Based on finite element analysis and the principle of mechanical equivalence, the supporting structures for the hydrogen and oxygen turbine pumps of a rocketengine were analyzed.
在对某火箭发动机氢、氧涡轮泵支撑结构进行有限元分析的同时，对该结构进行了力学理论探讨。
2
The first native liquid-fueled rocketengine used a liquid oxygen and carbon-hydrogen propellant, provided 5.6 tons of thrust, and was installed in unit e.
第一个使用液氧碳氢推进剂的国产液体燃料火箭发动机被安装在了火箭的E段上，它可以提供5.6吨的推力。
3
Base on these, the health condition evaluation system of the liquid hydrogen supplying system of a rocketengine testing platform was set up.