|Table of Contents|

Mass calculation of key assembly units in LH2/ LOX rocket engine based on visual interface(PDF)

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

Issue:
2015年04期
Page:
61-66
Research Field:
研究与设计
Publishing date:

Info

Title:
Mass calculation of key assembly units in LH2/ LOX rocket engine based on visual interface
Author(s):
XUE wei;  CAI Zhenyu;  CAO Hongjuan;  GE Qingming
Beijing Aerospace Propulsion Institute, Beijing 100076, China
Keywords:
aerospace propulsion systemliquid propellant rocket enginemass modelvisual interface
PACS:
V434-34
DOI:
-
Abstract:
At the beginning of project development of a new aerospace launch vehicle, in order to choose the design scheme of propulsion system, it's necessary to contrast and optimize the rocket's parameters, such as mass and performance. However, it's difficult to calculate the mass of a liquid propellant rocket engine duo to more related factors, because there is nearly no rule to follow, so the mass evaluation of a liquid propellant rocket engine is usually not precise. According to the characteristics of the liquid propellant rocket engine and project experiences, the mass calculation models for the key assembly units of the engine are proposed in this paper. Two kinds of different models to calculate the mass of thrust chamber and turbopump are presented and compared. At last, based on the VC++ platform, the visual interface was designed for the mass calculation model. The mass models were validated by the calculation of different kinds of liquid propellant rocket engines.

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