Patent ID: 9650995
Date: 2017-05-16
CPC Classifications: F02K

Claim:
1. A hybrid rocket engine comprising: a first pump powered by a first turbine; a second pump powered by a second turbine; a gas generator connected to the first pump and the second pump, wherein an output of the gas generator is connected to the first turbine and the second turbine to provide mechanical power to the first pump and the second pump; a third pump powered by a third turbine; a fourth pump powered by a fourth turbine; and a nozzle comprising an expander cycle in a wall and a combustion chamber; wherein an output of the third pump is connected to the expander cycle, and an output of the expander cycle is connected to the third turbine and the fourth turbine to provide mechanical power to the third pump and the fourth pump, and wherein an output of the fourth pump, an output of the third turbine, and an output of the fourth turbine are connected to the combustion chamber.