The present disclosure generally pertains to a rocket propulsion oxidizer compound that is a solution, is a homogenous and stable liquid at room temperature and includes nitrous oxide and nitrogen tetroxide. In addition, an apparatus is provided for burning a fuel and nitrous oxide/nitrogen tetroxid
The present disclosure generally pertains to a rocket propulsion oxidizer compound that is a solution, is a homogenous and stable liquid at room temperature and includes nitrous oxide and nitrogen tetroxide. In addition, an apparatus is provided for burning a fuel and nitrous oxide/nitrogen tetroxide. The apparatus has a combustor, a catalyst, a nitrous oxide/nitrogen tetroxide supply passage for directing the nitrous oxide/nitrogen tetroxide to a contact position with the catalyst, and a fuel supply passage for supplying the fuel to the combustor. The catalyst acts to facilitate decomposition of the nitrous oxide/nitrogen tetroxide, while the combustor burns the fuel, the decomposed nitrous oxide/nitrogen tetroxide and/or nitrous oxide/nitrogen tetroxide decomposed in the reaction.
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1. A fluid combustion system comprising: a liquid oxidizer solution for use in a rocket propulsion system comprising nitrous oxide dissolved into nitrogen tetroxide that is a homogenous and stable liquid at room temperature,a hydrocarbon fuel that is a homogenous and stable liquid at room temperatur
1. A fluid combustion system comprising: a liquid oxidizer solution for use in a rocket propulsion system comprising nitrous oxide dissolved into nitrogen tetroxide that is a homogenous and stable liquid at room temperature,a hydrocarbon fuel that is a homogenous and stable liquid at room temperature, the hydrocarbon fuel containing a catalyst that is capable of causing a catalytic decomposition of at least one of the nitrous oxide and the nitrogen tetroxide and thereby creating sufficient heat to facilitate autoignition of the hydrocarbon fuel, andat least one additive having a theoretical specific energy greater than that of said nitrous oxide. 2. The fuel combustion system of claim 1, wherein said at least one additive is an earth-storable oxidizer. 3. The fuel combustion system of claim 1, wherein said liquid is non-viscous at room temperature. 4. The fuel combustion system of claim 1, wherein said liquid is a gel at room temperature. 5. The fluid combustion system of claim 1 comprising: the oxidizer solution for use in a rocket propulsion system comprising a homogenous solution that includes nitrous oxide and approximately 28 to 52 weight percent nitrogen tetroxide,the hydrocarbon fuel that is a homogenous and stable liquid at room temperature, the hydrocarbon fuel containing a catalyst that is capable of causing a catalytic decomposition of at least one of the nitrous oxide and the nitrogen tetroxide, wherein the oxidizer solution is combined with the liquid hydrocarbon fuel containing the oxidizer catalyst capable of creating sufficient heat from a catalytic decomposition of the oxidizer solution to facilitate autoignition of the hydrocarbon fuel, andat least one additive having a theoretical specific energy greater than that of said nitrous oxide. 6. The fuel combustion system of claim 5, wherein said solution is a non-viscous liquid at room temperature. 7. The fuel combustion system of claim 5, wherein said solution is a gel at room temperature. 8. The fuel combustion system of claim 1 wherein the hydrocarbon fuel is propane. 9. The fuel combustion system of claim 1 wherein the catalyst is selected from the group consisting of platinum, rhodium, tungsten carbine, copper, cobalt and gold. 10. The fuel combustion system of claim 5 wherein the hydrocarbon fuel is propane. 11. The fuel combustion system of claim 5 wherein the oxidizer catalyst is selected from the group consisting of platinum, rhodium, tungsten carbine, copper, cobalt and gold. 12. An fuel combustion system for use in a rocket propulsion system comprising: an oxidizer component that is a homogenous and stable liquid at room temperature including nitrous oxide dissolved into nitrogen tetroxide, anda fuel component that is a homogenous and stable liquid at room temperature including a hydrocarbon fuel and a catalyst, andat least one additive having a theoretical specific energy greater than that of said nitrous oxidewherein, following contacting the oxidizer component with the fuel component, the oxidizer solution further includes an amount of heat generated at least in part by an interaction of the catalyst with the oxidizer component that is sufficient to cause autoignition of the hydrocarbon fuel. 13. The fuel combustion system according to claim 12 wherein the oxidizer component includes between 35% and 65% (molar ratio) nitrogen tetroxide. 14. The fuel combustion system according to claim 13, wherein the at least one additive includes an earth-storable oxidizer that has a specific energy greater than that of nitrous oxide. 15. The fuel combustion system according to claim 1 wherein the oxidizer component includes between 35% and 65% (molar ratio) nitrogen tetroxide. 16. The fuel combustion system according to claim 15, wherein the at least one additive includes an earth-storable oxidizer that has a specific energy greater than that of nitrous oxide. 17. The fuel combustion system according to claim 5 wherein the oxidizer component includes between 35% and 65% (molar ratio) nitrogen tetroxide. 18. The fuel combustion system according to claim 17, wherein the at least one additive includes an earth-storable oxidizer that has a specific energy greater than that of nitrous oxide. 19. The fuel combustion system of claim 5, wherein said at least one additive is an earth-storable oxidizer. 20. The fuel combustion system of claim 12, wherein said at least one additive is an earth-storable oxidizer.
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이 특허에 인용된 특허 (2)
Herdy, Jr., Joseph Roger, Burning nitrous oxide and a fuel.
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