Modelling, design &amp; thermochemical analysis of a 10 N monopropellant High Test Peroxide-HTP-thruster for space applications

Darfilal, Djamal; Mohamed, Khatir

doi:10.1109/rast.2017.8002946

Cited by 3 publications

(1 citation statement)

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“…The specific impulse (I sp ) is mostly considered as the performance of the propulsion system [1,2]. The MPT system has medium performance at low cost where the I sp is range between 130 and 280s, being developed for landing and altitude control of the spacecraft, positioning and for the Reaction Control System (RCS) of satellites that is used since 1940s to provide operations of orbit maintenance, orbit transfer and orbit correction [3][4][5][6].…”

Section: Introductionmentioning

confidence: 99%

Optimization of 10 N Monopropellant High Test Peroxide Thruster for Space Applications

Benzenine

Seladji

Darfilal³

et al. 2022

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Monopropellant thruster is one of the most propulsion system types developed in the space industry. This system uses a single type of propellant that reacts in porous medium catalytic packed bed to generate thrust in the form of hot gases. The last decade, green propellant hydrogen peroxide (H2O2), also known as High Test Peroxide (HTP), thanks to its low cost and easy to store as liquid, is used as an alternative solution of hydrazine which is very toxic and not environmentally friendly. In the current study, hydrogen peroxide monopropellant thruster is investigated for application in the future satellites. A numerical simulation is performed using the Computational Fluid Dynamics (CFD) software ANSYS Fluent in order to simulate fluid flow of hydrogen peroxide in thruster, and the finite volume method was employed for resolving the governing equation. Species transport model is applied in the single-phase reaction simulation using the Eddy Dissipation model (EDM) for turbulence-chemistry interaction. A mathematical approach based on the local thermal non-equilibrium (LTNE) model is used to describe the heat transfer through solid and fluid phases in the packed bed consisting of identical spherical silver particles. Several simulations performed allowed an optimal design of the injector, catalyst bed length and diameter and nozzle geometry, to achieve a 10N monopropellant thruster with hydrogen peroxide at 87.5% concentration.

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