Modeling and Analysis of a LOX/Ethanol Liquid Rocket Engine

Mota, Fábio Antônio da Silva; Hinckel, J. N.; Rocco, Evandro Marconi; Schlingloff, Hanfried

doi:10.5028/jatm.v10.914

Cited by 6 publications

(2 citation statements)

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“…The resistance at the throat is particularly important since the strongest heat fluxes are found in this region, as represented in figure 1. The total thermal flux profile is estimated from an analytical thermal analysis based on a Russian methodology [10][11][12] combined with Bartz correlation, that shows a maximum thermal load of 0.75 MW m −2 is obtained in the throat region of a 5 kN chamber [13].…”

Section: Simulation and Experimental Set-up For Ablation Testsmentioning

confidence: 99%

Microstructural and ablative properties of graphite nozzles with SiC coating deposited by CVD technique

Loureda

Caliari

Regiani

et al. 2020

Mater. Res. Express

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The development of efficient, reliable and affordable propulsion units is one of the main objectives in the development of aerospace technology. Typically the final cost of the vehicle is deeply affected by this subsystem. In this study, a hybrid combination of the ablative chamber is presented where graphite nozzles coated with chemical vapor deposited Silicon Carbide (CVD-SiC) is submitted to the ablative environment, generated by a DC plasma torch operating at a power of 35 kW and homogeneous heat flow of 0.75 MW m −2 . The ablative properties of the samples were evaluated by measuring the weight loss as a function of the exposure time, weight loss of 0.11% after 70 s of exposition due to the formation of SiO gas was observed. The microstructure characteristics of SiC coating before and after ablation tests were carried out by SEM and XRD showing that it goes to scale oxidation to forming of SiO 2 (β-quartz) and SiC (β to α) phase transformation. Whereas the ablation mechanism showed to be dependent on the initial coating thickness and exposure time.

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Section: Simulation and Experimental Set-up For Ablation Testsmentioning

confidence: 99%

Microstructural and ablative properties of graphite nozzles with SiC coating deposited by CVD technique

Loureda

Caliari

Regiani

et al. 2020

Mater. Res. Express

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show abstract

“…The objective function strives for the maximization of the specific impulse and the thrust‐to‐weight ratio of the engine on the basis of the systemic requirements and design assumptions by changing the combustion pressure and oxidizer‐to‐fuel mass flow rate ratios. Mota et al 17 studied the performance and dry weight of the engine to develop the L‐75 with an oxygen‐ethanol propellant. Then, they analyzed the effects of changing the design parameters on the performance, and studies for new propulsion systems are now being performed in the field of aerospace.…”

Section: Introductionmentioning

confidence: 99%

A new synthetic metamodel methodology for liquid‐propellant engine's cooling system optimization

2020

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The present paper strives for optimization of the cooling system of a liquid-propellant engine (LPE). To this end, the new synthetic metamodel methodology utilizing the design of experiment method and the response surface method was developed and im-How to cite this article: Alimohammadi HR, Naseh H, Ommi F. A new synthetic metamodel methodology for liquid-propellant engine's cooling system optimization.

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Multivariable Control Coupling Analysis and ALQR Thrust Controller Design of Liquid Rocket Engine

Guo

Liu

2021

2021 12th International Conference on Mechanical and Aerospace Engineering (ICMAE)

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Modeling and Analysis of a LOX/Ethanol Liquid Rocket Engine

Cited by 6 publications

References 0 publications

Microstructural and ablative properties of graphite nozzles with SiC coating deposited by CVD technique

Microstructural and ablative properties of graphite nozzles with SiC coating deposited by CVD technique

A new synthetic metamodel methodology for liquid‐propellant engine's cooling system optimization

Multivariable Control Coupling Analysis and ALQR Thrust Controller Design of Liquid Rocket Engine

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