scramjet engine

Review of scramjet engine development

超燃冲压发动机研究综述

Primary calculating model for integrated scramjet engine design

一体化超燃冲压发动机初步设计计算模型

Optimum Design of Scramjet Engine

超音速燃烧冲压发动机最佳设计参数

This study deals with the effect of vitiated air contamination on combustion and scramjet engine ground tests .

本研究关系到污染对燃烧的影响以及对于超音速燃烧冲压发动机地面试验的影响。

A scramjet engine goes as fast as a rocket , but it doesn , t have to carry its own oxygen supply .

超音速燃烧冲压式喷气发动机能使飞行像火箭一样快，但它不必自携氧气。

The research coinstantaneous shows that the boundary transition should be considered , and effective transition method should be adopted to ensure the normal work of the scramjet engine .

同时说明，在超燃进气道设计过程中，需要充分考虑边界层转捩问题，引入有效的边界层转捩控制方法，以保证发动机的正常工作。

Based on these efforts , primary calculating models for integrated scramjet engine inlet , separating section , combustion chamber and nozzle were built , and the primarily calculations were conducted .

在此基础上建立了一体化超燃冲压发动机进气道、隔离段、燃烧室及尾喷管计算模型，并对一体化设计的超燃冲压发动机模型进行了初步计算。

The scramjet engine uses the method of regenerated active thermal protection during its working . The temperature of the fuel can reach 400 ~ 600 ℃ before it flows into the combustion chamber .

超燃冲压发动机工作时采用的是再生主动热防护，燃料在进入燃烧室之前，燃油温度能够达到400～600℃。

An effort to multidisciplinary design optimization ( MDO ) of a hypersonic cruise vehicle propelled by scramjet engine based on design of experiment ( DOE ) and response surface approximation methods is presented .

建立了基于试验设计理论和响应面近似的超燃冲压发动机推进的高超声速巡航飞行器多学科设计优化方法。

In this paper a dual-mode Scramjet model engine was experimentally investigated with hydrogen fuel burning .

笔者研究了一个有突扩台阶的氢燃料高超声速冲压发动机模型的气体动力学特性和推力特性。

A dual-mode scramjet model engine with a rear-faced step is experimentally investigated with different hydrogen fuel injection manners .

在一个有突扩台阶的氢燃料高超声速冲压发动机模型内研究了氢燃料喷注方式对点火与燃烧效果的影响。

Scramjet combustor design optimization for a test scramjet model engine is conducted by employing genetic algorithms , and an optimal design much better than original design is obtained .

采用遗传算法对某试验超燃冲压模型发动机的燃烧室构型参数进行了优化设计，所得方案的性能大大优于实际方案。