First Steps In The Development And Testing Of Nontoxic, Bioderived Fuels For Hybrid Rocket Motors

Lyne, James Evans; Naoumov, Viatcheslav; Scoles, Josh; Dodge, Meghan; Elton, Ben; Wozniak, Paul R.; Austin, David; Combs, Cliff

doi:10.2514/6.2005-741

Cited by 14 publications

(7 citation statements)

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“…It should be taken into account that Putnam's data were obtained for the bees wax combustion, but at the same time all properties of the bees wax are close to the properties of paraffin 15,16 , which make reasonable a comparison of data obtained from paraffin and bees wax combustion. As follows from Figures 36-40, our regression rate curves are located "between" Karabeyoglu's and Putnam's curves.…”

Section: Tests Results Numerical Simulation and Data Analysismentioning

confidence: 90%

“…29 and 30 and formulas (15) and (16) Figure 31 shows the attempt to combine the results of the approximation of regression rates versus propellant mass flow rate for both inner diameters of the grains, but demonstrates considerably lower R 2 value compared to Fig. 29 and 30.…”

Section: Tests Results Numerical Simulation and Data Analysismentioning

confidence: 98%

“…They also explored lard as a bio-derived fuel, which has similar qualities of low melting temperature and latent heat of melting [15][16][17][18][19] . The regression rate formulas were obtained for combustion of bee's wax with oxygen as a function of average mass flux of oxidizer through the grain port, average mass flux of the propellant through the grain port, average pressure in the combustion chamber, and mass flow rate of oxidizer 15 …”

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: 90%

Section: Tests Results Numerical Simulation and Data Analysismentioning

confidence: 98%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

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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“…In parallel and in response to the aforementioned progression of technological maturation of paraffin as a highperforming hybrid rocket propellant, non-conventional, bio-derived hybrid rocket fuels have also been investigated, including lard, tallow, edible oils, and beeswax. Early work in this area conducted by Lyne et al identified beeswax as a promising area of research focus due to its combination of regression rate and mechanical stability as compared to softer bio-derived fuels [10]. This work was followed by numerous others at multiple research institutions, a detailed review of which follows and suggests that further investigation into beeswax as a high-performing hybrid rocket fuel is merited.…”

Section: Fig 2 Progressing Complexity Of Experimental Environments Used To Simulate Various Gravitational and Thermal Environments Of Intmentioning

confidence: 99%

Centrifugal Casting of Paraffin and Beeswax for Hybrid Rockets

Stober

Sanchez

Wanyiri

et al. 2020

AIAA Propulsion and Energy 2020 Forum

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A high-level research framework is presented which seeks to navigate the barriers associated with reusing wax phase change material onboard a satellite as a hybrid rocket fuel for de-orbit or other in-space propulsion needs, while also conducting fundamental studies of the fluid mechanics and heat transfer phenomena which drive the cooling and solidification of wax within a horizontal rotating cylinder in various gravitational and thermal environments. A detailed review of past work in the area of beeswax fuel for hybrid chemical propulsion is reported and served to motivate consideration of this fuel for centrifugal casting efforts, due to previously reported values of regression rate comparable to that of paraffin wax. The production process of beeswax fuel from beekeeping detritus was perfected and documented. Analysis of the shrinkage of beeswax and the neat Candlewic FR5560 paraffin wax used herein determined a volume shrinkage percentage during liquid to solid phase transition of 18.7 ± 0.62 and 13.3 ± 0.22%, respectively. An image analysis routine was developed in order to automate the process of determining the instantaneous solidification rate for each one-second timestep through the centrifugal casting process of paraffin and beeswax fuel grain sizes common for small-scale hybrid rockets. Beeswax completed solidification in 22% less time than paraffin under identical conditions but exhibited more coning of resulting solid wax. Calculated time-and space-averaged solidification rates for paraffin and beeswax were 0.017 and 0.028 mm/s, respectively, within a 50.8 mm inner diameter, 57.15 mm outer diameter, and 254 mm length polycarbonate tube. Careful analysis, however, shows that instantaneous solidification rate increases very slightly but steadily over time for both paraffin and beeswax, though the rate increase is greater for beeswax. The image analysis routine was most effective when applied to the beeswax solidification process as compared to that of paraffin, as the solid/liquid interface is considerably more salient in beeswax due to a distinct color change upon solidification. Dye will be used with paraffin casting in the future with the goal of improving solid/liquid phase contrast.

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“…These fuels have similar low melting temperatures and latent heats of melting [11][12][13][14] . The regression rate formulas obtained by Putnam for the combustion of bee's wax with oxygen, which can be represented as a function of average mass flux of oxidizer through the grain port, average mass flux of the propellant through the grain port, average pressure in the combustion chamber, and mass flow rate of oxidizer are shown below: 11-14 : Research on the combustion of bio-derived fuels remains very difficult and time consuming.…”

Section: Introductionmentioning

confidence: 99%

Undergraduate Research on Peculiarities of the Combustion of Ecologically Clean Paraffin Wax Fuels in Hybrid Propellant Rocket Engines

Naoumov

Masoud

Skomin

et al. 2015

53rd AIAA Aerospace Sciences Meeting

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The paper describes the student-faculty research of the combustion of non-conventional bio-derived fuels in a lab-scale Hybrid Propellant Rocket Engine (HPRE). The long-term goal of the senior capstone project is to study specific features of combustion of nonconventional bio-derived hybrid propellant rocket fuels such as paraffin, beeswax, and lard, which are non-toxic and non-explosive with different oxidizers. Combustion of above fuels with additives (aluminum powder) was studied as well. The study was concentrated on the obtaining of regression rates (velocities of the combustion) for the listed propellants, and investigating losses of melted unburned bio-derived fuels. Such fuels could replace conventional toxic and explosive fuels, and are planned to be used on the NASA sounding rockets. A lab-scale HPRE, test fixture and instrumentation system have been designed, manufactured, assembled and used for the research and analysis of combustion. More than 60 tests were performed to study the specific features of combustion using paraffin and bee's wax. The results of the study were presented at 51 st AIAA Meeting and Exhibits, and SciTech, 52 nd Aerospace Sciences Meeting. This paper summarizes 2013/14 research results on the combustion of paraffin and paraffin with aluminum powder; represents new findings, such as regression rate formulas for paraffin wax combustion with 10% of aluminum powder obtained for two different diameters of the grain ports; the paper also illuminates the study of the losses of unburned paraffin wax and discusses novel methodology of the prediction of losses of unburned fuel based on the measurements of the temperature of the exhaust plum of combustion products. 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 k -Mass oxidizer-to-fuel ratio st k -Stoichiometric mass oxidizer-to-fuel ratio 1 Professor, 2 Figure 1. Simplified diagram of HPRE Figure 2. Simplified schematic of the combustion in HPRE 2 R -Gas constant sp I -Specific impulse m/s or s f m  -Mass flow rate of fuel, kg/s ox m  -Mass flow rate of oxidizer, kg/s p m  -Mass flow rate of propellant, kg/s f G -Average mass flux of fuel through the grain port, g/cm 2 s ox G -Average mass flux of oxidizer through the grain port, g/cm 2 s p G -Average mass flux of propellant through the grain port, g/cm 2 s i A -Cross-sectional area of injector, m 2 a -Jet coefficient m u -Velocity on the axis of the plume of the combustion products, m/s  r -Regression rate, mm/s in d -Initial port diameter (before fuel burnout), cm fin d -Final port diameter (after fuel burnout), cm * A -Nozzle throat area, m 2  -Specific heat ratio

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First Steps In The Development And Testing Of Nontoxic, Bioderived Fuels For Hybrid Rocket Motors

Cited by 14 publications

References 1 publication

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

Centrifugal Casting of Paraffin and Beeswax for Hybrid Rockets

Undergraduate Research on Peculiarities of the Combustion of Ecologically Clean Paraffin Wax Fuels in Hybrid Propellant Rocket Engines

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