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Static performance modeling and simulation of the staged combustion cycle LPREs

机译：分级燃烧循环LPRE的静态性能建模和仿真

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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 linearon-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.
机译：当前研究的目的是分析分级燃烧循环液体推进剂火箭发动机（SCCLPRE）的稳态性能，并提供所有必要的技术输入数据的综合案例研究。为此，使用模块化概念，将发动机组件分为14个模块，并在MATLAB Simulink中开发了用于SCCLPRE集成系统仿真的建模和仿真平台。案例研究选择了航天飞机主机（SSME），并对其静态性能进行了研究。总共考虑了34个元素，并使用110个线性/非线性方程式建立了发动机的系统模块化模型。大多数方程是通过直接替换初始猜测并通过11个嵌套的迭代循环进行迭代来求解的，而一些非线性复杂方程是通过Newton-Raphson方法求解的。模拟了SSME在四个不同节气门水平上的节气门性能，并研究了节气门对发动机主要元件的影响。发现通过节流，预燃器，燃烧室和高压涡轮泵的压力比其他因素受到的影响更大。 109％额定推力水平（RTL），100％RTL，60％RTL和50％RTL时的模拟平均误差分别为1.63％，5.76％，12.91％和15.28％。与以前的研究相比，仿真精度提高了3％至7％。开发的模型是对SSME和其他SCCLPRE进行进一步研究的基础。 （C）2018 Elsevier Masson SAS。版权所有。

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