Patent ID: 11952965
Assignee: LABORATOIRE REACTION DYNAMICS INC.
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  B | IPC B  F

Claim 2:
3. The rocket engine of claim 1, wherein the solid fuel includes a third solid fuel, the first solid fuel, the second solid fuel, and the third solid fuel being disks disposed in series along the longitudinal axis of the rocket engine, the first solid fuel, the second solid fuel, and the third solid fuel burning along the regression direction being parallel to the longitudinal axis, the first solid fuel located in front of the second solid fuel and the second solid fuel located in front of the third solid fuel such that the first solid fuel is burned before the second solid fuel and that the second solid fuel is burned before the third solid fuel, the third solid fuel differing from the first solid fuel and the second solid fuel by the one or more rheoloqical properties, the solid fuel having a third phase in which the first solid fuel and the second solid fuel are burned and the axial end face is defined by the third solid fuel, a third mass flow rate of combustion gases generated by the solid fuel in the third phase is equal to the second mass flow rate of combustion gases generated by the solid fuel in the second phase.