Design of Multiport Grain with Hydrogen Peroxide Hybrid Rocket

Ahn, Byeonguk; Kang, Han‐Young; Lee, Eun Kwang; Yun, Yongtae; Kwon, Sejin

doi:10.2514/1.b36949

Cited by 25 publications

(8 citation statements)

References 27 publications

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“…The fuel composition of FGSPs may be radially designed using energetic additives and/or by adapting fuel/binder volume-fraction, to achieve target ballistic performance and thrust profile for the mission. Likewise, the grain geometry and port(s) may also be altered to achieve the mission requirements, as in [5,[39][40][41]. Further, FGSPs also offer bolstered sustainability towards the flight inertial loads, radial combustion pressure, thrust, and temperature loads.…”

Section: Local Regression Analysismentioning

confidence: 99%

Ballistic and thermomechanical characterisation of paraffin-based hybrid rocket fuels loaded with light metal hydrides

Akhter

Hassan

2021

Acta Astronautica

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Section: Local Regression Analysismentioning

confidence: 99%

Ballistic and thermomechanical characterisation of paraffin-based hybrid rocket fuels loaded with light metal hydrides

Akhter

Hassan

2021

Acta Astronautica

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“…Different kinds of silica, carbon, and alumina are possible candidates as a catalyst support, but gamma phase alumina was ultimately selected, as it has not only a high enough surface area for a catalyst reaction but also durability in the high-pressure and -temperature environment. In addition, it has reliability and good compatibility with the active material as reported [10,11,18,22,66,73,81,87].…”

mentioning

confidence: 79%

“…Storability of this green propellant has been dramatically improved since its first major use as a propellant in the 1950s [17]. As a result, a large body of research advocates the use of H 2 O 2 as a propellant for propulsion systems [10,11,[18][19][20][21]. However, there are still challenges with regards to the longterm storability of H 2 O 2 and even the effect of the stabilizing agents on H 2 O 2 propulsion performance is an issue as described in [22].…”

Section: Introductionmentioning

confidence: 99%

“…In regard to the catalyst active material to effect hydrogen peroxide decomposition, there are various options, such as platinum [19,[76][77][78][79][80][81][82], iridium [20], ferrous chloride [83], silver [84][85][86], and manganese dioxide [10,11,18,22,66,73,81,87]. In this study, manganese dioxide was chosen as the active material, because it has exhibited high decomposition efficiency for hydrogen peroxide, and it is relatively easily fabricated at low cost.…”

mentioning

confidence: 99%

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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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“…c* efficiency exceeding 97% is possible for non-metalized fuels. [57] provides data of tests of 90% HTP and PE fuel, where characteristic velocity was between 93.4% + / − 1.5% and 99.6% + / − 1.6% of its theoretical value, where the higher range was obtained for a 14-port grain design and a corresponding increase in the combustion chamber pressure and a decrease in oxidizer-to-fuel ratio. Values of 72-89% combustion efficiencies for 90% HTP and highly metalized fuels can be found in [58].…”

Section: Introductionmentioning

confidence: 99%

Development of Green Storable Hybrid Rocket Propulsion Technology Using 98% Hydrogen Peroxide as Oxidizer

et al. 2021

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This paper presents the development of indigenous hybrid rocket technology, using 98% hydrogen peroxide as an oxidizer. Consecutive steps are presented, which started with interest in hydrogen peroxide and the development of technology to obtain High Test Peroxide, finally allowing concentrations of up to 99.99% to be obtained in-house. Hydrogen peroxide of 98% concentration (mass-wise) was selected as the workhorse for further space propulsion and space transportation developments. Over the course nearly 10 years of the technology’s evolution, the Lukasiewicz Research Network—Institute of Aviation completed hundreds of subscale hybrid rocket motor and component tests. In 2017, the Institute presented the first vehicle in the world to have demonstrated in-flight utilization for 98% hydrogen peroxide. This was achieved by the ILR-33 AMBER suborbital rocket, which utilizes a hybrid rocket propulsion as the main stage. Since then, three successful consecutive flights of the vehicle have been performed, and flights to the Von Karman Line are planned. The hybrid rocket technology developments are described. Advances in hybrid fuel technology are shown, including the testing of fuel grains. Theoretical studies and sizing of hybrid propulsion systems for spacecraft, sounding rockets and small launch vehicles have been performed, and planned further developments are discussed.

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Design of Multiport Grain with Hydrogen Peroxide Hybrid Rocket

Cited by 25 publications

References 27 publications

Ballistic and thermomechanical characterisation of paraffin-based hybrid rocket fuels loaded with light metal hydrides

Ballistic and thermomechanical characterisation of paraffin-based hybrid rocket fuels loaded with light metal hydrides

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

Development of Green Storable Hybrid Rocket Propulsion Technology Using 98% Hydrogen Peroxide as Oxidizer

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