Performance Modeling of a Paraffin Wax / Nitrous Oxide Hybrid Rocket Motor

Geneviève, Bernard; Brooks, Michael J.; Beaujardiere, Jean-François P. Pitot de la; Roberts, Lance W.

doi:10.2514/6.2011-420

Cited by 23 publications

(9 citation statements)

References 4 publications

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“…Regression data versus oxidizer mass flux were also compared with Putnam's data. Figure 37 demonstrates the regression rates calculated using the formula, proposed by Putnam (formula 3) which are about 50%-200% higher compared to regression rates calculated using formula (14). Figure 38 shows comparison of the regression rates data for 1.0in and 0.5in grain diameter with Putnam's regression rate formula (6).…”

Section: Tests Results Numerical Simulation and Data Analysismentioning

confidence: 91%

“…As follows from Fig. 36 the regression rates calculated using formula proposed by Karabeyoglu (2) are about 50%-80% less than regression rates calculated using formula (14). Regression data versus oxidizer mass flux were also compared with Putnam's data.…”

Section: Tests Results Numerical Simulation and Data Analysismentioning

confidence: 98%

“…During the last 30 years, several universities and companies associated with NASA launched research projects on the combustion of advanced HPRE fuels with different oxidizers, specifically bio-fuels such as paraffin-based fuels. These fuels are treated as non-toxic and non-explosive; and can generate a high value of heat with different oxidizers 4,[9][10][11][12][13][14] since they have relatively high value of the heat of combustion. One of the important advantages of paraffin-based fuels is their low melting temperature and low latent heat of melting and evaporation, that dramatically simplifies the conversion of the solid fuel into liquid and gas phase.…”

Section: Introductionmentioning

confidence: 99%

“…Research was performed by several universities and corporations, such as Scaled Composites, Sierra Nevada Space Systems, XCOR Aerospace, and others to develop a safer and dependable combination of hybrid rocket fuels and oxidizers. Considerable work on the combustion of paraffin-based fuels was done by researchers from Stanford University, who proposed a set of relationships for the calculation of regression rates of the combustion of paraffin-based fuels 4,[9][10][11][12][13][14] . One such regression rate formula obtained for the combustion of paraffin and oxygen for oxidizer to fuel ratios from 1.7 to 2.3 is as follows 9 :…”

Section: Introductionmentioning

confidence: 99%

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Hybrid Propellant Rocket Engine Test Fixture and Research on the Combustion of Non-Conventional Fuels

Naoumov

Haralambous

Goldreich

et al. 2013

51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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This paper introduces the first step of the research performed by the Central Connecticut State University faculty/student research team on the combustion of nonconventional fuels in a small-scale Hybrid Propellant Rocket Engine (HPRE). The long-term goal of the research was to investigate the combustion of non-conventional bio-derived fuels such as beeswax, lard, with different oxidizers (oxygen, hydrogen peroxide, nitrous oxide) along with additives such as aluminum powder; and to obtain approximation formulas for the calculation of regression rates for listed propellants and propellants with additives. A small-scale HPRE, test fixture and instrumentation system have been designed, manufactured and assembled. To validate proper operation of the engine, test facility and instrumentation system, the first tests focused primarily on the combustion of paraffin and bee's wax with oxygen. Initial experiments were performed; experimental data were collected and followed by comparison with theoretical data, calculated using computer code, created by authors. The approximation formulas for the calculation of the regression rates of the paraffin with oxygen were obtained and compared with existing data of other researchers. Nomenclature T-Thrust, N e u -Velocity of combustion products at nozzle exit, m/s e A -Exit area of the nozzle, m 2 e p -Pressure at the exit of the nozzle, pa P -Pressure in the combustion chamber, psig a p -Ambient pressure, pa  -Molar oxidizer-to-fuel ratio K -Mass oxidizer-to-fuel ratio st K -Stoichiometric mass oxidizer-to-fuel ratio i b -Number of atoms of an element, , in a chemical compound i  -Valence of an element, i in a chemical compound j  -Molar mass of chemical compound, j, kg/kmol f m  -Mass flow rate of fuel, kg/s ox m  -Mass flow rate of oxidizer, kg/s 1 Professor,

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Section: Tests Results Numerical Simulation and Data Analysismentioning

confidence: 91%

Section: Tests Results Numerical Simulation and Data Analysismentioning

confidence: 98%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Hybrid Propellant Rocket Engine Test Fixture and Research on the Combustion of Non-Conventional Fuels

Naoumov

Haralambous

Goldreich

et al. 2013

51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

View full text Add to dashboard Cite

show abstract

“…Research worldwide is dedicated to addressing these problems and has made great progresses. Bernard et al proposed a one-dimensional nonsteady flow predictive performance model for N 2 O/paraffin HRMs and proved the efficiency by comparing the proposed model with hot-fire test data [2]. A regression rate model for a mixed oxidizer hybrid motor, whose grains are lightly oxidized, was proposed using a linear combination of traditional regression rate equations, and tests were conducted to determine the best coefficients for the presumed models [3].…”

Section: Introductionmentioning

confidence: 99%

Design Optimization and Parameter Analysis of a Hybrid Rocket Motor-Powered Small LEO Launch Vehicle

Zhu

Wang

et al. 2021

International Journal of Aerospace Engineering

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In this paper, the effects of different grain shapes of a hybrid rocket motor (HRM) and different payload mass/orbit heights on the design of small launch vehicles (SLVs) are systematically discussed. An integrated overall design model for the hybrid rocket motor-powered small launch vehicle (HPSLV) is established, and two groups of three-stage SLVs capable of sending small payloads to the low earth orbit (LEO) are designed and optimized. In the first group, the SLVs with different grain shapes and different numbers of chambers in HRMs at the 1st and the 2nd stages are optimized and analyzed. In the second group, the SLVs capable of sending different payload mass to different orbit heights are optimized and analyzed. Pareto graphs of the design results show that the design of HRM at the 1st stage has the greatest impact on the take-off mass, total velocity increment, and maximum axial overload of the SLV. Self-organizing maps show that the take-off mass, maximum diameter, overall length, and velocity increment of the SLVs have the same variation tendency. For the 1-chamber HRM at the 1st stage, the wheel-shaped grain is better than circle-shaped and star-shaped grains in terms of reducing the total mass and length of the SLV, and the 4-chamber parallel HRM has more advantages over all 1-chamber designs for the same reason. The theoretical velocity increments are calculated by the Tsiolkovsky formula, and the actual velocity increments are obtained based on the trajectory simulation data. The results indicate that the HPSLV has a regular distribution in terms of the ratio of theoretical (actual) velocity increments at three different stages, and the estimated distribution ratio is around 1 : 1.55 : 1.69 (1 : 1.9 : 2.39), which can provide some reference for future development of HPSLV.

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Preparation of Paraffin-Based Solid Combustible for Hybrid Propulsion Rocket Motor

Cardoso¹,

Ferrão²,

Kawachi³

et al. 2017

Journal of Propulsion and Power

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Performance Modeling of a Paraffin Wax / Nitrous Oxide Hybrid Rocket Motor

Cited by 23 publications

References 4 publications

Hybrid Propellant Rocket Engine Test Fixture and Research on the Combustion of Non-Conventional Fuels

Hybrid Propellant Rocket Engine Test Fixture and Research on the Combustion of Non-Conventional Fuels

Design Optimization and Parameter Analysis of a Hybrid Rocket Motor-Powered Small LEO Launch Vehicle

Preparation of Paraffin-Based Solid Combustible for Hybrid Propulsion Rocket Motor

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