The rocket-based combined-cycle engine is considered as a promising scheme to achieve affordable and reusable space transportation. Under the ejector mode, the air mass flow rate is limited by aerodynamic chocking in the mixer of the engine. In other words, the air mass flow rate is determined by the downstream mixing. However for the requirement of critical air mass flow rate, the air stream supplying and the internal thrust measurement are difficult to conduct in the conventional ground experimental facilities. And more importantly, the critical thrust performance is also hard to obtain. A novel experimental facility is introduced in which the air stream is entrained from the ambient atmosphere. The inlet throat is large enough to make sure the inflow air is throttled by aerodynamic chocking in the mixer. In addition, a supersonic ejector is used to simulate the pressure environment at a high altitude. The internal thrust under different flight conditions can be calculated through the measured parameters in the experiments. The results show that the novel experimental facility can be used to study the thrust performance of rocket-based combined-cycle engine in ejector mode. The test precision is acceptable and the thrust difference between the test and the simulation is less than 8%. With the increase of the inflow Mach number, the engine internal drag under the cold flow condition rises as well as the specific impulse augmentation. The specific impulse augmentation could be 16.5% when the entrainment ratio is 1.88 at a simulated condition of H6.8 km / Mach 1.2.

基于火箭的联合循环发动机被认为是实现负担得起和可重复使用的太空运输的有前途的方案。在喷射器模式下，空气质量流量受到发动机混合器中的空气动力阻塞的限制。换句话说，空气质量流量由下游混合决定。然而对于要求 临界空气质量流量、气流供应和内部推力测量在常规地面实验设施中难以进行。更重要的是，临界推力性能也很难获得。引入了一种新的实验设施，其中空气流从环境大气中夹带。入口喉部足够大，以确保流入的空气通过混合器中的空气动力阻塞进行节流。此外，采用超音速喷射器模拟高空压力环境。不同飞行条件下的内推力可以通过实验中的实测参数计算得出。结果表明，该新型实验装置可用于研究火箭基联合循环发动机在喷射器模式下的推力性能。 是可以接受的，测试和模拟之间的推力差异小于8%。随着流入马赫数的增加，发动机在冷流条件下的内阻增加，比冲增加。在H6.8 km / Mach 1.2的模拟条件下，当夹带比为1.88时，比冲增加可以是16.5%。