Patent ID: 11920543
Assignee: RADIAN AEROSPACE INC.
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  B | IPC B  F

Claim 5:
6. A rocket propulsion system, comprising
a combustion chamber; and
a propellant injector coupled to the combustion chamber, and including:
an oxidizer inlet;
an oxidizer distributor in fluid communication with the oxidizer inlet;
a fuel inlet;
a fuel distributor in fluid communication with the fuel inlet;
a fuel piston movably positioned between the fuel inlet and the fuel distributor; and
an oxidizer piston movably positioned between the oxidizer inlet and the oxidizer distributor, and positioned to open an oxidizer flow path between the oxidizer inlet and the oxidizer distributor before the fuel piston opens a fuel flow path between the fuel inlet and the fuel distributor, wherein the fuel piston and the oxidizer piston are nested relative to each other;

wherein the oxidizer piston includes an oxidizer piston wall around an oxidizer passageway in fluid communication with the oxidizer distributor and the oxidizer inlet, the oxidizer piston wall comprises a fuel piston channel extending within the oxidizer piston wall, and the fuel piston is movable within the fuel piston channel.