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日本液氧/液氢推进系统(打算用于未来日本运载火箭H-1的第二级)的研制计划,目前正由日本有关火箭技术的三家有代表性的机构,即:宇宙开发事业团,航空宇宙技术研究所和东京大学宇宙航空研究所合作执行。宇宙航空研究所从1975年便开始按照自己的计划进行液氧/液氢推进系统研制性的研究工作,到1980年,七吨级推力的发动机各主要组合件的研制性试验已接近完成。该发动机的推力室为管束式结构,其额定设计性能为:真空推力7000公斤,真空比推力433秒。燃气发生器为侧向出口逆流型式,它由球形燃烧室,12个同轴式喷嘴的喷注器和一个起动活门组成。涡轮泵的结构设计是非常特殊的,它在过去的火箭发动机上从来未曾研制过。液氧泵和液氢泵分别安装在各自的终端,而涡轮装在涡轮泵装置的中央,两台泵各自装在互不相连的两根轴上,因为两个涡轮转子之间没有导向叶片(静子),所以两个转子彼此按相反的方向旋转。固体推进剂燃气发生器用作涡轮的起动器。1980年6月,发动机系统与这些组合件一起组装并进行了试验。宇宙航空研究所在管束式推力室研制的同时,还正在研制沟槽式推力室,此种推力室准备用于未来的高性能发动机,沟槽式推力室的制造采用了扩散焊接工艺。本文介绍了由宇宙航空研究所进行的液氧/液氢推进系统方面的研制现状。
The development plan of the Japanese liquid oxygen / liquid hydrogen propulsion system (to be used for the second stage of the future Japanese carrier rocket H-1) is currently under the supervision of three representative agencies of Japan’s rocket technology, namely, the Space Development Group, Aerospace Technology Institute and the University of Tokyo Institute of Astronautics in cooperation. Since 1975, the Institute of Astronautics and Astronautics (JAXA) has started its research work on liquid oxygen and hydrogen-hydrogen propulsion systems in accordance with its own plan. By 1980, the development test of the major components of a seven-ton-thrust engine was nearing completion. The thrust chamber of the engine is a tube bundle structure, and its rated design performance is: a vacuum thrust of 7000 kg and a vacuum ratio of 433 seconds. The gas generator is a lateral outlet countercurrent version consisting of a spherical combustor, an injector for 12 coaxial nozzles and a start-up valve. Turbine pump structural design is very special, it has never been rocket engine in the past. Liquid oxygen pump and liquid hydrogen pump were installed in the respective terminal, and the turbine mounted in the center of the turbo pump device, the two pumps are installed in the two separate shaft, because there is no guide between the two turbine blades ( Stator), so the two rotors rotate in opposite directions to each other. Solid propellant gas generator used as a turbine starter. In June 1980, the engine system was assembled with these assemblies and tested. Astronautics Institute of Aeronautics and Astronautics at the same time, is also developing trench thrust chamber, this thrust chamber is prepared for the future of high-performance engine, trench thrust chamber using diffusion welding process. This article presents the current status of research and development on liquid oxygen and liquid hydrogen propulsion systems conducted by the Aeronautics and Space Administration.