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

Claim 15:
16. A rocket engine system, comprising: an oxidizer tank containing a liquid oxidizer; a catalyst having an inlet fluidly connected to the oxidizer tank and an outlet; a rocket engine having a combustion chamber extending along a longitudinal axis, the combustion chamber having a chamber inlet fluidly connected to the outlet of the catalyst for receiving a catalyzed oxidizer and a chamber outlet for outputting combustion gases; and a solid fuel within the combustion chamber, the solid fuel having a viscosity that decreases in a regression direction being parallel to the longitudinal axis, the chamber inlet located axially between the solid fuel and the chamber outlet relative to the longitudinal axis, a distribution of the viscosity of the solid fuel in the regression direction selected such that a mass flow rate of combustion gases generated by the solid fuel remains substantially constant with an increase of a volume of the combustion chamber free of the solid fuel as the solid fuel is being burned while a mass flow rate of the catalyzed oxidizer in the combustion chamber is constant as the solid fuel is being burned.