同时也获得了一些对喷管设计极有用的结论。
At the same time, some valuable conclusion for the jet nozzle design have been obtained.
强调最小喷管长度转向采用锐边喉管道的喷管设计的极限值。
The emphasis on the minimum nozzle length was carried to the limit with the design of nozzle with sharpedged throats.
另外，本文还讨论了新型喷管设计理论、思路和工程化等相关问题。
Furthermore, some related topics about nozzles design and engineering also have been discussed.
优化结果表明，所建立的计算模型是正确的，并可用于其它大中型号的喷管设计。
The optimization results show that the models established are correct. The method can be used as a referece for others nozzle design.
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。
It's indicated that the design of the nozzle of the rocket assisted engine is to direction advantage in engineering by the experiment.
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。
The design of the nozzle of the rocket assisted engine with the base bleed compound extended range shrapnel is introduced in this paper.
本实验喷管设计点效率均超过99%，部分实验接近100%，高度补偿效果明显。
The maximum nozzle efficiency of all of plug nozzle tested here are more than 99%, some of them are nearly 100%. It has good altitude compensation.
基于特征线法，并考虑变比热的影响，开展了高超声速飞行器用单膨胀斜面喷管设计。
For hypersonic vehicles, the effect of nozzle aerodynamic characteristics on vehicles performance is serious.
本文提出了确定气动窗口所需自由旋涡气动特性的过程，讨论了特征线方法在非对称超音速喷管设计中的应用，该喷管被用来产生自由旋涡流动。
In this article the procedures are described for determining free vortex segment properties. Characteristics method is used to design nozzle which produces free vortex segment.
这些结果为HYTEN喷管的工程设计、优化和概念验证提供了基本的物理图像。
All these results have provided physical vision for engineering design, optimization and concept verification of HYTEN nozzle.
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；
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.
可为固体火箭发动机喷管的设计与研究提供有效参考。
Good references for solid rocket motor nozzle design and research are provided.
本文介绍一种设计固体火箭喷管的新方法。
A new method of the solid propellant rocket nozzle design is presented.
而高超声速风洞喷管的设计和计算则对解决这一类问题具有重要的科学意义和实用价值。
The design and computation of the hypersonic nozzle have scientific and practical value to solve these problems.
研究结果对于吸气式激光推力器的喷管构形设计具有指导意义。
The results are very useful to design nozzle structure of laser thruster that works in air-breathing mode.
本文的分析对延伸喷管锁紧机构的设计具有应用价值。
The depiction of this paper is available to the design of locking mechanism of extendible nozzle.
计算结果表明，该喷管出口锥与延伸锥结构是安全的，但考虑到材料性能的波动，安全余量较小，应从设计上保证产品的可靠性。
According to the computed result , the structure of NEEC is safe , but its safety margin is small, so the safety of the product should also be ensured through the design.
提出了一种尾喷管与进气道整流罩保形设计方案，既保持导弹外形特征不变，又与尾喷管内型面实现一体化保形设计。
A kind of conformal design scheme for tailpipe nozzle and inlet cowl was put forward, which not only keeps missile shape, but also realizes integral conformal design with inner contour of nozzle.
通过热和结构计算，对固体火箭发动机喷管缝隙设计进行了分析。
Gap design of solid rocket motor nozzle was analysized through thermal and structure analysis.
介绍了一种最新设计的轻质单级延伸喷管，它具有独特的可抛展开系统。
A new designed lightweight one stage extendible exit cone nozzle with the unique deployment system thrown out (EECDT) is presented.
介绍了固体火箭发动机喷管硬质泡沫塑料堵盖的设计方法与试验过程。
Design methods and test process of nozzle closure made of hard foamed plastics for SRM are introduced.
利用该法设计的一系列喷管，其M数分布满足用户需要。
This method is used to design a series of nozzles. Their Mach number profiles are satisfied for the users.
叙述了滚动球窝喷管在设计中许用接触应力的选择依据及方法，并根据以往的经验公式及其试验数据对影响许用接触应力的几个因素进行了分析。
Selection basis and method on allowable contact stress of rolling ball-socket nozzle were described. Based on empirical formula and test data, several factors affecting allowable stress were analyzed.
深入研究微喷管内流场性能有助于微推进系统的优化设计。
In-depth study on micro-nozzle flow field performance contributes to optimization design of micro-propulsion system.
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。
According to the entire design requirements and restraints of a certain solid propellant rocket motor, design method of nozzle contour is put forward.
结果表明，内喷管喉径是影响环簇式塞式喷管尺寸大小的最主要设计参数；
The results show that throat diameter of the inner nozzle is the most important design parameter influencing structure size of the annular clustered plug nozzle.
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.
试验和应用表明，微推偏喷管是存在的，新设计方法是可行的。
Experimental tests and applications on rockets show that the mini thrust misalignment nozzle exists and the new method of design is feasible.
试验和应用表明，微推偏喷管是存在的，新设计方法是可行的。
Experimental tests and applications on rockets show that the mini thrust misalignment nozzle exists and the new method of design is feasible.
应用推荐