Abstract
ABSTRACTIn this work, a new composition based on Paraffin wax and HTPB fuel, loaded with nanoparticles has been proposed for hybrid propulsion system. Lithium aluminium hydride (LiAlH4) and Magnesium hydride (MgH2) nanoparticles have been used as additives. A detailed rheological, thermal and ballistic characterisation has been carried out. The Magnesium hydride doped hybrid fuel exhibits lower viscosity as compared to the Lithium aluminium hydride doped one, leading to comparatively enhanced entrainment-aided combustion. LiAlH4 doped hybrid fuels also exhibit solid-like behaviour and thus greater stability in the solid phase in contrast to the MgH2 doped fuel. LiAlH4 doped fuel is thermally more stable and produces relatively greater residual-mass. The loading of nanoparticles significantly improves the fuel regression performance during ballistic firing. This can be attributed to the release of nascent hydrogen and metal nanoparticles during dehydrogenation of metal hydrides. Regression rate enhancement in the range of 350%–475% is observed in comparison to the conventional HTPB hybrid fuels. A power law governing regression rate has been proposed for the tested hybrid fuels.
Highlights
Hybrid rockets fuel offer several advantages over the conventional rocket fuel based systems
A novel hybrid rocket fuel composition has been proposed which comprises of Paraffin wax and Hydroxyl-terminated poly butadiene (HTPB) as base, blended with Lithium aluminium hydride (LiAlH4) and Magnesium hydride (MgH2) nanoparticles
It was observed that the Magnesium hydride doped hybrid fuels exhibit lower viscosity as compared to the Lithium aluminium hydride doped counterpart
Summary
Hybrid rockets fuel offer several advantages over the conventional rocket fuel based systems. It combines the benefits of both solid and liquid fuels. Advantage of hybrid fuel include reduced de-bonding and crack sensitivity, fuel insensitivity to combustion instability, and increased specific impulse (Isp) in comparison to its solid counterpart. Hybrid fuel-based rocket engines offer the possibility of throttling and on-demand thrust termination/restart. Superiority of hybrid rocket system over the liquid ones broadly includes intrinsic safety from explosion hazard due to phase-separation among propellants. Hybrid propellants demonstrate greater flexibility in fuel/oxidiser selection with minimal environmental impacts. These features make it a suitable alternative to the conventional systems for various space applications
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