Patent ID: 9677503
Date: 2017-06-13
CPC Classifications: B64G,F02K,F05D,Y10T

Claim:
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; and at 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, and 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.