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直连式燃烧室试验装置用于研究以氢作燃料的超燃冲压发动机燃烧室的性能。通过使用氢燃料补氧燃烧加热器，该装置可进行模拟Ｍａ＋５～８飞行状态的试验。是近进行了模拟Ｍａ＝５．９～６．２加速过程的试验。试验时有计划地改变了燃料流量，同时，燃料与空气的当量比保持恒定，燃烧室由具有燃前激波系（在喷嘴平面产生亚音速气流）的双燃料冲压发动机转变成没有燃前激波系的超燃冲压发动机。提供了试验结果并介绍了试验设备及控制系统。
The Direct Combustion Chamber Test Unit was used to study the performance of a scramjet engine combustor with hydrogen as the fuel. Through the use of hydrogen fuel oxygen combustion heater, the device can simulate the Ma +5 ~ 8 flight state test. Is a simulation of the recent Ma 5.9 ~ 6.2 acceleration process of the experiment. The fuel flow was systematically changed during the test while the equivalence ratio of fuel to air was kept constant. The combustion chamber was transformed by a dual fuel ramjet with a pre-combustion shock (subsonic airflow at the nozzle plane) Wave system of scramjet engine. Provided the test results and introduced the test equipment and control system.