The present invention relates to improved rocket engine systems. In one embodiment, an improved rocket engine system includes a propellant source, at least one power source, at least one power source motor, a rocket engine, and at least one pump. The improved rocket engine system may further include
The present invention relates to improved rocket engine systems. In one embodiment, an improved rocket engine system includes a propellant source, at least one power source, at least one power source motor, a rocket engine, and at least one pump. The improved rocket engine system may further include at least one of the following: at least one controller, at least one propellant valve, and a propellant pressurizing source.
대표청구항▼
1. A rocket engine system comprising: a propellant source comprising at least one of a fuel source and an oxidizer source;at least one electric power source for propulsion comprising a plurality of individually-separated, electric power source entities for propulsion;an ejection fixture configured t
1. A rocket engine system comprising: a propellant source comprising at least one of a fuel source and an oxidizer source;at least one electric power source for propulsion comprising a plurality of individually-separated, electric power source entities for propulsion;an ejection fixture configured to jettison at least one of said plurality of individually-separated, electric power source entities from said rocket engine system;at least one electric motor in operative communication with said at least one electric power source for propulsion;a rocket engine; andat least one pump,wherein at least one of said at least one pump is in operative communication with a corresponding electric motor of said at least one electric motor,wherein at least one of said at least one pump is in operative communication with said rocket engine,wherein said propellant source is used to cool and enhance heat rejection from said at least one electric motor where said at least one electric motor is in communication with said propellant source and operating at a temperature of said propellant source,wherein said at least one electric motor is submerged in a propellant source fluid flow, andwherein at least one of said at least one pump is in operative communication with said propellant source whereby at least one of said at least one pump is able to supply said propellant source to said rocket engine. 2. The rocket engine system according to claim 1, wherein said fuel source is selected from the group consisting of a liquid fuel, a solid fuel, a gaseous fuel, and any combination thereof, and wherein said oxidizer source is selected from the group consisting of a liquid oxidizer, a solid oxidizer, a gaseous oxidizer, and any combination thereof. 3. The rocket engine system according to claim 1, wherein said plurality of individually-separated, electric power source entities for propulsion is a plurality of batteries. 4. The rocket engine system according to claim 1, wherein said at least one pump is a turbo pump. 5. The rocket engine system according to claim 1, wherein said at least one pump consists of two pumps that are mechanically connected to one another. 6. The rocket engine system according to claim 1, further comprising at least one controller, wherein at least one of said at least one controller is located between a corresponding electric power source for propulsion of said at least one electric power source for propulsion and a corresponding electric motor of said at least one electric motor. 7. The rocket engine system according to claim 1, further comprising at least one propellant valve, wherein at least one of said at least one propellant valve is located between said propellant source and a corresponding pump of said at least one pump. 8. The rocket engine system according to claim 1, further comprising a first controller, a second controller, a first propellant valve, and a second propellant valve, wherein said at least one electric power source for propulsion is a first electric power source for propulsion and a second electric power source for propulsion, wherein said at least one electric motor is a first electric motor and a second electric motor,wherein each of said first electric motor and said second electric motor is in operative communication with a corresponding electric power source for propulsion of said first electric power source for propulsion and a second electric power source for propulsion,wherein said at least one pump is a first pump and a second pump, wherein each of said first pump and said second pump is in operative communication with a corresponding electric motor of said first electric motor and a second electric motor,wherein each of said first pump and said second pump is in operative communication with said rocket engine, andwherein each of said first pump and said second pump is in operative communication with said propellant source whereby each of said first pump and said second pump is able to supply said propellant source to said rocket engine, wherein each of said first controller and said second controller is located between a corresponding electric power source for propulsion of said first electric power source for propulsion and a second electric power source for propulsion and a corresponding electric motor of said first electric motor and a second electric motor, andwherein each of said first propellant valve and said second propellant valve is located between said propellant source and a corresponding pump of said first pump and said second pump. 9. The rocket engine system according to claim 8, wherein said plurality of individually-separated, electric power source entities for propulsion are selected from the group consisting of a plurality of batteries, a plurality of fuel cells, a plurality of solar cells, a plurality of capacitor sources, a plurality of generators, and any combination thereof. 10. The rocket engine system according to claim 8, wherein said plurality of individually-separated, electric power source entities for propulsion are a plurality of batteries. 11. The rocket engine system according to claim 10, wherein said plurality of batteries are separated into modules. 12. A rocket engine system comprising: a propellant source;at least one electric power source for propulsion;at least one electric motor in operative communication with said at least one electric power source for propulsion, wherein said at least one electric motor is in thermal communication with said propellant source;a rocket engine; andat least one pump, wherein at least one of said at least one pump is in operative communication with a corresponding electric motor of said at least one electric motor, wherein at least one of said at least one pump is in operative communication with said rocket engine,wherein at least one of said at least one pump is in operative communication with said propellant source whereby at least one of said at least one pump is able to supply said propellant source to said rocket engine, and wherein said at least one electric motor is submerged in a propellant source fluid.
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이 특허에 인용된 특허 (8)
Terry M. Abel ; Thomas A. Velez, Electrical drive system for rocket engine propellant pumps.
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