A modular method for the analysis of liquid rocket engine cycles

The paper describes the methodology of DLR's tools for rocket engine systems analysis. The holistic approach begins with a component based cycle analysis. Parameter variations are performed in order to select the engine reference case. After selection of suitable engine parameters the derived engine performance is used as basis of a high level launcher analysis.The paper provides a detailed description of the tools and the implemented methods. The paper then discusses different variants of open loop cycles. Different propellant combinations are compared and parametric variations of mixture ratio, chamber pressure, and nozzle expansion ratio are performed. Following the engine cycle analysis a launcher trajectory analysis is performed to evaluate the engine concept in terms of achievable payload masses. A generic space launch system is used as baseline for this evaluation.

show abstract

“…2 It allowed a flexible user defined cycle definition and contained routines for tripropellant and multiple thrust chamber engines.…”

Section: Iib1 Tool Heritage and Development Roadmapmentioning

confidence: 99%

Performance Analysis of Low-Complexity Upper-Stage Demonstrator Engines

Herbertz¹,

Fromm²,

Manfletti³

2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

View full text Add to dashboard Cite

show abstract

“…29, and all of the operating parameters are listed. 23 There are boost pumps for both oxygen and hydrogen to increase suction pressure to the main pumps. The oxygen boost pump has two stages with different rotational speeds, actuated by a hydraulic turbine.…”

Section: B Rd-o120mentioning

confidence: 99%

“…30 and operating parameters are listed. 23 The RD-170 has four combustion chambers fed by a single turbopump driven by gas from an oxidizer-rich preburner. There are boost pumps for oxygen and kerosene.…”

Section: Rd-170mentioning

confidence: 99%

“…Figure 31 shows the tripropellant engine based on an oxidizer-rich staged combustion preburner cycle that uses a combination of liquid oxygen, kerosene, and liquid hydrogen as propellants. 23 The basis for this tripropellant engine cycle is the RD-170 engine. A multiple nozzle version, similar to the RD-170, is called the RD-701, whereas a single nozzle version, used for U.S. SSTO packaging and thrust requirements, is called the RD-704.…”

Section: A Rs-2200mentioning

confidence: 99%

See 1 more Smart Citation

Cycles for Earth-to-Orbit Propulsion

Manski¹,

Goertz²,

Sa-oslash³

et al. 1998

Journal of Propulsion and Power

Self Cite

View full text Add to dashboard Cite

The reduction of Earth-to-orbit launch costs in conjunction with an increase in launcher reliability and operational ef ciency are the key demands on future space transportation systems. Results of various system analyses indicate that these demands can be met with future single-stage-to-orbit (SSTO) vehicles using advanced technologies for both structure and propulsion systems. This paper will provide a classi cation and description of all turbopump feed liquid rocket engine cycles, followed by a combined vehicle/propulsion analysis of the design parameters for the propulsion systems and their associated thermodynamic cycles for the launch of future SSTO vehicles. Existing and projected rocket engine cycles capable of SSTO missions will be presented.

show abstract

“…[1]. In 2000, K. Liu, Y. Zhang developed a methodology for modularization modeling and transient simulation of LPREs and created an object oriented program using Microsoft Visual C++ 6.0 [2].…”

Section: Introductionmentioning

confidence: 99%

Modular simulation software development for liquid propellant rocket engines based on MATLAB Simulink

Naderi

Liang

Karimi³

2017

MATEC Web Conf.

View full text Add to dashboard Cite

Abstract. Focusing on Liquid Propellant Rocket Engine (LPRE) major components, a steady state modular simulation software has been established in MATLAB Simulink. For integrated system analysis, a new algorithm dependant on engine inlet mass flow rate and pressure is considered. Using the suggested algorithm, it is possible to evaluate engine component operation, similar to the known initial parameters during hot fire test of the engine on stand. As a case study, the reusable Space Shuttle Main Engine (SSME) has been selected and the simulation has been performed to predict engine's throttled operation at 109 percent of the nominal thrust value. For this purpose the engine actual flow diagram has been converted to 34 numerical modules and the engine has been modelled by solving a total of 101 steady state mathematic equations. The mean error of the simulation results is found to be less than 5% compared with the published SSME data. Using the presented idea and developed modules, it is possible to build up the numerical model and simulate other LPREs.

show abstract

A modular method for the analysis of liquid rocket engine cycles

Cited by 17 publications

References 0 publications

Performance Analysis of Low-Complexity Upper-Stage Demonstrator Engines

Performance Analysis of Low-Complexity Upper-Stage Demonstrator Engines

Cycles for Earth-to-Orbit Propulsion

Modular simulation software development for liquid propellant rocket engines based on MATLAB Simulink

Contact Info

Product

Resources

About