rbcc

Research status about rocket based combined cycle ( RBCC ) propulsion system

火箭基组合循环（RBCC）推进系统研究现状

The results show that the software is applicable to RBCC motor performance analysis .

结果表明，该软件适用于RBCC发动机性能分析。

Present situation and progress of investigation on rocket based combined cycle ( RBCC ) propulsion system

RBCC组合循环推进系统研究现状和进展

As for the research of the performance of the motor , the directed RBCC is adopted mostly .

对于发动机性能的研究，国内外大多采用直连式RBCC实验系统进行研究。

This paper aims designs the ground test system of direct-connect RBCC , and disposes of the experimental data .

本文就是针对这一有效的方法，进行了直连式RBCC发动机地面实验，对实验数据进行了处理。

The investigation lays a fine foundation for realizing stable high efficient combustion based on the thermal throat RBCC ramjet mode .

研究工作为实现基于热力喉道的RBCC亚燃模态稳定高效燃烧提供了良好的基础。

RBCC engine performance analysis model plays an important part in scheme selection and model design for Hypersonic Flight Vehicle , RBCC engine design and performance analysis .

RBCC发动机性能分析模型在高超声速飞行器方案选择、总体设计以及RBCC发动机设计与性能分析等方面具有极其重要的作用。

The present situation and progress of investigation on rocket based combined cycle ( RBCC ) propulsion system was introduced both at home and abroad in details .

对火箭基组合循环（RBCC）推进系统的国内外研究现状和进展进行了详细综述。

For it 's excellent performance , Rocket-Based-Combined-Cycle ( RBCC ) should be the most competitive propulsion system of Hypersonic Flight Vehicle for martial and civil purpose .

火箭基组合循环（Rocket-Based-Combined-Cycle，RBCC）发动机具有优越的全弹道性能，是实现高超声速飞行的最有潜力的动力方案，具有广泛的军事和民用航天应用前景。

The progress in subsonic and supersonic combustions has been attained , but the ejecting mode and mode match of RBCC has just been begun .

国内已制定了研究计划并正在开展，其中亚燃和超燃模态的研究取得了相当的进展，但引射模态以及模态匹配的研究还刚刚起步。

Finally dynamic technology of soaring hypersonic cruise vehicle was preliminarily investigated . The fuel consumption of rocket based combined cycle ( RBCC ) for the soaring hypersonic cruise vehicle was analyzed .

对滑跃式高超音速巡航飞行器的动力技术进行了初步研究，分析了采用火箭基组合循环发动机（RBCC）方案所需的燃料消耗。

Applying 3-D turbulent finite volume numerical algorithm validated , different operation status of Rocket Based Combined Cycle ( RBCC ) model with different structures and working conditions of primary rocket were simulated in ejector mode .

应用经过校验的三维湍流有限体积数值算法，对引射模态下RBCC模型不同一次引射火箭结构和工作参数条件下的多种工作状态进行了模拟。

In ejector and ramjet modes , working over a wide Mach number range is very important for the RBCC inlet , so the2D RBCC inlet should be variable-geometry .

对工作于引射和亚燃模态的RBCC发动机进气道来说，宽马赫数工作的要求显得尤为突出，使得二元进气道应采用变几何结构。