| 重型火箭下面级发动机基本参数分析 |
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| 引用本文： | 李湘宁,刘宇.重型火箭下面级发动机基本参数分析[J].航空动力学报,2009,24(4):938-944. |
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| 作者姓名： | 李湘宁 刘宇 |
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| 作者单位： | 北京航空航天大学,宇航学院,北京,100191 |
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| 摘 要： | 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.
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| 关 键 词： | 重型火箭 液体火箭发动机 液氧/烃类推进剂 |
| 收稿时间： | 4/21/2008 2:55:57 PM |
| 修稿时间： | 2008/6/30 0:00:00 |
Basic parameters analysis of first stage engine system for heavy lift vehicle |
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| LI Xiang-ning and LIU Yu.Basic parameters analysis of first stage engine system for heavy lift vehicle[J].Journal of Aerospace Power,2009,24(4):938-944. |
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| Authors: | LI Xiang-ning and LIU Yu |
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| Institution: | School of Astronautics;Beijing University of Aeronautics and Astronautics;Beijing 100191;China |
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| Abstract: | The structure and basic parameters of propulsion system for existing heavy lift launch vehicles were analyzed.The structure and task requirements were proposed to meet the manned lunar-landing demand.Considering the performance,economics,technical difficulties and working reliability,a scheme of the first stage engine system for heavy lift launch vehicle was proposed,including the thrust level,propellant type and engine cycle.System simulation models were established for 9 model engines using the object-ori... |
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| Keywords: | heavy lift launch vehicle liquid propellant rocket engine liquid oxygen/hydrocarbon propellants |
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