Ignition of Hydrogen Peroxide with Gel Hydrocarbon Fuels

Connell, Terrence L.; Risha, Grant A.; Yetter, Richard A.; Natan, Benveniste

doi:10.2514/1.b36458

Cited by 24 publications

(7 citation statements)

References 26 publications

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“…In the study of Connell et al, experimental counter flow and impinging jet studies and modeling analysis of hypergolic hydrogen peroxide (H 2 O 2 ) have been considered. Moreover, tests including gel hydrocarbon fuel/particle mixtures have been conducted to characterize the condensed phase reaction rates and ignition delay times [27]. The mixtures consisted of n-dodecane, n-heptane, and kerosene containing fumed silica and sodium borohydride (NaBH 4 ) particles.…”

Section: Hypergolic Systems With Hydrogen Peroxide Oxidizermentioning

confidence: 99%

“…Consistent with fuel volatility trends, elevating the reactant temperature reduced the ignition delay. Modeling results have indicated that the ignition process relies upon the reaction between NaBH 4 and H 2 O 2 in order to gasify and heat an ignition kernel to the H 2 O 2 ∕fuel mixture auto ignition temperature [27].…”

Section: Hypergolic Systems With Hydrogen Peroxide Oxidizermentioning

confidence: 99%

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Hypergolic Systems based on Hydrogen Peroxide Oxidizer

Türker

2023

EJCS

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Hydrogen peroxide, H2O2, is a promising and nontoxic oxidant. In recent years considerable attention has been paid to the development of hypergolic system compositions, because the use of them not only markedly simplifies the engine design and rocket system operation but also provides the possibility of their repeated use. Moreover, their high performance, high environmental compatibility and low toxicity make them highly preferable. The present review considers recent works on hypergolic systems involving hydrogen peroxide as the oxidizer and various green propellants of organic and inorganic nature with or without certain additives.

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Section: Hypergolic Systems With Hydrogen Peroxide Oxidizermentioning

confidence: 99%

Section: Hypergolic Systems With Hydrogen Peroxide Oxidizermentioning

confidence: 99%

Hypergolic Systems based on Hydrogen Peroxide Oxidizer

Türker

2023

EJCS

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“…Drop-on-drop tests exhibited that this kind of gelled kerosene is hypergolic with hydrogen peroxide as shown in a sequence of photographs in Figure 9. Total ignition delay time was 8 ms. Connell et al [50][51][52] also investigated the issue and showed that it is feasible.…”

Section: Comparable Bipropellant Rocket Propulsion System 31 Overviewmentioning

confidence: 99%

Green Comparable Alternatives of Hydrazines-Based Monopropellant and Bipropellant Rocket Systems

Hasan¹,

Grinstein²,

Kuznetsov³

et al. 2019

Aerospace Engineering

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Concepts are presented for "green" (with reduced hazards) replacements for monopropellant hydrazine propulsion systems and for hypergolic bipropellant systems while maintaining similar performance. At the onset of the "green propulsion" age, "green" alternatives to hydrazine propulsion have been emerging. The introduction rate of these into space systems is very slow due to the conservatism of the space propulsion industry. The concept presented here for monopropellant hydrazine systems offers gradual conversion to "green propellants" by dual capability of conventional hydrazine systems and ammonium dinitramide (ADN)-based systems. An initial risk reduction program has been carried out for materializing the concept. It includes proof of concept of dual use of all propulsion system parts. Materials compatibility and actual operation have been demonstrated. For bipropellants, we present the emerging "green" hypergolic system based on kerosene and peroxide, similar in performance to MMH/N 2 O 4 . Results of the proof-of-concept and development model systems are presented. The experimental results of various engine types demonstrate the capability to operate in both pulse and steady-state modes and the ability to produce different thrust levels. The fuel and oxidizer show very robust hypergolicity and short ignition delay times, as well as characteristic velocity efficiency exceeding 98%.

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“…For the hypergolic gel propellant combination, a catalyst or hypergolic substance for hydrogen peroxide has been introduced to the fuel gelation process, which is attracting significant interest among several research groups [24,[31][32][33][34]. Connell et al [27,34] fabricated and tested gel hydrocarbon fuels such as n-dodecane, n-heptane, and kerosene with particle mixtures including sodium borohydride (NaBH 4 ), which is a hypergolic material with hydrogen peroxide, and investigated the ignition delay characteristics of the H 2 O 2 /fuel mixture. Shoaib et al [31,33] prepared alcohol family fuels such as ethanol, propanol, butanol, pentanol, hexanol, and heptanol, which were then gelled with organic gelling agent propyl cellulose and featured hypergolic additives and hydrogen peroxide.…”

Section: Design Of the Propulsion Systemmentioning

confidence: 99%

“…Today, gelation technology attracts much interest [23][24][25][26][27][28][29][30][31] for its potential to increase enthalpy using metal particles as additives, deliver greater stability, and increase storability in respect of liquid propellants. The gel propellant has increasing viscosity at a decreased shear rate in a storage, which can contribute to the storability of hydrogen peroxide as well.…”

Section: Introductionmentioning

confidence: 99%

Preliminary Assessment of Hydrogen Peroxide Gel as an Oxidizer in a Catalyst Ignited Hybrid Thruster

Huh

Jyoti

Yun

et al. 2018

International Journal of Aerospace Engineering

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In regard to propulsion system applications, the stability of liquid propellants in long-term storage is of increasing importance, and this had led to a greater interest in gelation technology. As part of a preliminary test to determine the feasibility of using a gel propellant in a rocket with a catalyst bed, a hybrid rocket with a catalyst reactor using a gel propellant as an oxidizer was tested for the first time in this study. Experiments were conducted with two different oxidizers: one with liquid phase hydrogen peroxide and the other with gel phase hydrogen peroxide, as well as high-density polyethylene as fuel for a 250 N class hybrid thruster performance test. The thruster was designed with the catalyst ignition system, and a catalyst was manufactured to be inserted into the catalyst reactor to facilitate oxidizer decomposition. While the test result with neat hydrogen peroxide indicated sufficient decomposition efficiency using a manganese dioxide/alumina catalyst and successful autoignition of the fuel via the decomposed product, gel hydrogen peroxide exhibited insufficient decomposition and there were difficulties in operating the thruster as a part of the catalyst was covered in the gelling agent. This preliminary study identifies the potential challenges of using a gel phase oxidizer in a catalyst ignited hybrid thruster and discusses the technical issues that should be addressed in regard to a gel propellant hybrid thruster design with a catalyst reactor.

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Ignition of Hydrogen Peroxide with Gel Hydrocarbon Fuels

Cited by 24 publications

References 26 publications

Hypergolic Systems based on Hydrogen Peroxide Oxidizer

Hypergolic Systems based on Hydrogen Peroxide Oxidizer

Green Comparable Alternatives of Hydrazines-Based Monopropellant and Bipropellant Rocket Systems

Preliminary Assessment of Hydrogen Peroxide Gel as an Oxidizer in a Catalyst Ignited Hybrid Thruster

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