Transient Analysis of the LE-7A Rocket Engine Using the Rocket Engine Dynamic Simulator (REDS)

Yamanishi, Nobuhiro; Kimura, Toshiya; Takahashi, Masahiro; Okita, Koichi; Negishi, Hideyo; Atsumi, Masahiro

doi:10.2514/6.2004-3850

Cited by 15 publications

(5 citation statements)

References 4 publications

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“…The REDS was verified with a large amount of engine test data registered in ReDak. 1 On the other hand, coupled analysis between fluid and structure was carried out for the purpose of the troubleshooting which occurred in the liquid hydrogen turbopump of LE-7A. [2][3][4] It was confirmed that the analytical result had caught the phenomenon of the trouble correctly by comparison with test data contained in ReDak.…”

Section: A Analysis Of Phenomena In Rocket Enginementioning

confidence: 92%

Development and Utilization of Rocket Engine Test Database (ReDak) in Japan Aerospace Exploration Agency

Sugimori¹,

Ueda²,

Nanri³

et al. 2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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This paper presents an outline of the rocket engine test database system developed by the Japan Aerospace Exploration Agency (JAXA) and examples of its practical use. At JAXA, we have developed many rocket engines over the past 30 years and have tested the various kinds of engines and their components, i.e., combustion chambers and turbopumps. Moreover, JAXA has carried out development tests of rocket engines at test stands constructed all over the country. To allow the data acquired by various test stands should be managed intensively and accessed by selected organizations and companies, a database system (ReDak: Rocket Engine Data Archive in Kakuda) was developed. The data stored in ReDak are not only measurement data, pressure, temperature, etc., to evaluate engine function and performance, but also documents evaluating the conditions and results all tests. The data in ReDak are useful for trend analysis of data and verification of analytical models. This article introduces the database system of ReDak and its utilization by showing examples of its practical use. We hope that the data stored in ReDak will be utilized by organizations other than JAXA, and further contribute to technical development of rocket engines and growth of a space industry community.

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Section: A Analysis Of Phenomena In Rocket Enginementioning

confidence: 92%

Development and Utilization of Rocket Engine Test Database (ReDak) in Japan Aerospace Exploration Agency

Sugimori¹,

Ueda²,

Nanri³

et al. 2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

View full text Add to dashboard Cite

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“…The space-advanced countries developed simulation programs mostly for LPREs by developing their own SLVs. Typical examples are rocket engine transient simulation (RO-CETS) developed by Pratt & Whitney in the U.S., consisting of thirteen component modules, and the rocket engine dynamic simulator (REDS) by Japan Aerospace eXploration Agency (JAXA), which is an upgrade version of ROCETS using partial differential Equation (PDE) to obtain nonlinear mass flow rate and heat transfer characteristics in the pipeline [28,29]. EcosimPro is also one of the representative programs used for a commercial program called European Space Propulsion System Simulation (ESPSS), employing a set of libraries containing various types of components that can be interconnected to model complex dynamic systems in Europe [30,31].…”

Section: Liquid-propellant Rocket Enginesmentioning

confidence: 99%

“…Lumped model method [34,40,60,67] Method of characteristics [37,141] Volume-junction method (Lumped parameter method) [29,39,47,142] 3.2.3. Others…”

Section: Refs (Selected)mentioning

confidence: 99%

“…In an LPRE, since the cooling system (or heat exchanger) uses fuel before injecting it into the combustion chamber, the heat from the combustion gas changes the fuel state, such as gasified or two-phase flow. For this reason, if the fuel is a cryogenic propellant, the fuel state changes intensify, so the nonlinearity of the pressure drop by the heat becomes more extreme than in other types of fuels [29,34,53,158,159]. On the other hand, if the fuel is not cryogenic, the nonlinearity of the pressure drop by the heat is negligible enough to represent using the function of mass flow rate with a constant coefficient, so the governing equations related to the heat exchangers can become algebraic equations and the differential type equations are required no more.…”

Section: Mathematical Modeling Of Chemical Propulsion Systemsmentioning

confidence: 99%

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Numerical Simulation of Chemical Propulsion Systems: Survey and Fundamental Mathematical Modeling Approach

Cha

2023

Aerospace

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This study deals with the mathematical modeling and numerical simulation of chemical propulsion systems (CPSs). For this, we investigate and summarize a comprehensive collection of the simulation modeling developments of CPSs in academic works, applications, and industrial fields. Then, we organize and analyze the simulation modeling approaches in several ways. After that, we organize differential-algebraic Equations (DAEs) for fundamental mathematical modeling consisting of the governing Equations (ordinary differential equations, ODEs) for the components and other equations derived from several physical rules or characteristics (algebraic equations or phenomenological equations, AEs) and then synthesize and summarize the fundamental structures of analytic mathematical modeling by types (liquid-propellant rocket engines, solid-propellant rocket motors, and hybrid-propellant rocket motors) of CPSs.

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“…Li et al reviewed the technological progress of the dynamic characteristics simulation, and the result can be summarized as "graphical interface, independent simulation environment, metamodel abstraction, and high reusability" [13]. Some representative achievements are German DRL company modular engine analysis system [14], ROCETS in NASA Marshall Space Flight Center and its improved software ESAY5x [15], CARINS in French [16], and Japan LE-7A Engine MPI parallel software REDS [17]. In terms of commercial platforms, there are EcosimPro of Spain's EAI Company, the aerospace propulsion system simulation module ESPSS [18] jointly developed by the European Space Agency, AMESim of Siemens company [19], and so on.…”

Section: Introductionmentioning

confidence: 99%

Dynamic Characteristics of LOX/Kerosene Variable Thrust Liquid Rocket Engine Test System Based on General Modular Simulation Method

Wang

Yan

et al. 2022

International Journal of Aerospace Engineering

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For the research demand of reusable LOX/kerosene variable thrust liquid rocket engine, a test system with electric displacement pumps is designed and a multidisciplinary modular dynamic simulation method based on AMESim platform is used to analyze the system. The method comprehensively considers the characteristics of complex components in the engine and realizes the fast module assembly and variable step size solution. Considering the combustion model of thrust chamber, the positive displacement pump model with complex leakage channels, and the cooling jacket heat transfer model, the component dynamic equations are deduced and the final model simulation results reveal that the system has a smooth ignition, stage turning, and shutdown process. The thrust can reach 6900 N in high working condition and the variable thrust ratio is 5 : 1. The dynamic characteristics of the system show that the performance error of main pump components is less than 5%, the maximum average temperature rise of the thrust chamber coolant is about 28°C, and the time of stage adjustment is within 300 ms, which mean the overall design of the system is reasonable. Although the accumulation of LOX before kerosene injection can adversely affect the temperature of the thrust chamber, large pressure pulses do not occur due to the ignitor’s duty flame. Moreover, the pintle injectors based on PID control can effectively stabilize the pressure drop at lower conditions. The system and the simulation method provide important support for the actual engine test and the general LRE dynamic characteristics analysis.

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Transient Analysis of the LE-7A Rocket Engine Using the Rocket Engine Dynamic Simulator (REDS)

Cited by 15 publications

References 4 publications

Development and Utilization of Rocket Engine Test Database (ReDak) in Japan Aerospace Exploration Agency

Development and Utilization of Rocket Engine Test Database (ReDak) in Japan Aerospace Exploration Agency

Numerical Simulation of Chemical Propulsion Systems: Survey and Fundamental Mathematical Modeling Approach

Dynamic Characteristics of LOX/Kerosene Variable Thrust Liquid Rocket Engine Test System Based on General Modular Simulation Method

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