Recent advancements in experimental and numerical characterization of paraffin-based fuels for hybrid rocket application

Martino, Giuseppe D. Di; Gallo, Giuseppe; Mungiguerra, Stefano; Carmicino, Carmine; Savino, Raffaele; Cardillo, Daniele; Battista, Francesco

doi:10.2514/6.2019-4195

Cited by 5 publications

(1 citation statement)

References 15 publications

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“…As observed in Ref. [36,37], the mechanism of fuel regression growth with the port diameter is a combination of the increased heat transfer to the wall with the larger liquid wax mechanical entrainment both promoted by the oxidizer jet impingement on the grain surface. An influence of the port diameter on the regression rate was to be expected also from the consideration that, as shown in Figure 8b (despite the oscillations due to the pressure fluctuation) the regression rate is nearly constant with time, displaying only a marginal decrease toward the end of the firing, which clearly involves dependence on an additional parameter other than the mass flux.…”

Section: Figure 11 Average Regression Rate As a Function Of The Total...mentioning

confidence: 65%

Reconstructed Ballistic Data Versus Wax Regression-Rate Intrusive Measurement in a Hybrid Rocket

Messineo

Kitagawa

Carmicino

et al. 2020

Journal of Spacecraft and Rockets

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Burning tests of a laboratory-scale hybrid rocket engine were carried out with gaseous oxygen and a microcrystallinewax based fuel to look into the feasibility of using an intrusive resistor-based sensor for measuring the fuel regression rate.This initial screening was driven by the need for real-time control of the oxidizer-to-fuel ratio in altering-intensity swirlingflow-type hybrid rocket engines aiming at performance optimization. To build up a framework for comparison with the measured data, a traditional ballistic reconstruction technique was critically revised; with the measured aft-chamber pressure and oxygen mass flow rate time histories, the fuel regression-rate and port diameter were reconstructed over the firing, by estimating the combustion efficiency with the constraint that calculated and measured fuel mass consumed are equal. This technique invariably suffers from the issue of presenting multiple solutions for the fuel mass flow rate in the proximity of the optimum mixture ratio, for which a novel variable-efficiency approach is proposed. Reconstructed data show that regression rate is nearly constant in each firing, yielding dependence upon the port diameter other than the mass flux.Resistor-sensor raw data displayed large deviation from the ballistic results for the slower burning rate of the sensor support.A detailed analysis is presented.

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Section: Figure 11 Average Regression Rate As a Function Of The Total...mentioning

confidence: 65%

Reconstructed Ballistic Data Versus Wax Regression-Rate Intrusive Measurement in a Hybrid Rocket

Messineo

Kitagawa

Carmicino

et al. 2020

Journal of Spacecraft and Rockets

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Ramjet combustion instability and thermodynamic performances

Zhao¹

2023

Thermoacoustic Combustion Instability Control

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Multiphysics Modeling for Combustion Instability in Paraffin-Fueled Hybrid Rocket Engines

Casalino,

Ferrero,

Folcarelli

et al. 2024

Journal of Spacecraft and Rockets

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The use of paraffin-based fuels is a promising approach to a low regression rate in hybrid rocket engines, and the capability to describe and predict combustion instability in the presence of liquefying fuels becomes an enabling step towards the application of hybrid rockets in a wide range of space transportation systems. In this work, a multiphysics model having this purpose is presented and discussed. The model is based on a network of submodels in which chamber gas dynamics is described by a quasi-1D Euler model for reacting flows while thermal diffusion in the grain is described by the 1D heat equation in the radial direction. An artificial neural network is introduced to reduce the computational cost required by the chemical submodel. A sensitivity analysis is performed to identify the key parameters, which have the largest influence on combustion instability and to evaluate the predictive capability of the model despite the uncertainty introduced with the necessary modeling simplifications. Results are presented considering two test cases with different oxidizers: hydrogen peroxide and gaseous oxygen. The procedure shows good agreement with the experimental results available in the literature.

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Recent advancements in experimental and numerical characterization of paraffin-based fuels for hybrid rocket application

Cited by 5 publications

References 15 publications

Reconstructed Ballistic Data Versus Wax Regression-Rate Intrusive Measurement in a Hybrid Rocket

Reconstructed Ballistic Data Versus Wax Regression-Rate Intrusive Measurement in a Hybrid Rocket

Ramjet combustion instability and thermodynamic performances

Multiphysics Modeling for Combustion Instability in Paraffin-Fueled Hybrid Rocket Engines

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