| 重型运载火箭动力系统分析 |
| |
| 引用本文： | 李湘宁,刘宇.重型运载火箭动力系统分析[J].航空动力学报,2010,25(1):180-186. |
| |
| 作者姓名： | 李湘宁 刘宇 |
| |
| 作者单位： | 北京航空航天大学,宇航学院,北京,100191 |
| |
| 摘 要： | 讨论了两种载人登月的动力系统方案,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,提出了重型火箭箭体结构和任务要求.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.提出了一套重型火箭动力系统,建立了一个运载火箭系列,并对其运载能力进行了计算.经综合分析,提出登月火箭可采用8 m直径的三级半结构,助推级、第一级和第二级均为推力5 000 kN量级富氧预燃室补燃循环液氧煤油发动机,第三级为2台50 t氢氧发动机.
|
| 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： | 2008/12/22 0:00:00 |
| 修稿时间： | 6/2/2009 12:00:00 AM |
Basic parameters analysis of first stage engine system for heavy lift vehicle |
| |
| LI Xiang-ning and LIU Yu.Basic parameters analysis of first stage engine system for heavy lift vehicle[J].Journal of Aerospace Power,2010,25(1):180-186. |
| |
| Authors: | LI Xiang-ning and LIU Yu |
| |
| Institution: | School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China |
| |
| Abstract: | Two proposals of manned lunar-landing propulsion system were discussed.The structure and basic parameters of propulsion system for existed 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,working reliability,a scheme of the first stage engine system for heavy lift launch vehicle was proposed.A heavy lift vehicle(HLV) system and a HLV series were estableshed,and their payload capability was calculated.Based on integrative analysis,the lunar launch vehicle is suggested to be 3 stage with 4 boosters,and two 50t liquid oxygen/liquid hydrogen are used for the third stage,while liquid oxygen/kerosene stage combustion cycle engines about 5000kN are used for all other stages. |
| |
| Keywords: | heavy lift launch vehicle liquid propellant rocket engine liquid oxygen/hydrocarbon propellants |
| 本文献已被 CNKI 万方数据 等数据库收录！ |
| 点击此处可从《航空动力学报》浏览原始摘要信息 |
| 点击此处可从《航空动力学报》下载免费的PDF全文 |
|
