Study of the Combustion of Pure Bio-Derived Fuels and Bio-Derived Fuels with Additives in Hybrid Propellant Rocket Engine

Naoumov, Viatcheslav; Masoud, Nidal Al; Sherman, K. M.; Doolittle, Matthew; Ziegler, Matthew M.; Thorne, D. J.

doi:10.2514/6.2017-0833

Cited by 8 publications

(5 citation statements)

References 9 publications

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“…Karabeyoglu et al (2004) achieved a regression rate in the range of 0.5–2 mm/s at an oxidizer mass flux of 50–150 kg/m 2 s using paraffin/oxygen. Naoumov et al (2017) attained performance of palm-based fuels paraffin, with a range of regression rate 0.5 to +1 mm/s at 70–140 kg/m 2 s and beeswax 0.6–1.4 mm/s at 45–145 kg/m 2 s oxidizer flux.…”

Section: Resultsmentioning

confidence: 93%

“…Beeswax tested with oxygen and nitrous oxide showed the highest regression rate three times as high as hydroxyl-terminated polybutadiene and liquid oxygen, paraffin and oxygen combinations (Putnam, 2007). A laboratory hybrid rocket motor using polymethyl methacrylate, polyethene, paraffin, beeswax fuel grains with gaseous oxygen and found beeswax performance was the highest among all other combinations (Makled and Al-Tamimi, 2017; Naoumov et al , 2017).…”

Section: Introductionmentioning

confidence: 99%

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Regression rate performance of paraffin wax and bees wax –Gox with varied grain configuration in a hybrid rocket motor

Saravanan

Shanmugam

Veerappan

2021

AEAT

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Purpose This paper aims to determine the regression rate using wax fuels for three different grain configurations and find a suitable grain port design for hybrid rocket application. Design/methodology/approach The design methodology of this work includes different grain port designs and subsequent selection of solid fuels for a suitable hybrid rocket application. A square, a cylindrical and a five-point star grained were designed and prepared using paraffin and beeswax fuels. They were tested in a laboratory-scale rocket with gaseous oxygen to study the effectiveness of solid fuels on these grain structures. The regression rate by static fire testing of these wax fuels was analyzed. Findings Beeswax performance is better than that of paraffin wax fuel for all three designs, and the five-slotted star fuel port grain attained the best performance. Beeswax fuel attained an average regression rate ≈of 1.35 mm/s as a function of oxidizer mass flux Gox ≈ 111.8 kg/m2 s and for paraffin wax 1.199 mm/s at Gox ≈ 121 kg/m2 s with gaseous oxygen. The local regression rates of fuels increased in the range of 0.93–1.194 mm/s at oxidizer mass flux range of 98–131 kg/m2 s for cylindrical grain, 0.99–1.21 mm/s at oxidizer mass flux range of 96–129 kg/m2s for square grain and 1.12–1.35 mm/s at oxidizer mass flux range of 91–126 kg/m2 s for a star grain. A complete set of the regression rate formulas is obtained for all three-grain designs as a function of oxidizer flux rate. Research limitations/implications The experiment has been performed for a lower chamber pressure up to 10 bar. Originality/value Different grain configurations were designed according to the required dimension of the combustion chamber, injector and exhaust nozzle of the design of a lab-scale hybrid rocket, and input parameters were selected and analyzed.

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Section: Resultsmentioning

confidence: 93%

Section: Introductionmentioning

confidence: 99%

Regression rate performance of paraffin wax and bees wax –Gox with varied grain configuration in a hybrid rocket motor

Saravanan

Shanmugam

Veerappan

2021

AEAT

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“…The field of beeswax-fueled hybrid chemical propulsion is considerably underdeveloped compared to paraffin. An extensive search of literature related to beeswax hybrid rocket fuels yields a series of initial studies at the University of Tennessee, Knoxville culminating in two postgraduate theses [10,34,35], a series of annual senior design projects at Central Connecticut State University [36][37][38][39][40][41][42][43][44], and the lone peer reviewed article in the field of beeswax propulsion by the Egyptian Space Technology Centre [45]. Most of these works generally investigated a broad range of bioderived hybrid rocket fuels, but beeswax consistently proved most practical as a hybrid rocket fuel.…”

Section: B Beeswax 1) Evaluation As a Hybrid Rocket Fuelmentioning

confidence: 99%

“…A series of studies by Naoumov et al from 2013 to 2020 attempted to establish regression rate comparisons between paraffin, beeswax, and each of these with up to 10% micron-sized aluminum powder added for fuel grain port diameters of 12.7, 25.4, and 38.1 mm at combustion chamber pressures of 0.448 to 0.965 MPa [36][37][38][39][40][41][42][43][44]. Over 150 hot fires were conducted with gaseous oxygen alongside theoretical thermodynamic calculations which showed (1) little influence of aluminum addition on regression rate, (2) experimentally-determined regression rates of beeswax above those for paraffin reported by Karabeyoglu [3] but below those for beeswax reported by Putnam [35] at similar conditions; namely, oxidizer mass fluxes between 0.7 and 1.75 g/cm 2 s. Experimental efforts in these studies were plagued with low oxidizer mass flow rates (0.5-0.95 equivalence ratios), though in the most recent work attempts at increasing the mass flow rate of gaseous oxygen proved successful [44].…”

Section: B Beeswax 1) Evaluation As a Hybrid Rocket Fuelmentioning

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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“…Hybrid rocket engines combine solid fuel with a liquid or gas oxidizer. This type of rocket propulsion is attractive and provides many advantages over conventional liquid or solid rocket propulsion systems due to their low-cost, fuel handling simplicity, durability, throttling capability, and eco-friendly attributes [2][3][4][5][6][7][8]. It is easy to throttle the hybrid rocket engines by adjusting the oxidizer mass flow rate, which serves as ideal candidates for adjustable thrust rocket and is appropriate for all applications where rockets are used [9][10][11][12].…”

Section: Introductionmentioning

confidence: 99%

Modelling of Hybrid Rocket Flow-Fields with Computational Fluid Dynamics

Ismail

Rozainuddin

Nordin

et al. 2022

CFDL

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A low regression rate is a major limitation in the hybrid rocket propulsion system. This paper is to study the regression rate characteristics of a cylindrical solid grain with cryogenic propellants. Paraffin (P) fuel is coupled with two types of oxidizers, namely gaseous oxygen (GOX) and nitrous oxide (N2O). ANSYS software is used as the CFD platform to observe the hybrid rocket flow-fields. The modelling values obtained from the pressure, temperature, velocity, and wall heat flux contours are used to calculate the hybrid rocket performance in terms of regression rate, thrust, specific impulse, characteristic velocity, and exit Mach number. The numerical results show that the mass-flow-inlet boundary conditions, initial design feature, and type of propellant play an important role in the enhancement of hybrid rocket performance. Result shows that enhanced of 68 % of the regression rate, 59 % of thrust, 6 % of specific impulse and exit Mach number, and % of characteristic velocity by improved 50% of mass flow rate. Due to the high flame temperature, the GOX/P propellants produce the best hybrid rocket motor compared with the others.

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Study of the Combustion of Pure Bio-Derived Fuels and Bio-Derived Fuels with Additives in Hybrid Propellant Rocket Engine

Cited by 8 publications

References 9 publications

Regression rate performance of paraffin wax and bees wax –Gox with varied grain configuration in a hybrid rocket motor

Regression rate performance of paraffin wax and bees wax –Gox with varied grain configuration in a hybrid rocket motor

Centrifugal Casting of Paraffin and Beeswax for Hybrid Rockets

Modelling of Hybrid Rocket Flow-Fields with Computational Fluid Dynamics

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