发射器和卫星推进喷嘴的设计

World Academy of Science, Engineering and Technology, International Journal of Mathematical, Computational, Physical, Electrical and Computer Engineering Pub Date : 2013-06-24 DOI:10.5139/ijass.2014.15.1.91

R. Haoui

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引用次数: 10

摘要

这项工作的目的是确定用于推进装置、发射器或搭载卫星的超音速喷嘴轮廓。这种设计的作用是:首先，提供重要的推进力，即出口气流均匀平行;其次，在不改变喷嘴内流量的情况下，找到短长度的轮廓。第一个详细的程序是利用轴对称流动的特征方法来确定发散型的轮廓。第二个方案是通过使用有限体积法来构思的，以确定和测试找到连接到收敛的剖面。

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Design of the propelling nozzles for the launchers and satellites

The aim of this work is to determine supersonic nozzle profiles that are used in propulsion, for launchers or embarked with satellites. This design has the role of firstly, providing important propulsion, i.e. with uniform and parallel flow at exit; and secondly, to find short length profiles, without modification of the flow in the nozzle. The first elaborate program is used to determine the profile of the divergent, by using the characteristics method for an axisymmetric flow. The second program is conceived by using the finite volume method, to determine and test the profile found connected to a convergent.

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来源期刊

World Academy of Science, Engineering and Technology, International Journal of Mathematical, Computational, Physical, Electrical and Computer Engineering

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