Abstract To meet the working requirements of the Rocket-Based Combined Cycle (RBCC) engine, a gas-oxygen/kerosene ejector rocket (strut rocket) is designed and experimentally studied. It was required to operate at a combustion chamber pressure of 2.0 MPa, oxygen-fuel ratio of 2.0, and a single rocket flow of 110 g/s. First, the strut rocket was designed, including the strut design with cooling channels, the rocket engine head design, and the thrust chamber design. The injector, panel, ignition, body thermal protection, and combustion performance were examined through the single component’s cold and hot firing test and the whole rocket. The test results show that the head injector can reasonably achieve the uniform mixing of gas/liquid propellant. The strut rocket can realize multiple stable and reliable ignitions, and there is no ablation at the throat of the thrust chamber, verifying the reliability of the thermal protection design. The rocket combustion efficiency can reach 97.8%, indicating that the strut rocket has excellent combustion performance.
Qu et al. (Fri,) studied this question.