An Application of Commercial Grade Hydrogen Peroxide for Hybrid/Liquid Rocket Engine

Tsujikado, Nobuo; Koshimae, Masatoshi; Ishikawa, Rikiya; Kitahara, Kazuki; Ishihara, Atsushi

doi:10.2514/6.2002-3573

Cited by 13 publications

(4 citation statements)

References 1 publication

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“…Here, n represents a mole fraction of water present in the hydrogen peroxide fuel; typically, the hydrogen peroxide concentrations range 85% -90% by mass. In this propulsion design, the chemical decomposition of the hydrogen peroxide is achieved using a homogeneous catalysis approach wherein the catalyst reacts with the hydrogen peroxide in the liquid phase [9]. The resulting exothermic reaction produces high-temperature gaseous products that are subsequently passed through a converging-diverging supersonic nozzle to produce the desired thrust.…”

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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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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“…Work on HTP hybrid technology was continued in the 1990s [35]. Renewed increased interest in HTP hybrids can be seen in the 21st century and intense experimental research and development has been carried out in the last two decades in over a dozen countries worldwide, including: Australia [36], China [37], France [38], Germany [39], Italy [40], Israel [41], Japan [42], Norway [43], Poland [44], South Korea [45], Taiwan [46], the United Kingdom [47] and the United States [48]. The vacuum performance of a HTP hybrid rocket motor has been demonstrated experimentally with a combustion efficiency of approximately 98% [49].…”

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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“…The need of less toxic propellants has developed a renewed interest in using hydrogen peroxide engines. The use of hydrogen peroxide (H 2 O 2 ) as an oxidizer in bipropellant liquid rocket engines [1] as well as in hybrid rocket engines is interested [2]. The general applications of hydrogen peroxide could be fund in reusable launch vehicles and upper stages [3].…”

Section: Introductionmentioning

confidence: 99%

Multidisciplinary Design Optimization of Hydrogen Peroxide Monopropellant Propulsion System using GA and SQP

Adami¹,

Mortazavi²,

Nosratollahi³

2015

IJCA

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An intense simplification in production, storage and handling of hydrogen peroxide develop a renewed interest in hydrogen peroxide thrusters especially for low cost attitude control or orbit correction (orbit maintenance). Chemical decomposition, aerothermodynamics flow and structure demand different optimum conditions such as tank pressure, catalyst bed pressure, concentration of H 2 O 2 and geometry. These parameters play important role in propulsion system's mass and performance. Discipline conflicts are solved by Multidisciplinary Design Optimization (MDO) techniques with synchronized optimization for all subsystems respect to any criteria and limitations. In this paper, monopropellant propulsion system design optimization algorithm is presented and result of the design algorithm is validated. Results of the design algorithm have been compared with data of two different operational thrusters. According to the results, the proposed model can suitably predict total mass and performance with errors below than 10%. Then, MDO framework is proposed for the monopropellant propulsion system. Optimum propellant mass, thrust level, mass flow rate, nozzle geometry, catalyst bed length and diameter, propellant tank mass, feeding subsystem mass and total mass are derived using hybrid optimization (GA+SQP) for two space missions.

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An Application of Commercial Grade Hydrogen Peroxide for Hybrid/Liquid Rocket Engine

Cited by 13 publications

References 1 publication

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

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

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

Multidisciplinary Design Optimization of Hydrogen Peroxide Monopropellant Propulsion System using GA and SQP

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