accuracy being used to calculate internal ballistic performance of other grain configuration motor and plays a important role in spinning motor design.
文中提供的计算方法具有较高预示精度，可推广到其它药四旋转发动机的内弹道计算，对旋转发动机设计具有指导作用。
The method has high accuracy being used to calculate internal ballistic performance of other grain configuration motor and plays a important role in spinning motor design.
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