|Table of Contents|

Thermal analysis of low-thrust liquid rocket engine on orbit(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2019年03期
Page:
15-19
Research Field:
研究与设计
Publishing date:

Info

Title:
Thermal analysis of low-thrust liquid rocket engine on orbit
Author(s):
YAN Bo1; 2;  ZHANG Huiqiang1;  WANG Bing1
(1.School of Aerospace, Tsinghua University, Beijing 100084, China;2.Research and Development Center, China Academy of Launch Vehicle Technology, Beijing 100076,China)
Keywords:
liquid rocket engine;  low-thrust;  solar radiation;  numerical simulation;  thermal analysis
PACS:
V434; TB131
DOI:
-
Abstract:
In order to obtain the influence of solar radiation on the thermal characteristics of low-thrust liquid rocket engine for deep-space-exploration, this paper analyzes the thermal environment of thrust chamber for the liquid rocket engine on orbit.Solar radiation is considered due to its effect on the heterogeneity of temperature field.With considering the structure of a liquid rocket engine, APDL is introduced into ANSYS Workbench to build a finite element model for simulating its three-dimensional steady-state thermal analysis.In view of the actual working situation of low-thrust liquid engine in geosynchronous orbit(GEO), the structural temperature changes of the engine thrust chamber during steady working and not working are analyzed, respectively.The influence of solar radiation on the temperature field is obtained.The solar radiation has little effect on the thrust chamber temperature during the steady state operation.The maximum difference of chamber wall temperature between solar radiation and non-solar radiation is 10 K.When the engine is not working, the engine surface temperature with receiving solar radiation is higher, and the maximum temperature difference is 71.41 K.The solar radiation has a great influence on the non-uniformity of the model.This research provides a criterion to the thermal design of low-thrust liquid rocket engine.

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Last Update: 2019-06-30