This Paper presents the results of a rotating detonation engine rocket sled test demonstration on a 127 mm gauge rail at 100 m long high-speed running track test equipment to evaluate the thrust performance of a stand-alone rotating detonation engine propulsion system. The developed sled test demonstrator contained all onboard subsystems, including engine, gas cylinders, valves, controller, and a data logger. The sled test demonstrator successfully generated thrust, and three or four detonation waves of 1460 to $1800\mathrm{m}/\mathrm{s}$ were observed during the 2.0 s burn time. The measured specific impulse in the sled test was 144 s as estimated from the acceleration of the demonstrator and the mass decrease in the onboard cylinders. The test results were compared with the data from a laboratory-stand firing test using a load cell, and the specific impulses of the sled test were found to be comparable to the results of the stand firing test.

本文介绍了在100 m长的高速跑道测试设备上的127 mm轨距轨道上的旋转爆震发动机火箭雪橇测试演示的结果，以评估独立式旋转爆震发动机推进系统的推力性能。开发的雪橇测试演示器包含所有机载子系统，包括发动机，气瓶，阀门，控制器和数据记录器。雪橇测试演示器成功产生了推力，并产生了3到4次1460的爆轰波$1800\mathrm{米}/\mathrm{s}$在2.0秒的燃烧时间内观察到。根据示威者的加速度和车载汽缸的质量下降，在雪橇测试中测得的比冲为144 s。将测试结果与使用称重传感器的实验室标准点火测试的数据进行了比较，发现滑板测试的特定脉冲与标准点火测试的结果相当。