These conclusions can present some references to the rocket design.
有关结论可以为高速旋转条件下发动机设计提供参考。
In pursuing specifications set out for the system, the designers had adopted a series of rocket design features.
为推行规范测定用于系统，设计者已经采用一系列的火箭设计特点。
As part of this exploration plan, 2015 is now the deadline for finalizing a heavy-lift rocket design, and there will be renewed focus on advanced propulsion systems and other technologies.
探索计划要求重载火箭的研制需要在2015年之前完成，到时还将会重新集中研发推进系统及其他科技项目。
This paper, combining with rocket design, studies the application of 3-time optimum method with constraints to rocket design. Optimal direction and synthetic assessment methods are presented.
本文结合具体的火箭弹设计，讨论了带有约束条件的三次优化方法在火箭弹设计中的应用，提出了最佳方向和综合评定法两种优化方法。
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.
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。
Of course, this dilemma arises in many human endeavors, from building design, to rocket science, to patent law.
当然，这种界定在人类的许多方面都开始出现，从构建设计到火箭科学，到专利权法。
The new space vehicle design USES shuttle rocket parts, an Apollo-style capsule and a lander capable of carrying four people to the moon.
新一代航天工具的设计采用了运载火箭部件、和“阿波罗”号类似的太空舱和一个能够搭载四名探月宇航员的登陆舱。
The Augustine panel questioned the cost, design and construction schedule of the rocket in a report submitted to the White House for consideration.
奥古斯汀专项研究小组质疑提交给白宫考虑的报告中的成本、设计以及建设计划。
Engineers hope the can-crushing tests will prove the strength of thin materials, enabling rocket builders to design lightweight materials for future heavy-lift launch vehicles.
工程师们希望这次“压罐子”实验将验证这些轻巧材料的受力性能，从而使以后的火箭制造者们在未来更大起飞重量的航天器中可以尽可能的设计采用轻量化的材料。
One solution is the "rocket stove", a simple design that diverts the smoke outside.
一个办法是“rocketstove”，一种将烟排到室外的简单设计。
As a rocket scientist, I do analysis of mission-design impacts of future technology advancements.
作为一名火箭科学家，我会分析任务设计对未来科技进步的影响。
The initial Shuttle design predicted neither foam debris problems nor poor sealing action of the Solid Rocket Booster joints.
航天飞机的初始设计即没有预料到泡沫脱落问题也没有预料到固体火箭助推器连接密封性能这么差。
The results will be useful to the design of Base-Bleed and Rocket Compound Extended Range Projectiles.
结果将有助于某型号底排-火箭复合增程弹的设计分析。
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.
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。
The design and realization of a variable thrust liquid rocket engine control system is present in this paper.
本文讨论了某型变推力液体火箭发动机数字控制系统的设计和实现。
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。
A new method of the solid propellant rocket nozzle design is presented.
本文介绍一种设计固体火箭喷管的新方法。
The hydrodynamic design of advanced liquid rocket engine high performance inducers is a challenging technology.
先进液体火箭发动机高性能螺旋轮的流体动力设计是个关键技术。
An integrated conceptual design software system for solid rocket motors SRMCAD is developed.
研制了一种固体火箭发动机集成方案设计系统软件SRMCAD。
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。
The tentative design of constant altitude flight solid rocket composed of the sustainer the booster and its simple control method is presented.
介绍了主发动机加助推器和简易控制方法实现固体火箭等高飞行的设计方案。
The tentative design of constant altitude flight solid rocket composed of the sustainer, the booster and its simple control method is presented.
介绍了主发动机加助推器和简易控制方法实现固体火箭等高飞行的设计方案。
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.
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 design of the nozzle of the rocket assisted engine with the base bleed compound extended range shrapnel is introduced in this paper.
经射击试验证明文中所述对增程弹火箭助推发动机喷管设计具有一定的指导意义。
Taking system optimization design of SRM as the example, physical programming of was proven to be efficient in modelling of decision-making uncertainty during the solid rocket motor design.
以固体火箭发动机总体方案优化设计为例，证明了物理规划方法作为固体火箭发动机设计决策不确定性建模方法的有效性。
Design optimization of solid rocket booster was carried out by using traditional and multi-disciplinary design optimization (MDO) method.
采用传统设计优化方法和多学科设计优化(MDO)方法进行了固体火箭助推器设计优化。
An calculating method for design parameter optimization of the propulsion system of the sounding rocket is given.
提出了探空火箭动力系统设计参数优化计算方法。
MDO method can improve design quality for solid rocket booster, and greatly reduce iterative times and shorten design period.
采用MDO方法，可提高固体火箭助推器的设计质量，大大减少设计迭代次数，从而缩短设计周期。
The characteristics of the dynamic process of starting and accelerating were mastered by the rocket sled test and some design mistakes were exposed also.
通过火箭橇试验，可掌握导弹发射条件下弹用涡轮喷气发动机启动加速特征，暴露发动机在启动加速方面的设计缺陷。
The characteristics of the dynamic process of starting and accelerating were mastered by the rocket sled test and some design mistakes were exposed also.
通过火箭橇试验，可掌握导弹发射条件下弹用涡轮喷气发动机启动加速特征，暴露发动机在启动加速方面的设计缺陷。
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