In the framework of the PulCheR project, an experimental test campaign on a 40 N bipropellant thruster prototype has been carried out with the aim of assessing the attainable propulsive performance in steady state conditions of 98% concentration hydrogen peroxide and propyne. The preliminary atmospheric tests without the combustion chamber on the selected liquid/liquid coaxial injectors show the lack of the hypergolicity of the innovative propellant combination when injected in liquid phase at ambient temperature and the ignitability of the mixture when the decomposition of propyne is promoted by a spark plug. In the final tests on the bipropellant prototype, the tested ignition device has not been able to start the combustion and, therefore, the experimental propulsive performance has not been assessed.

PROPULSIVE PERFORMANCE OF A C3H4/H2O2 ROCKET PROTOTYPE FOR FUTURE GREEN BIPROPELLANT THRUSTERS

Angelo, Pasini
Primo
;
Giovanni, Pace
Secondo
;
2015-01-01

Abstract

In the framework of the PulCheR project, an experimental test campaign on a 40 N bipropellant thruster prototype has been carried out with the aim of assessing the attainable propulsive performance in steady state conditions of 98% concentration hydrogen peroxide and propyne. The preliminary atmospheric tests without the combustion chamber on the selected liquid/liquid coaxial injectors show the lack of the hypergolicity of the innovative propellant combination when injected in liquid phase at ambient temperature and the ignitability of the mixture when the decomposition of propyne is promoted by a spark plug. In the final tests on the bipropellant prototype, the tested ignition device has not been able to start the combustion and, therefore, the experimental propulsive performance has not been assessed.
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Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11568/891783
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