论文部分内容阅读
本文介绍涡轮泵式和加压式两种推进系统的小型氢氧发动机的研究试验结果。涡轮泵式推进系统具有高性能和高质量比的优点。加压式推进系统具有高可靠性和结构简单的优点。运载工具上面级采用上述超低温推进系统将增加载荷容量并降低成本。例如 H-1A 大型火箭第三级的固体发动机用超低温级发动机取代载荷容量将从550公斤增加到800公斤。系统参数经过研究,选用1000公斤推力级发动机作研究试验。生产了一台用于加压式推进系统的推力室组件并进行了试验。试验结果表明,它具有满足系统要求的良好性能。带有点大器和推进剂活门的涡轮泵式发动机系统通过热试车也取得预期的性能。
This article presents the results of research trials on small oxy-hydrogen engines in turbo-pump and pressurized two-propulsion systems. Turbine pump propulsion system has the advantages of high performance and high quality ratio. Pressurized propulsion system has the advantages of high reliability and simple structure. The use of the above cryogenic propulsion system at the top of the vehicle will increase the load capacity and reduce costs. For example, H-1A large rocket third-class solid engine with ultra-low temperature grade engine replacement load capacity will be increased from 550 kg to 800 kg. System parameters after research, the choice of 1000 kg thrust-class engine for research and testing. A thrust chamber assembly for a pressurized propulsion system was produced and tested. The test results show that it has good performance to meet the system requirements. Turbine-pump engine systems with point amplifiers and propellant valves also achieved the expected performance with a hot test run.