Demonstration of 2,500 N-class H<sub>2</sub>O<sub>2</sub>/HDPE Hybrid Rocket for Lab-scale Sounding Rocket

Yun, Yongtae; Huh, Jin Woo; Kim, Young-il; Kang, Shinjae; Heo, Seonuk; Kwon, Sejin

doi:10.2514/6.2018-4526

Cited by 3 publications

(6 citation statements)

References 14 publications

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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%

“…propellant is used, it was not intended to bring about a higher chamber pressure than typical of these small-scale propulsion systems [11,67,69]. As a result, it was determined to have 20 bar in this work.…”

Section: International Journal Of Aerospace Engineeringmentioning

confidence: 99%

“…There is a hybrid rocket which is economical, safe, and reliable, and it is an attractive choice for space propulsion as it has the advantages of both solid and liquid rocket propulsion systems. Many previous hybrid rocket applications [8][9][10][11][12][13][14][15][16], from lab-based sounding rockets to spaceships, demonstrate their advantages.…”

Section: Introductionmentioning

confidence: 99%

“…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.…”

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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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mentioning

confidence: 79%

Section: International Journal Of Aerospace Engineeringmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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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A practical design approach for a single-stage sounding rocket to reach a target altitude

Huh

Kwon

2022

Aeronaut. j.

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A new type of design domain for a sounding rocket is suggested in this study, which is more intuitive, simplified, and conducive to a single-stage sounding rocket development process. Among the various operation parameters, this study identifies several effective variables, which are also among the most practical in a sounding rocket design process. Of the many design variables considered for peak altitude optimisation, arguably the three most effective in shaping the whole system and conferring the most practicality in the design process of a sounding rocket were determined. A simulation-based study was conducted to establish: the effect of the selected parameters on flight performance, and the optimum design conditions of a single-stage sounding rocket in terms of its peak altitude. The simulation result was compared with randomly chosen experimentally tested flight data and validated. With the clear performance curves varying depending on the variables, the combination of the considered design inputs was effective. The new type of design domain and design procedure proposed is expected to constitute a useful reference and deliver practical benefits to the development process for a target-altitude-optimised single-stage sounding rocket.

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Hydrogen Peroxide Decomposition Catalysts Used in Rocket Engines

et al. 2020

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Demonstration of 2,500 N-class H₂O₂/HDPE Hybrid Rocket for Lab-scale Sounding Rocket

Cited by 3 publications

References 14 publications

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

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

A practical design approach for a single-stage sounding rocket to reach a target altitude

Hydrogen Peroxide Decomposition Catalysts Used in Rocket Engines

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Demonstration of 2,500 N-class H2O2/HDPE Hybrid Rocket for Lab-scale Sounding Rocket

Cited by 3 publications

References 14 publications

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

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

A practical design approach for a single-stage sounding rocket to reach a target altitude

Hydrogen Peroxide Decomposition Catalysts Used in Rocket Engines

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Product

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Demonstration of 2,500 N-class H₂O₂/HDPE Hybrid Rocket for Lab-scale Sounding Rocket