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.
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