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在综合现有的强化混合技术基础上，提出了一种新的喷嘴模型——低角度分级喷嘴模型，并设计了缩尺寸燃烧室。通过燃烧室入口马赫数为２的氢燃烧超音速燃烧实验，获得了超音速燃烧室中壁压沿轴向的变化规律，证明了低角度分级喷嘴模型燃烧室比目前公认的后掠斜坡喷嘴模型燃烧室有更高的燃烧效率。分析认为可通过优化燃烧室设计来降低低角度分级喷嘴模型燃烧室的总压损失。并且，由１维计算还可知道，对超音速燃烧室，随着当量比φ（φ≤１）的增加，燃烧效率减小，总压损失增加，燃烧室出口马赫数减小。
On the basis of synthesizing the existing hybrid technology, a new nozzle model - a low-angle grading nozzle model was proposed and a compact combustion chamber was designed. The variation of wall pressure in the supersonic combustion chamber along the axial direction was obtained through the hydrogen combustion supersonic combustion experiment with the Mach number of 2 at the inlet of the combustion chamber. It was proved that the combustion chamber of the low-angle graded nozzle model was better than the currently recognized sweep model The combustion chamber has a higher combustion efficiency. It is considered that the total pressure loss in the combustion chamber of the low-angle staged nozzle model can be reduced by optimizing the combustion chamber design. In addition, the 1-D calculation shows that with the supersonic combustion chamber, as the equivalent ratio φ (φ ≦ 1) increases, the combustion efficiency decreases, the total pressure loss increases, and the Mach number of the combustion chamber decreases.