A hot-gas-generating apparatus for reacting a propellant comprises a combustion chamber, at least one injector that is arranged upstream of the combustion chamber and can be closed, on the combustion chamber side, to the propellant, electrodes being integrated in said injector, and at least one supply line for the propellant. In this context, the propellant is a monopropellant and a substantially water-free ionic solution having low vapor pressure, preferably with a residual water content of less than five percent by mass, which is capable of self-sustaining combustion at a given combustion chamber pressure, and the electrodes have at least two electrodes of opposite polarity which are suitable for electrically igniting the propellant by means of a flow of current through the propellant when this propellant flows between the opposite-polarity electrodes.
C06B 23/00 - Compositions characterised by non-explosive or non-thermic constituents
C06B 25/34 - Compositions containing a nitrated organic compound the compound being a nitrated acyclic, alicyclic or heterocyclic amine
C06B 33/12 - Compositions containing particulate metal, alloy, boron, silicon, selenium or tellurium with at least one oxygen supplying material which is either a metal oxide or a salt, organic or inorganic, capable of yielding a metal oxide the material being two or more oxygen-yielding compounds
F02K 9/42 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof using liquid or gaseous propellants
F23R 3/28 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
2.
HOT-GAS-GENERATING APPARATUS WITH IONIC MONOPROPELLANT AND LOW-VOLTAGE IGNITION
A hot-gas-generating apparatus for reacting a propellant comprises a combustion chamber, at least one injector that is arranged upstream of the combustion chamber and can be closed, on the combustion chamber side, to the propellant, electrodes (5, 6) being integrated in said injector, and at least one supply line for the propellant. In this context, the propellant is a monopropellant and a substantially water-free ionic solution having low vapor pressure, preferably with a residual water content of less than five percent by mass, which is capable of self-sustaining combustion at a given combustion chamber pressure, and the electrodes (5, 6) have at least two electrodes of opposite polarity which are suitable for electrically igniting the propellant by means of a flow of current through the propellant when this propellant flows between the opposite-polarity electrodes.
F02K 9/95 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof characterised by starting or ignition means or arrangements
patents
