Design, Optimization, and Launch of a 3" Diameter N2O/Aluminized Paraffin Rocket

McCormick, A.W.; Hultgren, Eric; Lichtman, Martin; Smith, J. O.; Sneed, Ryan C.; Azimi, S.

doi:10.2514/6.2005-4095

Cited by 17 publications

(7 citation statements)

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“…Recently, it was developed in Stanford University and in the Ames-NASA Research Center, both in the USA, a new paraffinbased fuel whose regression rate is approximately three times higher than conventional hybrid fuels (Karabeyoglu et al, 2003a(Karabeyoglu et al, ,b, 2004. Promising results were obtained by several researchers (Brown and Lydon, 2005;Karabeyoglu et al, 2004;Santos et al, 2005;McCormick et al, 2005;Authors, 2006;Authors, 2007) using paraffin with different oxidizers -liquid oxygen (LOX), gaseous oxygen (GOX), nitrous oxide (N 2 O) and hydrogen peroxide (H 2 O 2 ).…”

Section: Introductionmentioning

confidence: 99%

Preliminary analysis of hybrid rockets for launching nanosats into LEO

Costa¹,

Vieira²

2010

J. Braz. Soc. Mech. Sci. & Eng.

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This work determines the preliminary mass distribution of hybrid rockets using 98% H2O2 and solid paraffin mixed with aluminum as propellants. An iterative process is used tocalculate the rocket performance characteristics and to determine the inert mass fractionfrom given initial conditions. It is considered a mission to place a 20 kg payload into a 300 km circular equatorial orbit by air launched and ground launched hybrid rockets usingthree stages. The results indicate total initial masses of about 7800 kg for a groundlaunched hybrid rocket and 4700 kg for an air launched hybrid rocket

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Section: Introductionmentioning

confidence: 99%

Preliminary analysis of hybrid rockets for launching nanosats into LEO

Costa¹,

Vieira²

2010

J. Braz. Soc. Mech. Sci. & Eng.

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“…In addition, because less oxidizer is required to burn a comparable volume of aluminized fuel grain compared to pure paraffin wax fuel grain, the oxidizerfuel ratio is lowered, allowing for the design of a more compact rocket. According to Stanford University research, a 40% aluminized paraffin wax/nitrous oxide propellant has a 25% higher rate of regression than plain paraffin wax [16]. Besides, due to its relatively high heat of oxidation, high density, and ease of ignition, aluminum is the most researched additive for solid fuel formulations.…”

Section: Aluminiummentioning

confidence: 99%

Metals and Alloys Additives as Enhancer for Rocket Propulsion: A Review

Ismail

Nordin

Azami

et al. 2021

ARFMTS

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A rocket's engine usually uses fuel and oxygen as propellants to increase the rocket's projection during launch. Nowadays, metallic ingredients are commonly used in the rocket’s operation to increase its performance. Metallic ingredients have a high energy density, flame temperature, and regression rate that are important factors in the propulsion process. There is a wide range of additives have been reported so far as catalysts for rocket propulsion. The studies show that the presence of metal additives improves the regression rate, specific impulse and combustion efficiency. Herein, the common energetic additives for rocket propulsion such as metal and light metals are reviewed. Besides the effect of these energetic particles on the regression behaviors of base (hybrid) fuel has been exclusively discussed. This paper also proposed a new alloy namely high entropy alloys (HEAs) as a new energetic additive that can potentially increase the performance of the rocket propellant system.

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“…Most researches considered metal additives in polymeric-based solid fuels [6,8,9,27,[41][42][43][44][45]. More recently, metal additives in paraffin-based fuels have also been considered [8,[46][47][48][49][50].…”

Section: Particle Additives In Solid Fuelsmentioning

confidence: 99%

Approaches to Low Fuel Regression Rate in Hybrid Rocket Engines

Pastrone

2012

International Journal of Aerospace Engineering

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Hybrid rocket engines are promising propulsion systems which present appealing features such as safety, low cost, and environmental friendliness. On the other hand, certain issues hamper the development hoped for. The present paper discusses approaches addressing improvements to one of the most important among these issues: low fuel regression rate. To highlight the consequence of such an issue and to better understand the concepts proposed, fundamentals are summarized. Two approaches are presented (multiport grain and high mixture ratio) which aim at reducing negative effects without enhancing regression rate. Furthermore, fuel material changes and nonconventional geometries of grain and/or injector are presented as methods to increase fuel regression rate. Although most of these approaches are still at the laboratory or concept scale, many of them are promising.

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Design, Optimization, and Launch of a 3" Diameter N2O/Aluminized Paraffin Rocket

Cited by 17 publications

References 0 publications

Preliminary analysis of hybrid rockets for launching nanosats into LEO

Preliminary analysis of hybrid rockets for launching nanosats into LEO

Metals and Alloys Additives as Enhancer for Rocket Propulsion: A Review

Approaches to Low Fuel Regression Rate in Hybrid Rocket Engines

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