| 火箭低温液体推进剂增压系统数学模型 |
| |
| 引用本文： | 张超,鲁雪生,田丽亭. 火箭低温液体推进剂增压系统数学模型[J]. 低温与超导, 2005, 33(2): 35-38 |
| |
| 作者姓名： | 张超 鲁雪生 田丽亭 |
| |
| 作者单位： | 中原工学院能源与环境工程系,郑州,450007;上海交通大学制冷与低温工程研究所,上海,200030 |
| |
| 摘 要： | 针对火箭低温液体推进剂增压系统建立了数学模型,目的是为获得满足工程精度要求的飞行期间贮箱内气相空间的压力、温度以及贮箱壁壁温的变化规律.数学模型被证明有较好的计算精度,且模型能适应不同种类的增压气体,甚至混合型增压气体,能适应加注后停放期间和飞行期间的计算.
|
| 关 键 词： | 火箭 低温液体 推进剂 增压系统 数学建模 |
| 修稿时间： | 2005-01-17 |
The Numerical Model of Rocket Cryogenic Liquid Propellant Pressurization System |
| |
| Zhang Chao,Lu Xuesheng,Tian Liting. The Numerical Model of Rocket Cryogenic Liquid Propellant Pressurization System[J]. Cryogenics and Superconductivity, 2005, 33(2): 35-38 |
| |
| Authors: | Zhang Chao Lu Xuesheng Tian Liting |
| |
| Abstract: | A numerical model is made for the rocket cryogenic liquid propellant pressurization system, which want to obtain the regularity of pressure, temperature and gas mass in gas space of the propellant tank and the wall temperature of the tank. The comparison between the calculated and the flight results proves well the accuracy of the numerical model. The model can be used in different pressurization gas and combined pressurization gas conditions, and also be used in calculation in the parking period after the filling-up. |
| |
| Keywords: | Rocket Cryogenic liquid Propellant Pressurization system Numerical model |
| 本文献已被 CNKI 万方数据 等数据库收录！ |
|
