基于RLV飞行过程的氢氧发动机参数设计模型

金平; 汪小卫; 李茂; 蔡国飙

基于RLV飞行过程的氢氧发动机参数设计模型

北京航空航天大学宇航学院, 北京 100191

详细信息

中图分类号: V 412.1
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出版历程
- 收稿日期: 2010-01-19
- 网络出版日期: 2011-04-30

Modeling of hydrogen engine parameters design during flight to orbit of reusable launch vehicle

School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 为了考察氢氧发动机参数选择对可重复使用运载器性能的影响,基于氢氧发动机参数建立了可重复使用运载器入轨飞行过程的计算模型,包括运载器运动方程、飞行控制条件和质量模型,研究了发动机混合比对运载器飞行参数和运载器质量的影响规律.在运载器总质量恒定的情况下,随着发动机混合比由4增大到14,推进剂质量和发动机质量先减小后增大,储箱质量减小,三者的综合效果使得有效载荷质量先增大后减小.
- 可重复使用运载器 /
- 飞行参数 /
- 有效载荷质量 /
- 氢氧发动机 /
- 混合比
Abstract: In order to investigate the influence of hydrogen engine parameters on launch vehicle performance, the mathematical models suited for single stage to orbit reusable launch vehicle flight process were brought up based on hydrogen engine performance parameters, including rocket motion equations, flight control conditions and vehicle mass model. The vehicle mass variety rules were discussed in detail changed with hydrogen engine mixture ratio during flight to orbit. The results show that on the condition the vehicle gross mass set, when hydrogen engine mixture ratio increases from 4 to 14, propellants mass and engine mass decrease firstly and then increase, tank mass decrease all the time, which synthetically bring forth payload mass increase firstly and then decrease.
- reusable launch vehicle /
- flight parameters /
- payload mass /
- hydrogen engine /
- mixture ratio

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参考文献(1)

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