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为了指导未来近地轨道运载火箭技术的研制工作,需要对运载火箭作一些研究分析。最近的研究工作已经分析了采用双组元烃类燃料发动机和单独的液氢燃料发动机一起使用的单级运载火箭和两级运载火箭。初期研究工作表明,利用液氢冷却和产生动力的三组元发动机具有极大潜力。本研究报告对双组元发动机和三组元发动机进行了比较。比较结果表明,采用三组元发动机比采用双组元发动机的运载火箭的结构重量轻,双膨胀发动机能使运载火箭的结构重量减到最小。然而,双钟形喷管发动机也能使运载火箭的结构重量减到那么小,而且是一种较容易冷却的设计方案。
In order to guide the future development of near-Earth orbit rocket technology, some research and analysis on launch vehicles are needed. Recent research has analyzed single-stage and two-stage launch vehicles using a two-component hydrocarbon fuel engine together with a separate liquid hydrogen-fueled engine. Initial research shows that the use of liquid hydrogen cooling and the power of the three-component engine has great potential. This study compares two-component engines and three-component engines. The comparison results show that the structure of the three-component engine is lighter than that of the two-component vehicle, and the double-expansion engine can minimize the weight of the carrier rockets. However, the twin bell nozzle engine also makes the structure weight of the launch vehicle as small as possible, and is a design that is easier to cool.