电动泵压式液氧煤油变推力火箭发动机动力学建模与仿真分析: Part I-单点工况分析

doi:10.7527/S1000-6893.2021.24884

流体力学与飞行力学

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电动泵压式液氧煤油变推力火箭发动机动力学建模与仿真分析: Part I-单点工况分析

崔朋, 宋杰, 李清廉, 陈兰伟, 梁涛, 孙郡

国防科技大学空天科学学院高超声速冲压发动机技术重点实验室, 长沙 410073

收稿日期:2020-10-16 修回日期:2021-01-21 出版日期:2022-01-15 发布日期:2021-01-21
通讯作者: 李清廉 E-mail:peakdreamer@163.com
基金资助:
载人航天预先研究项目（050302）

Dynamic modeling and simulation analysis of LOX/RP1 variable thrust engines using motor pump: Part I-single condition analysis

CUI Peng, SONG Jie, LI Qinglian, CHEN Lanwei, LIANG Tao, SUN Jun

Science and Technology on Scramjet Laboratory, College of Aerospace Science and Technology, National University of Defense Technology, Changsha 410073, China

Received:2020-10-16 Revised:2021-01-21 Online:2022-01-15 Published:2021-01-21
Supported by:
Pre-research Project in Manned Space (050302)

摘要/Abstract

摘要： 为了解决电动泵压式液氧煤油变推力火箭发动机系统响应特性不明晰的问题，综合考虑了电池、电机及冷却通道的影响，建立了电动泵压式液氧煤油变推力火箭发动机仿真平台，深入研究了不同工况下系统响应特性以及系统性能参数随推力水平的变化规律。研究结果表明：系统性能参数响应存在短板效应，尽管电动泵响应速度快，而冷却通道参数响应速度慢，导致系统性能参数响应时间是电动泵转速响应时间的10倍以上；此外，低推力工况时，适当降低混合比，能够保证冷却通道出口亚临界情况下的顺利调节。因此，为了提高系统响应特性，在满足冷却压降要求时，应尽可能提高冷却通道内冷却剂流速。

关键词: 液氧煤油, 电动泵, 变推力, 液体火箭发动机, 系统动力学, 建模与仿真, 冷却通道

Abstract: LOX/RP1 variable thrust liquid rocket engines using a motor pump have been widely studied in recent years because of their environmentally friendly performance, adjustable throttling depth and convenient adjustment. As a kind of variable thrust rocket engine, its system response characteristics are critical in directly determining the spacecraft maneuverability. However, previous research on the LOX/RP1 variable thrust engine using a motor pump mainly focuses on the system scheme design, and the dynamic analysis is relatively preliminary. In this paper, the response characteristics of the throttling system under different conditions and the variation of system performance parameters with the thrust level are studied by establishing a simulation platform of the LOX/RP1 variable thrust engine using a motor pump in consideration of the influence of the battery, motor and cooling channel. The results show that, although the response speed of the motor pump is fast, that of the cooling channel parameters is slow, leading to a short board effect. That is, the response time of the system performance parameters is ten times more than that of the motor pump speed. Contrarily, under low operating conditions, reducing the mixing ratio can ensure the smooth regulation of the thrust when the cooling channel outlet is in subcritical condition. Therefore, to improve the response characteristics of the system, the flow velocity in the cooling channel should be increased as much as possible when the pressure drop requirements are met.

Key words: LOX/RP1, motor pumps, variable thrust, liquid rocket engines, system dynamics, modeling and simulation, cooling channels

中图分类号:

V435

崔朋, 宋杰, 李清廉, 陈兰伟, 梁涛, 孙郡. 电动泵压式液氧煤油变推力火箭发动机动力学建模与仿真分析: Part I-单点工况分析[J]. 航空学报, 2022, 43(1): 124884.

CUI Peng, SONG Jie, LI Qinglian, CHEN Lanwei, LIANG Tao, SUN Jun. Dynamic modeling and simulation analysis of LOX/RP1 variable thrust engines using motor pump: Part I-single condition analysis[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(1): 124884.

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电动泵压式液氧煤油变推力火箭发动机动力学建模与仿真分析: Part I-单点工况分析

Dynamic modeling and simulation analysis of LOX/RP1 variable thrust engines using motor pump: Part I-single condition analysis

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