Granted Patent B2

US 12,510,337 · App. 17/756,548 · Granted Dec 30, 2025

Inventors: Andrew Lapsa (Seattle, WA); Thomas Feldman (Kent, WA)

F42B15/34

Abstract

Claims (50)

1 . An upper stage rocket of a multi-stage rocket system, the upper stage rocket comprising:

a forward end;

an aft end opposite the forward end;

a propulsion engine at the aft end;

an actively-cooled heat shield system including:

a heat shield at the aft end and defining a windward side of the upper stage rocket during travel of the upper stage rocket in an atmospheric re-entry trajectory;

a tank onboard the upper stage rocket, the tank configured to store a coolant;

a pump onboard the upper stage rocket, the pump configured to receive the coolant from the tank and output a pressurized coolant;

a heat exchanger onboard the upper stage rocket, the heat exchanger integrally connected with the heat shield and configured to receive the pressurized coolant from the pump, transfer heat from the heat shield to the pressurized coolant to generate a heated fluid, and output the heated fluid;

a turbine onboard the upper stage rocket, the turbine including:

an inlet configured to receive the heated fluid output from the heat exchanger;

a shaft coupled to the pump and including turbine blades mounted thereon, the shaft configured to rotate and thereby power the pump when the heated fluid received from the heat exchanger acts on the turbine blades; and

an outlet configured to output the heated fluid.

2 . The upper stage rocket of claim 1 , wherein at least the heat exchanger, the turbine, and the pump are configured such that, once operation of the pump is started, an amount of energy supplied to the turbine from the heat exchanger is alone sufficient to continue operation of the pump.

3 . The upper stage rocket of claim 1 , wherein the heat shield is configured to be exposed to a high Mach number flow environment during normal operation.

4 . The upper stage rocket of claim 1 , wherein the heat shield system and the propulsion engine share a multi-purpose component; and

wherein the multi-purpose component is at least one of the heat shield, the tank, the pump, the heat exchanger, and the turbine.

5 . The upper stage rocket of claim 4 , wherein the pump of the heat shield system is a fuel pump of the propulsion engine.

6 . The upper stage rocket of claim 1 , further comprising an exhaust conduit through which at least a portion of the heated fluid output from the turbine exits the upper stage rocket.

7 . The upper stage rocket of claim 1 , wherein the coolant is at least one of an active coolant, a liquid coolant, and a cryogenic coolant.

8 . The upper stage rocket of claim 1 , wherein the heated fluid is at least one of a gas and a supercritical fluid.

9 . The upper stage rocket of claim 1 , wherein the heat shield system further includes:

a primary heated fluid conduit configured to transfer the heated fluid from the heat exchanger to the inlet of the turbine; and

a bypass conduit configured to bypass, from at least a portion of the primary heated fluid conduit, an excess of energy in the heated fluid for power use by an auxiliary system.

10 . The upper stage rocket of claim 9 , wherein the auxiliary system is a tank.

11 . The upper stage rocket of claim 9 , wherein the auxiliary system is a gas thruster.

12 . The upper stage rocket of claim 9 , wherein the auxiliary system is a transpiration cooling system.

13 . The upper stage rocket of claim 9 , wherein the auxiliary system is an auxiliary power unit (APU).

14 . The upper stage rocket of claim 1 , further comprising an exhaust conduit through which at least a portion of the heated fluid output from the turbine exits the upper stage rocket; and

wherein the exhaust conduit is at the aft end of the upper stage rocket.

15 . The upper stage rocket of claim 1 , wherein the pump of the heat shield system is a fuel pump of the propulsion engine; and

wherein the heat shield system further includes:

a primary heated fluid conduit configured to transfer the heated fluid from the heat exchanger to the inlet of the turbine; and

a bypass conduit configured to bypass, from at least a portion of the primary heated fluid conduit, an excess of energy in the heated fluid for power use by an auxiliary system.

16 . The upper stage rocket of claim 1 , wherein the heat shield system and the propulsion engine share at least one multi-purpose component; and

wherein the at least one multi-purpose component is the tank.

17 . The upper stage rocket of claim 1 , wherein the coolant is at least one of an active coolant, a liquid coolant, and a cryogenic coolant; and

wherein the heated fluid is at least one of a gas and a supercritical fluid.

18 . The upper stage rocket of claim 1 , further comprising an exhaust conduit at the aft end of the upper stage rocket through which at least a portion of the heated fluid output from the turbine exits the upper stage rocket;

wherein the pump of the heat shield system is a fuel pump of the propulsion engine; and

wherein the heat shield system further includes:

a primary heated fluid conduit configured to transfer the heated fluid from the heat exchanger to the inlet of the turbine; and

a bypass conduit configured to bypass, from at least a portion of the primary heated fluid conduit, an excess of energy in the heated fluid for power use by an auxiliary system.

19 . A method for actively cooling a windward side of an upper stage rocket of a multi-stage rocket system during atmospheric re-entry, comprising:

initiating driving of a pump onboard the upper stage rocket to initiate output of a pressurized coolant from the pump;

flowing the pressurized coolant output by the pump through a heat exchanger integrally connected with a heat shield that defines at least a portion of the windward side of the upper stage rocket;

transferring heat from the heat shield to the pressurized coolant to generate a heated fluid;

inputting the heated fluid to a turbine onboard the upper stage rocket, the turbine including a shaft coupled to the pump and turbine blades mounted to the shaft; and

exposing the turbine blades to the heated fluid to drive the shaft and thereby continue driving the pump.

20 . The method of claim 19 , wherein the transferring and inputting steps supply an amount of energy to the turbine that is alone sufficient to continue driving the pump.

Assignments (2)

Continuity (2)

References Cited (96)