Fuel Regression Characteristics in Hybrid Rockets Using Nitrous Oxide/High-Density Polyethylene

Ito, Seiji; Kamps, Landon T.; Nagata, Harunori

doi:10.2514/1.b37875

Cited by 4 publications

(3 citation statements)

References 11 publications

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“…[32,53,68,69], the chamber pressure has been found to have an influence on the regression rate, producing at most, a 5% of burn rate variations in our model. This effect has already been considered in several studies [52,55,58] through empirical laws akin to Eq. ( 29).…”

Section: Error Sourcesmentioning

confidence: 98%

“…( 29) a and n are constant preexponential and exponential coefficients, respectively. Both of them result from a polynomial adjustment coming from empirical data, generally leading to a coefficient of determination, R 2 , that can vary in a wide range (approximately from 0.43 to 0.99 [10,[51][52][53]). This power law is most employed in numerical models to describe HRE fuel pyrolysis in a simple and direct way.…”

Section: B Verifications For a Reactive Flow Case: Influence Of Mass ...mentioning

confidence: 99%

“…( 29)]. The computation of this diameter can be done by two techniques: geometrically, through the measurement of the averaged remaining fuel thickness of the block [51]; or by performing a fuel mass conservation in the chamber at the end of the test [52,55,57,59,[62][63][64]. Regression rate may vary up to a 15% using one method or the other due to the regression of the lateral faces of the solid fuel.…”

Section: Error Sourcesmentioning

confidence: 99%

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Pseudo-Two-Dimensional Modeling and Validation of a Hybrid Rocket Combustion Chamber

Granado

Hijlkema

Lestrade

et al. 2022

Journal of Propulsion and Power

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A pseudo 2-D model for the cylindrical combustion chamber of a hybrid rocket is developed in this article with the purpose of its integration in a system design tool used for engine predesign phases. A compromise of simplicity and accuracy is thus required. Integral transient boundary layer equations are included and coupled with the mass and energy balances at the fuel surface, where fuel pyrolysis is described by an Arrhenius law. Studies assessing the model in the non-reactive case provide satisfactory results regarding the description of the boundary layer. Concerning the hybrid case, the computed steady-state fuel regression rates are found to be in the low region of the reference values coming from semiempirical laws for several oxidizer/fuel couples and oxidizer mass fluxes, producing errors up to 50% for certain sources. The effect of mass flux and motor size is correctly simulated. Eventually, the whole engine operation is assessed through the comparison of the computed results with three experimental tests realized at our laboratory and using a 87.5% Hydrogen Peroxide/High-Density Polyethylene couple. Corresponding results lead to regression rate errors varying in a wide range (from 10

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