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

Pal, Yash; Palateerdham, Sasi Kiran; Mahottamananda, Sri Nithya; Sivakumar, S.; Ingenito, Antonella

doi:10.1016/j.jppr.2022.11.003

Cited by 11 publications

(16 citation statements)

References 44 publications

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“…One of the main concerns with paraffin-based fuels is their poor mechanical characteristics. Thus, the addition of additives to enhance the mechanical performance of paraffin for use in hybrid rocket engines represents an open field [3,35]. The limitations of paraffinbased fuel for hybrid rockets necessitate an exploration of additives to improve regression rates without compromising mechanical properties [30,35].…”

Section: Discussionmentioning

confidence: 99%

“…Thus, the addition of additives to enhance the mechanical performance of paraffin for use in hybrid rocket engines represents an open field [3,35]. The limitations of paraffinbased fuel for hybrid rockets necessitate an exploration of additives to improve regression rates without compromising mechanical properties [30,35]. This study investigates the mechanical and microstructural aspects of the novel paraffin-based propellant in comparison with pure paraffin, both before and after exposure to negative temperatures.…”

Section: Discussionmentioning

confidence: 99%

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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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Section: Discussionmentioning

confidence: 99%

Section: Discussionmentioning

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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“…where f is a friction factor. The solid-gas phase transition is modeled by the source term Ω = f ( ṁox ) [kg/(m 3 s)], defined by the so-called regression function of solid fuel mass loss due to reaction with the oxidant [9,10]. Based on previous work [11,12], it can be assumed that after leaving the tank, the two-phase (liquidvapor) oxidant mixture in the form of nitrous oxide expands and finally enters the combustion chamber in gaseous form.…”

Section: Mathematical Modelmentioning

confidence: 99%

“…where an individual heat capacities can be estimated basing on NASA polynomials [14]. By differentiating the equation of state (9) the following expression:…”

Section: Mathematical Modelmentioning

confidence: 99%

Quasi-Stationary Mathematical Model of Hybrid Rocket Engine Combustion Chamber

Wardach-Święcicka,

Kardaś

2024

Topical Problems of Fluid Mechanics 2024

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This paper presents a quasi-stationary one-dimensional mathematical model of the combustion chamber of a hybrid rocket engine. The model is based on stationary balance equations, considering time-varying input parameters. It makes it possible to quickly estimate the variability of parameters such as pressure, velocity, or temperature of gases inside the combustion chamber during engine operation. In addition, the assumption of a global paraffin oxidation reaction in nitrous oxide allows the determination of the composition of the exhaust gases. The results are consistent with numerical data from other researchers available in the literature.

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“…An innovative penetrative combustion mechanism, capable of affecting regression rate, was noticed during the combustion of low-packing density grains. Yash Pala, et al, aimed to increase the performance characteristics of paraffin-based fuel by using magnesium diboride (MgB2) and carbon black (CB) additives [15]. The mechanical performance results revealed that adding CB and MgB2 improved the ultimate strength and elastic modulus of the fuel, while thermal stability improved the thermal stability of the paraffin matrix.…”

Section: A Solid Propellantmentioning

confidence: 99%

Review on Sustainable Development of Space Vehicles

Wishwakarma¹,

Dingore²

2023

IJRASET

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As humanity is moving towards becoming a multi-planetary civilization, it is very important to make efficient use of resources available on our planet first and then head towards exploiting the resources of another celestial body. It is also important to cause minimum harm to the space environment around our planet as well as the planetary atmosphere. Advancement in conventional rocket fuel is one of the ways to optimize the consumption of fuel during a space launch but it cannot always be feasible. Finding cheaper alternatives like Biofuels can also be a significant point of discussion. Such fuels can be naturally obtained without much harm to the environment and they can be as effective as conventional rocket fuel. For complete sustainability, not only internal changes but also external changes should be considered. To attain space sustainability, we need to follow a technology-driven approach while considering the cost and effective management of the space missions. This paper is a review of various techniques involved in the sustainable development of space vehicles, and effects of existing techniques involved during the launch of the space vehicle.

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

Cited by 11 publications

References 44 publications

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

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

Quasi-Stationary Mathematical Model of Hybrid Rocket Engine Combustion Chamber

Review on Sustainable Development of Space Vehicles

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