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The propellant combustion process in the micro-chamber of the microthruster has been visually observed.
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For composite propellants, solid-phase thermal conduction is one of the dominant processes of propellant combustion and influences their burning characteristics.
This investigation analyses three finite-rate chemistry mechanisms of 2, 4 and 6 steps to simulate the combustion process in hybrid propellant rockets of HTPB-based (solid fuel) and gaseous oxygen.
In this work, direct measurements of the pressure variation and projectile velocity with multiple chamber geometries on the combustion process of bulk-loaded liquid propellant are performed using quartz pressure transducer and timing device.
combustion: stagesStages of the combustion process.
The redesign emphasized improving the combustion process.
The Heterogeneous Quasi One-dimensional (HeQu1-D) model for AP/HTPB composite propellant combustion is extended to aluminized propellants.
A micro-scale rocket consists of a combustion chamber containing the propellant, a converging and a diverging part to accelerate the gas generated by the propellant combustion.
The model takes into account solid propellant combustion, heat losses, and gas phase chemical reactions.
The reactions in the condensed phase (mainly the ADN decomposition reaction) control ADN/HTPB propellant combustion.
The linearized Denison Baum solid propellant combustion model is characterized by two parameters (α, A).
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