EXTERNALLY POWERED HYBRID PROPULSION SYSTEM

• US 20150040536A1
• Filed: 10/22/2013
• Published: 02/12/2015
• Est. Priority Date: 10/22/2012
• Status: Active Grant

• Current Assignee: Escape Dynamics, Inc.
• Original Assignee: Escape Dynamics, Inc.
• Inventors: Tseliakhovich, Dmitriy, Hanover, Matthew Loukas
• Granted Patent: US 9,453,480 B2
• Time in Patent Office: Days
• US Class Current: 60/203.1
• CPC Class Codes: B64G 1/402 Propellant tanks; Feeding propellants
• CPC Class Codes: B64G 1/404 Hybrid rocket engines
• CPC Class Codes: B64G 1/405 Ion or plasma engines per se F03H1/00
• CPC Class Codes: B64G 1/409 Unconventional spacecraft propulsion systems
• CPC Class Codes: B64G 1/428 Power distribution and management
• CPC Class Codes: F02K 9/44 Feeding propellants
• CPC Class Codes: F02K 9/72 using liquid and solid propellants, i.e. hybrid rocket-engine plants
• CPC Class Codes: F03H 1/00 Using plasma to produce a reactive propulsive thrust generating plasma H05H1/00 ion sources per se H01J27/02, ion sources for plasma processing or ion beams H01J37/08
• CPC Class Codes: F03H 99/00 Subject matter not provided for in other groups of this subclass
• CPC Class Codes: F05D 2300/2261 of silicon

Abstract

A hybrid propulsion system for a vehicle comprises a propellant tank for providing a supply of propellant, a propellant heater, and an exhaust nozzle. The propellant tank is in fluid communication with the propellant heater and is configured for providing a flow of propellant to the propellant heater. The propellant heater is in fluid communication with the propellant tank and the nozzle and initially comprises a supply of oxidizer that is configured for reacting chemically with the propellant to produce heat. The propellant heater is further configured for receiving a beam of microwave energy and facilitating transmission of the beam of microwave energy to the propellant. The nozzle is in fluid communication with the propellant heater and is configured for receiving a flow of propellant from the propellant heater, for accelerating the propellant, and for expelling the propellant so as to produce thrust.

Claims

1. A hybrid propulsion system for a vehicle, the hybrid propulsion system comprising:

a propellant tank for providing a flow of propellant;

a propellant heater; and

an exhaust nozzle;

the propellant tank being in fluid communication with the propellant heater and configured for providing a flow of propellant to the propellant heater;

the propellant heater being in fluid communication with the propellant tank and the exhaust nozzle and initially comprising a quantity of oxidizer, the quantity of oxidizer being configured for reacting chemically with the flow of propellant to produce heat;

the propellant heater being further configured for receiving a beam of microwave energy and facilitating transmission of the beam of microwave energy to the flow of propellant; and

the exhaust nozzle being in fluid communication with the propellant heater and being for receiving a flow of propellant from the propellant heater, for accelerating the flow of propellant, and for expelling the flow of propellant so as to produce thrust.

2. The hybrid propulsion system of claim 1, wherein the flow of propellant comprises hydrogen.

3. The hybrid propulsion system of claim 1, wherein the quantity of oxidizer is infiltrated into a refractory foam disposed within the propellant heater.

4. The hybrid propulsion system of claim 1, wherein the propellant heater comprises silicon carbide.

5. The hybrid propulsion system of claim 1, wherein the propellant heater comprises a ceramic matrix composite material.

6. The hybrid propulsion system of claim 1, wherein a manifold is disposed between the propellant heater and the exhaust nozzle, the manifold containing oxidizer.

7. The hybrid propulsion system of claim 1, wherein the propellant heater comprises a propellant heater shell, at least a portion of which is configured so as to be substantially transmissive to a beam of electromagnetic energy.

8. A method of operating a hybrid propulsion system for a vehicle comprising:

providing a flow of propellant, a propellant heater, and a nozzle, the flow of propellant being in fluid communication with the propellant heater, the propellant heater being in fluid communication with the flow of propellant and the nozzle;

initially disposing, in the propellant heater, a quantity of oxidizer configured for reacting chemically with the flow of propellant to produce heat;

establishing a flow of propellant from the flow of propellant to the propellant heater;

during an initial flight phase of the vehicle;

reacting the flow of propellant with the quantity of oxidizer in the propellant heater to produce a heated flow of propellant; and

delivering the flow of propellant from the propellant heater to the nozzle for delivery through the nozzle to outside the vehicle; and

during a subsequent flight phase of the vehicle;

heating the flow of propellant with an external microwave beam in the propellant heater to produce a heated flow of propellant; and

delivering the flow of propellant from the propellant heater to the nozzle for delivery through the nozzle to outside the vehicle.

9. The method of operating a hybrid propulsion system of claim 8, wherein the flow of propellant comprises hydrogen.

10. The method of operating a hybrid propulsion system of claim 8, wherein the quantity of oxidizer is infiltrated into a refractory foam disposed within the propellant heater.

11. The method of operating a hybrid propulsion system of claim 8, wherein the propellant heater comprises silicon carbide.

12. The method of operating a hybrid propulsion system of claim 8, wherein the propellant heater comprises a ceramic matrix composite material.

13. The method of operating a hybrid propulsion system of claim 8, wherein a manifold is disposed between the propellant heater with the nozzle, the manifold containing oxidizer.

14. The method of operating a hybrid propulsion system of claim 8, wherein the propellant heater comprises a propellant heater shell, at least a portion of which is configured so as to be substantially transmissive to a beam of electromagnetic energy.

15. A vehicle comprising a hybrid propulsion system, the hybrid propulsion system comprising:

a propellant tank for providing a supply of propellant;

a propellant heater; and

an exhaust nozzle;

the propellant tank being in fluid communication with the propellant heater and configured for providing a flow of propellant to the propellant heater;

the propellant heater being in fluid communication with the propellant tank and the exhaust nozzle and initially comprising a quantity of oxidizer, the quantity of oxidizer being configured for reacting chemically with the flow of propellant to produce heat;

the propellant heater being further configured for receiving a beam of microwave energy and facilitating transmission of the beam of microwave energy to the flow of propellant; and

the exhaust nozzle being in fluid communication with the propellant heater and being configured for receiving a flow of propellant from the propellant heater, for accelerating the flow of propellant, and for expelling the flow of propellant so as to produce thrust.

16. The vehicle of claim 15, wherein the quantity of oxidizer is infiltrated into a refractory foam disposed within the propellant heater.

17. The vehicle of claim 15, wherein the propellant heater comprises silicon carbide.

18. The vehicle of claim 15, wherein the propellant heater comprises a ceramic matrix composite material.

19. The vehicle of claim 15, wherein a manifold is disposed between the propellant heater and the exhaust nozzle, the manifold containing oxidizer.

20. The vehicle of claim 15, wherein the propellant heater comprises a propellant heater shell, at least a portion of which is configured so as to be substantially transmissive to a beam of electromagnetic energy.