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分析了已有重型火箭动力系统的结构和基本参数,以满足载人登月的任务要求为前提,提出了任务要求以及一套重型火箭箭体结构方案.从性能、经济性、技术难度、工作可靠性等方面综合考虑,提出重型火箭下面级的基本方案,包括推力量级、推进剂以及发动机循环方式的选择.采用面向对象的通用顺序化计算方法,建立发动机系统仿真模型,计算得到9个发动机方案的最高室压及功率平衡参数,分析了燃烧室压强和混合比对发动机性能的影响.经综合分析,建议重型火箭下面级发动机可选择推力4 500~5 000 kN富氧预燃室补燃循环液氧煤油发动机.
Based on the analysis of the structure and basic parameters of the existing heavy rocket power system, the mission requirements and a set of heavy rockets rocket body structure scheme are proposed on the premise of meeting the mission requirements of manned lunar landing.From the aspects of performance, economy, technical difficulty, work Reliability and other aspects, this paper puts forward the basic plan of the subordinate level of heavy rocket, including the selection of the thrust level, propellant and engine cycle mode.Using object-oriented general sequential calculation method, the engine system simulation model is established, and 9 The maximum chamber pressure and the power balance parameter of the engine are analyzed and the influence of the pressure and mixing ratio of the combustion chamber on the performance of the engine is analyzed.A comprehensive analysis suggests that the engine of the next stage of heavy rocket can choose a thrust of 4 500-5 000 kN oxygen- Burning liquid oxygen kerosene engine.