Static performance modeling and simulation of the staged combustion cycle LPREs

作     者：Naderi, Mahyar Liang Guozhu 

作者机构：Beihang Univ Sch Astronaut Beijing 100083 Peoples R China 

出 版 物：《AEROSPACE SCIENCE AND TECHNOLOGY》 (航宇科学与技术)

年 卷 期：2019年第86卷第Mar.期

页      面：30-46页

核心收录：

学科分类：08[工学] 0825[工学-航空宇航科学与技术] 

主　　题：Liquid propellant rocket engine Space Shuttle Main Engine (SSME) Steady state performance System modeling and simulation 

摘      要：The objective of the current research is to analyze the steady state performance of staged combustion cycle liquid propellant rocket engines (SCCLPREs) and to provide a comprehensive case study with all the required technical input data. For this purpose, using the modular concept, engine components are classified into 14 modules and a modeling and simulation platform for SCCLPRE integrated system simulation has been developed in MATLAB Simulink. Space shuttle main engine (SSME) has been selected as a case study, and its static performance has been studied. A total of 34 elements has been taken into account, and using 110 linear/non-linear equations the engine s system modular model has been established. Most of the equations are solved by direct substitution of the initial guesses and iteration through eleven nested iterative loops and a few nonlinear complex equations are solved by Newton-Raphson method. The SSME s throttled performance at four different throttling levels has been simulated, and the effect of throttling has been studied on engine major elements. It is found that by throttling, the pressure of preburners, combustion chamber and high-pressure turbopumps are influenced more than other elements. The simulation mean error at 109% rated thrust level (RTL), 100% RTL, 60% RTL and 50% RTL is 1.63%, 5.76%, 12.91% and 15.28% respectively. Comparing to the previous studies, the simulation accuracy has been enhanced 3% to 7%. The developed model is a basis for further research over SSME and other SCCLPRE. (C) 2018 Elsevier Masson SAS. All rights reserved.