Granted Patent B2

US 12,467,421 · App. 18/749,428 · Granted Nov 11, 2025

Inventors: Joel C. Sercel (Lake View Terrace, CA); Philip J. Wahl (Altadena, CA); Conrad T. Jensen (Altadena, CA); James G. Small (Sonoita, AZ); Benjamin G. Workinger (Chattanooga, TN); Samuel Daugherty-Saunders (Claremont, CA)

Assignee: Trans Astronautica Corporation

F02K9/64B64G1/401B64G1/402B64G1/446F02K9/42F02K9/44F02K9/60F03H99/00F24S20/20F24S23/30F24S23/70F24S70/16F24S2023/832

Abstract

Claims (30)

1 . A method of starting up a solar thermal rocket engine, comprising:

providing a gaseous propellant to the solar thermal rocket engine via one or more propellant channels;

introducing a liquid propellant to the solar thermal rocket engine via the one or more propellant channels; and

gradually reducing a gas-to-liquid propellant ratio provided to the solar thermal rocket engine via the one or more propellant channels to ensure that the solar thermal rocket engine is maintained in an instantaneous steady state.

2 . The method of claim 1 , wherein the gas-to-liquid ratio is reduced until the gaseous propellant is no longer provided to the solar thermal rocket engine.

3 . The method of claim 1 , further comprising:

raising a temperature of the solar thermal rocket engine using an electric heater before providing the gaseous propellant to the solar thermal rocket engine.

4 . The method of claim 3 , further comprising:

heating absorbing materials of the solar thermal rocket engine using solar energy in response to the temperature of the solar thermal rocket engine reaching an operating temperature.

5 . The method of claim 3 , wherein the solar thermal rocket engine comprises a control loop and a temperature sensor, wherein the control loop is configured to control the electric heater based on an output of the temperature sensor.

6 . The method of claim 1 , wherein a rate of change of the gas-to-liquid propellant ratio is maintained below a threshold level to prevent components of the solar thermal rocket engine from rising above a threshold temperature as the gas-to-liquid propellant ratio is gradually reduced.

7 . The method of claim 1 , further comprising:

transitioning the solar thermal rocket engine from an electro-thermal thruster mode to a solar-thermal thruster mode in response to reaching a thermal and fluid dynamic steady state within the solar thermal rocket engine.

8 . The method of claim 1 , wherein transitioning the solar thermal rocket engine from the electro-thermal thruster mode to the solar-thermal thruster mode comprises reducing power to an electric heating element and increasing concentrated light input into the solar thermal rocket engine.

9 . A solar thermal rocket, comprising:

a solar thermal rocket engine;

one or more propellant channels, the solar thermal rocket configured to:

provide a gaseous propellant to the solar thermal rocket engine via the one or more propellant channels,

introduce a liquid propellant to the solar thermal rocket engine via the one or more propellant channels; and

gradually reduce a gas-to-liquid propellant ratio provided to the solar thermal rocket engine via the one or more propellant channels to ensure that the solar thermal rocket engine is maintained in an instantaneous steady state.

10 . The solar thermal rocket of claim 9 , wherein the gas-to-liquid ratio is reduced until the gaseous propellant is no longer provided to the solar thermal rocket engine.

11 . The solar thermal rocket of claim 9 , further comprising:

an electric heater configured to raise a temperature of the solar thermal rocket engine before providing the gaseous propellant to the solar thermal rocket engine.

12 . The solar thermal rocket of claim 11 , wherein the solar thermal rocket engine comprises absorbing materials, the solar thermal rocket further configured to:

heat the absorbing materials of the solar thermal rocket engine using solar energy in response to the temperature of the solar thermal rocket engine reaching an operating temperature.

13 . The solar thermal rocket of claim 11 , wherein the solar thermal rocket engine comprises a control loop and a temperature sensor, wherein the control loop is configured to control the electric heater based on an output of the temperature sensor.

14 . The solar thermal rocket of claim 9 , wherein a rate of change of the gas-to-liquid propellant ratio is maintained below a threshold level to prevent components of the solar thermal rocket engine from rising above a threshold temperature as the gas-to-liquid propellant ratio is gradually reduced.

15 . The solar thermal rocket of claim 9 , wherein the solar thermal rocket is further configured to:

transition the solar thermal rocket engine from an electro-thermal thruster mode to a solar-thermal thruster mode in response to reaching a thermal and fluid dynamic steady state within the solar thermal rocket engine.

16 . The solar thermal rocket of claim 9 , wherein transitioning the solar thermal rocket engine from the electro-thermal thruster mode to the solar-thermal thruster mode comprises reducing power to an electric heating element and increasing concentrated light input into the solar thermal rocket engine.

Assignments (1)

Continuity (7)

References Cited (298)