火箭研究

As the centre of liquid-rocket-engine, the importance of the liquid hydrogen turbopump is significant. Turbopump rotordynamic instability problems concern many influencing factors, and there is great difficulty in solving them.

作为液体火箭发动机的心脏，液氢涡轮泵的重要性不言而喻，其中涡轮泵转子系统的动力稳定性问题中涉及的影响因素很多，其分析研究的难度也极大。

In order to improve the reliability, real-time capability and validity of turbopump fault detection system for a large liquid rocket engine, its hardware construction and layout, multi data acquiring cards synchronization, and algorithms integration were studied.

为了提高某大型液体火箭发动机涡轮泵故障检测系统的可靠性、实时性和有效性，研究了该系统硬件的构建与布局、多块数据采集卡的同步、以及算法的集成与综合等问题。

The crude rockets, says Anat Kurz, of the Institute of National Security Studies, are more "a statement of 'we are here' in the internal Palestinian power struggle between competing militias than serious 'resistance' to Israel".

以色列国家安全研究中心的阿那特。克兹指出现在巴勒斯坦对立的武装派别正处在激烈的内部权力争斗中，他们使用这种原始简陋的火箭与其说是真的要'反击'以色列，倒不如说是他们用来表明'我们在这里'。

NBR was used as basic material, bakelite /asbestine were used as reinforcer and alone used and used together, the ablation rate and the mechanical properties were tested in studing ablation material for solid rocket motor.

在固体火箭发动机用烧蚀材料研究中，以丁腈橡胶为基体材料，采用酚醛和石棉作为增强剂，进行单独和混合使用，测试了烧蚀率和机械性能。

An experimental unchoked ducted rocket motor system is designed in this paper, and some experiments are finished.

本文还完成了实验小型非壅塞固体火箭冲压发动机设计，并进行了实验研究。

The development of controllable flowsolid ducted rocket promote the study on control system of solid ducted rocket.

燃气流量可控的固体火箭冲压发动机促进了其燃气流量控制系统的研究。

The altitude characteristics, velocity characteristics and throttling characteristics of solid ducted rocket were theoretically studied.

系统地研究了固体火箭冲压发动机的高度特性、速度特性和节流特性。

With connected-pipe test facility, the combustion characteristics of the unchoked ducted rocket were investigated.

采用直连式实验装置系统地研究了非壅塞固体火箭冲压发动机的燃烧特性。

It was found that the aggregation method is suitable to treat solid fuel SQ in solid-liquid hydrid rocket.

研究发现固液混合火箭固体燃料SQ合适的处理方法为团聚法。

In this paper ,move ment pri nci ple of rocket i n direction pi pe was got by dy— namic si mulation ,and effect characteristic consideri ng contact stiffness ,detent force and nozzle thrust misalignment a— bout pitchi ng angle velocity was analysis .All the study set foundationfor further study of high—lowpressure launch sys— te m.

通 过发射仿真分析，获得了火箭弹在高低压发射系统中的内弹道变化规律，分析了火箭弹与定向器的接触刚度、耳轴扭转刚度、尾喷管推力偏心等因素对俯仰角速度的影响特性，所得结论为火箭武器高低压发射系统的进一步相关研究奠定了基础。

The split between the two groups can hardly be papered over.

这两个团体间的分歧难以掩饰。

This approach not only encourages a greater number of responses, but minimizes the likelihood of stale groupthink.

这种做法不仅鼓励了更多的反应，而且减少跟风的可能性。