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本文设计了由等截面段、扩张段和等截面段构成的超音速燃烧室，并进行了燃烧实验。用一维计算分析实验结果，表明由等截面段、扩张段和等截面段构成的超音速燃烧室，通过一定的喷油方式，能按飞行状态可分别实现超音速燃烧和亚音速燃烧，从而达到把超燃冲压发动机的工作范围下限扩大到飞行马赫数为３。
In this paper, a supersonic combustion chamber composed of equal sections, expansion sections and equal sections is designed and a combustion experiment is carried out. The results of one-dimensional calculation and analysis show that the supersonic combustion chamber, which is composed of equal section section, expansion section and equal section section, can realize supersonic combustion and subsonic combustion respectively by a certain fuel injection mode according to flight conditions Reach the scramjet engine working range expanded to the limit of Mach 3.