Performance Characteristics of Hydrogen Peroxide/Kerosene Staged-Bipropellant Engine with Axial Fuel Injector

Jo, Sungkwon; An, Sungyong; Kim, Jonghak; Yoon, Ho-Sung; Kwon, Sejin

doi:10.2514/1.b34083

Cited by 32 publications

(7 citation statements)

References 12 publications

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“…Therefore, the autoignition of a blended fuel using hot oxygen is possible. The possibility of autoigniting decomposed hydrogen peroxide was verified by Jo et al using kerosene as a fuel [5]. Therefore, the feasibility of blended hydrogen peroxide was evaluated in this research.…”

Section: Introductionmentioning

confidence: 84%

Evaluation of Ethanol-Blended Hydrogen Peroxide Monopropellant on a 10 N Class Thruster

Lee

Kwon

2013

Journal of Propulsion and Power

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The evaluation of an ethanol blended hydrogen peroxide monopropellant thruster was carried out. The specific impulse of hydrogen peroxide was increased by blending it with ethanol. Ethanol was selected because it presented no significant problem in terms of storability. An oxidizer-to-fuel ratio of 50 was selected considering the thermal characteristics of the material used and the higher specific impulse that was obtained in comparison to the theoretical specific impulse of hydrogen peroxide. For the thruster material, 316L stainless steel was chosen based on compatibility test results and other considerations. Barium hexaaluminate was used as a catalyst support because the chamber temperature increased owing to the combustion of ethanol. The surface area of barium hexaaluminate was approximately six times higher than that of alumina after heating at 1200°C. Platinum and manganese oxide with lead oxide catalysts were evaluated on a 10 N class thruster and the catalyst capacity, specific impulse, and efficiency characteristic velocity were almost similar. However, the fluctuation of the chamber pressure increased in the case of manganese oxide with lead oxide catalyst. The decomposition performance of both catalysts showed no remarkable difference, but the platinum catalyst was more reliable.Nomenclature C 1 = initial mass fraction of hydrogen peroxide L = characteristic length, m W 1 = mass of propellant before storability test, g W 2 = mass of propellant after storability test, g η C = C efficiency, % η Temp = temperature efficiency, %

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Section: Introductionmentioning

confidence: 84%

Evaluation of Ethanol-Blended Hydrogen Peroxide Monopropellant on a 10 N Class Thruster

Lee

Kwon

2013

Journal of Propulsion and Power

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“…In this system, the storage vessels are pressurized by the slowly controlled nitrogen gas; this increases pressure in the storage vessels of hydrogen peroxide and Kerosene. The hydrogen peroxide passes through a catalyst (manganese oxide, metallic silver, rhodium, palladium, platinum or gold) for self-decomposition and to enhance the performance of the thruster [10]. For this study, the catalyst chosen is manganese oxide (MnO 2 ) as a result of its availability and lower cost as compared to the others.…”

Section: Propellant Mechanism Overviewmentioning

confidence: 99%

Numerical Analysis and Modelling of a 100 N Hypergolic Liquid Bipropellant Thruster

Ngwu¹,

Ugheoke²,

Yusuf³

et al. 2020

AAST

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This study focuses on the stepwise procedure involved in the development of a numerical model of a bi-propellant hypergolic chemical propulsion system using key features and performance characteristics of existing and planned (near future) propulsion systems. The study targets specific impulse of 100 N delivery performance of thrust chambers which is suitable for primary propulsion and attitude control for spacecraft. Results from numerical models are reported and validated with the Rocket Propulsion Analysis (RPA) computation concept. In the modelling process, there was proper consideration for the essential parts of the thruster engine such as the nozzle, combustion chamber, catalyst bed, injector, and cooling jacket. This propulsion system is designed to be fabricated in our next step in advancing this idea, using a combination of additive manufacturing technology and commercial off the shelf (COTS) parts along with non-toxic propellants. The two non-toxic propellants being considered are Hydrogen Peroxide as the oxidiser and Kerosene as the fuel, thus making it a low-cost, readily available and environmentally-friendly option for future microsatellite missions.

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“…Therefore, it is suitable only for maneuvers with a small ΔV, but it has other characteristics that make it versatile even though it is a very toxic propellant. H 2 O 2 ∕kerosene rockets also have been researched and developed by some universities in the world including Korea [18][19][20][21]. Research into the use of H 2 O 2 as a propellant has been restarted recently because it is nontoxic, storable, and autoignitable with kerosene [19].…”

Section: A Jimentioning

confidence: 99%

“…Park tested autoignition characteristics of kerosene with decomposed H 2 O 2 for rocket-based combined-cycle engines [18]. Jo et al designed and tested 1000-N-class H 2 O 2 ∕kerosene bipropellant rockets using the autoignition capability for an igniter [19,20]. The TRL is low, but it is better than the other rocket types considering its overall characteristics.…”

Section: A Jimentioning

confidence: 99%

Requirements Analysis of Propulsion Systems for Lunar-Exploration Mission

Moon

Jang

Park

et al. 2013

Journal of Spacecraft and Rockets

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Requirements of a propulsion system for lunar-exploration missions using a launch vehicle, the development of which has recently started in Korea, were conceptualized. A new three-stage-to-orbit launch system, the Korea Space Launch Vehicle 2 will be a middle-class launch vehicle in that its expected payload capacity to low Earth orbit will be about 2.6 tons. The Korea Space Launch Vehicle 2 is under development and may possibly launch a lunar orbiter and a lander within 10-15 years. Considering some of the limitations and requirements a new space-propulsion system must be developed, and it has been found that a H 2 O 2 ∕kerosene-bipropellant rocket is the optimum propulsion system among several types of chemical rockets. The optimum thrust and burn-time requirements for orbital transfers and landing using H 2 O 2 ∕kerosene-bipropellant rockets were also derived by mass budget design and three-degree-of-freedom orbit-trajectory calculations. It has been found that, using the Korea Space Launch Vehicle 2, 1800 N-class H 2 O 2 ∕kerosene-bipropellant propulsion system with a continuous burn time of more than 340 s and an accumulated burn time of more than 710 s needs to be developed for the lunar-exploration missions.

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Performance Characteristics of Hydrogen Peroxide/Kerosene Staged-Bipropellant Engine with Axial Fuel Injector

Cited by 32 publications

References 12 publications

Evaluation of Ethanol-Blended Hydrogen Peroxide Monopropellant on a 10 N Class Thruster

Evaluation of Ethanol-Blended Hydrogen Peroxide Monopropellant on a 10 N Class Thruster

Numerical Analysis and Modelling of a 100 N Hypergolic Liquid Bipropellant Thruster

Requirements Analysis of Propulsion Systems for Lunar-Exploration Mission

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