为了提高RBCC引射火箭模态的推力性能，探索热力壅塞对引射模态推力的影响，开展了二次燃烧实验研究。
Secondary combustion was experimentally investigated to improve thrust of rocket ejector mode of RBCC, and to find the influence of thermal choke on thrust.
以固体火箭发动机作为燃气发生器，成功的进行了静态海平面零马赫状态下引射模态实验，获得了相关实验数据。
Using solid rocket as gas generator, the sea level static ejector modal experiment was conducted successfully, and relevant data was obtained.
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。
The progress in subsonic and supersonic combustions has been attained, but the ejecting mode and mode match of RBCC has just been begun.
在国内RBCC研究中首次从理论上获得了具有较高推力增强的RBCC引射模态方案，对开展RBCC引射模态研究有重要意义。
It is in the first time in domestic RBCC researches that the RBCC configuration with relatively higher thrust augmentation in ejecting mode is obtained.
然而，用回传波射矩阵法对结构进行模态分析以及用于层合复合材料框架结构动力响应的研究尚未见报道。
However, the studies on vibration modal analysis of frames by means of the MRRM and transient dynamic response of frames made of laminated composite beams have not been reported yet.
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。
In ejector and ramjet modes, working over a wide Mach number range is very important for the RBCC inlet, so the 2d 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。
In ejector and ramjet modes, working over a wide Mach number range is very important for the RBCC inlet, so the 2d RBCC inlet should be variable-geometry.
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