Experimental evaluation of HTPB/paraffin fuel blends for hybrid rocket applications

Thomas, James C.; Paravan, Christian; Stahl, Jacob; Tykol, Andrew J.; Rodriguez, Felix A.; Galfetti, L.; Petersen, Eric L.

doi:10.1016/j.combustflame.2021.02.032

Cited by 27 publications

(8 citation statements)

References 36 publications

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“…The re-ignition ability of paraffin-based fuel can be characterised by understanding the melting behavior under reheating conditions. Since the stability of the liquid melt layer formed over the fuel surface is directly related to the melting temperature of the fuel [41]. The low melting temperature of fuel can degrade a large amount of fuel into the combustion zone.…”

Section: Thermal Characterizationmentioning

confidence: 99%

Combustion performance of hybrid rocket fuels loaded with MgB2 and carbon black additives

Pal

Palateerdham

Mahottamananda

et al. 2023

Propulsion and Power Research

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Section: Thermal Characterizationmentioning

confidence: 99%

Combustion performance of hybrid rocket fuels loaded with MgB2 and carbon black additives

Pal

Palateerdham

Mahottamananda

et al. 2023

Propulsion and Power Research

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“…First principles modelling of the combustion of plain HTPB, plain paraffin, and mixed-fuel systems are discussed in the paper. [1] Adam Okninski (2021) carried out a study on hybrid rocket propulsion technology for space transportation. Paraffin is especially popular with LOX and N2O as oxidizers.…”

Section: Literature Reviewmentioning

confidence: 99%

Comparative Study on Hybrid Rocket Fuels for Space Launch Vehicles Moving in Higher Orbits

Bandyopadhyay¹,

Mishra²

2022

jame

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The current research is focused on understanding the propulsive parameters of hybrid rocket motors. A comparative study is prepared from various research papers. The fuels paraffin wax, hydroxyl-terminated polybutadiene (HTPB) and polymethyl methacrylate (PMMA) with added additives (Al/Mg) were combined with two oxidizers, liquid oxygen (LOX), nitrous oxide (N2O). The propulsive parameters examined were the combustion efficiency, combustion or adiabatic flame temperature, characteristics velocity and regression rate. The propellant pair paraffin-N2O provided the highest performance for all parameters studied. This study provides an advantageous propellant option for future rocket propulsion based on a comparative investigation

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“…Several studies have investigated diverse fuels used in hybrid rocket engines, including HTPB. Many studies refer to different fuels used in hybrid racket engines, including HTPB (hydroxyl-terminated polybutadiene)/paraffin [13], mixtures with varying concentrations of crystalline wax and paraffin wax, PolyEthylene wax, High-Density PolyEthylene, Poly-Methyl MethAcrylate (PMMA) fuel grains, and sorbitol [14,15]. To enhance the performance of hybrid rocket engines, various additives are developed, as their performance is generally lower compared to liquid fuel engines.…”

Section: Introductionmentioning

confidence: 99%

Experimental Research into an Innovative Green Propellant Based on Paraffin–Stearic Acid and Coal for Hybrid Rocket Engines

Cican,

Paraschiv,

Buturache

et al. 2024

Inventions

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This study focuses on an innovative green propellant based on paraffin, stearic acid, and coal, used in hybrid rocket engines. Additionally, lab-scale firing tests were conducted using a hybrid rocket motor with gaseous oxygen as the oxidizer, utilizing paraffin-based fuels containing stearic acid and coal. The mechanical performance results revealed that the addition of stearic acid and coal improved the mechanical properties of paraffin-based fuel, including tensile, compression, and flexural strength, under both ambient and sub-zero temperatures (−21 °C). Macrostructural and microstructural examinations, conducted through optical and scanning electron microscopy (SEM), highlighted its resilience, despite minimal imperfections such as impurities and micro-voids. These characteristics could be attributed to factors such as raw material composition and the manufacturing process. Following the mechanical tests, the second stage involved conducting a firing test on a hybrid rocket motor using the new propellant and gaseous oxygen. A numerical simulation was carried out using ProPEP software to identify the optimal oxidant-to-fuel ratio for the maximum specific impulse. Following simulations, it was observed that the specific impulse for the paraffin and for the new propellant differs very little at each oxidant-to-fuel (O/F) ratio. It is noticeable that the maximum specific impulse is achieved for both propellants around the O/F value of 2.2. It was observed that no hazardous substances were present, unlike in traditional solid propellants based on ammonium perchlorate or aluminum. Consequently, there are no traces of chlorine, ammonia, or aluminum-based compounds after combustion. The resulting components for the simulated motor include H2, H2O, O2, CO2, CO, and other combinations in insignificant percentages. It is worth noting that the CO concentration decreases with an increase in the O/F ratio for both propellants, and the differences between concentrations are negligible. Additionally, the CO2 concentration peaks at an O/F ratio of around 4.7. The test proceeded under normal conditions, without compromising the integrity of the test stand and the motor. These findings position the developed propellant as a promising candidate for applications in low-temperature hybrid rocket technology and pave the way for future advancements.

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Experimental evaluation of HTPB/paraffin fuel blends for hybrid rocket applications

Cited by 27 publications

References 36 publications

Combustion performance of hybrid rocket fuels loaded with MgB2 and carbon black additives

Combustion performance of hybrid rocket fuels loaded with MgB2 and carbon black additives

Comparative Study on Hybrid Rocket Fuels for Space Launch Vehicles Moving in Higher Orbits

Experimental Research into an Innovative Green Propellant Based on Paraffin–Stearic Acid and Coal for Hybrid Rocket Engines

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