Methods and systems for restartable, hybrid-rockets

Patent metadata

Field	Value
Publication number	US-10774789-B2
Application number	US-201916362430-A
Country	US
Kind code	B2
Filing date	Mar 22, 2019
Priority date	Jul 30, 2012
Publication date	Sep 15, 2020
Grant date	Sep 15, 2020

Abstract

Embodiments of the present invention are directed to various devices, systems and methods of providing a restartable, hybrid-rocket system that uses Acrylonitrile Butadiene Styrene (ABS) and compressed air containing oxygen levels up to 40% as a propellant. Alternatively, embodiments of the present invention includes restartable hybrid rocket system that uses a heterogeneous matrix of ABS and a solid oxidizing agent in addition to compressed air as a propellant. When the ABS is exposed to an electrical potential field, the electrical field's effect on the ABS produces localized arcing between multiple layers of the ABS resulting in joule heating and pyrolysis of the ABS. The pyrolysis produces spontaneous combustion of the ABS once the oxidizer flow provides a local oxygen partial pressure greater than two atmospheres at the surface of the ABS.

First claim

We claim:

1. A restartable, hybrid-rocket system, comprising:
a container configured to deliver an oxidizer flow containing an oxygen-enriched compressed-air mixture having an oxygen concentration greater than 32% molar (by volume);
a housing formed through fused deposition modeling of multiple layers of Acrylonitrile Butadiene Styrene (ABS); the housing having a proximal and a distal end, the housing defining a bore extending therethrough between the proximal and distal ends, the bore defined by an internal surface of the ABS within the housing, and the bore configured to pass the oxidizer flow therethrough; and
at least two electrodes extending through the housing to the internal surface of the ABS, the at least two electrodes configured to provide an electrical potential field along the internal surface of the ABS between the at least two electrodes;
wherein:
the internal surface of the ABS, when exposed to the electrical potential field from the at least two electrodes, is configured to produce localized arcing between the multiple layers of the ABS resulting in joule heating and pyrolysis of the internal surface of the ABS; and
the pyrolysis of the internal surface is configured to produce spontaneous combustion of the internal surface of the ABS once the oxidizer flow provides a local oxygen partial pressure greater than two atmospheres within the bore at the internal surface of the ABS.

2. The restartable, hybrid-rocket system of claim 1 , wherein the restartable, hybrid-rocket system is configured to completely cease combustion of the internal surface of the ABS once the oxidizer flow is stopped and thereafter re-initiate spontaneous combustion of the internal surface of the ABS when the internal surface of the ABS is again exposed to the electrical potential field from the at least two electrodes and the oxidizer flow again provides a local oxygen partial pressure of two atmospheres within the bore at the internal surface of the ABS.

3. The restartable, hybrid-rocket system of claim 2 , wherein the restartable, hybrid-rocket system is configured to completely cease and thereafter re-initiate combustion of the internal surface of the ABS at least five times.

4. The restartable, hybrid-rocket system of claim 1 , wherein the oxygen concentration is between 32 and 40% molar (by volume).

5. The restartable, hybrid-rocket system of claim 1 , wherein the oxygen-enriched compressed-air mixture is instead nitrous oxide (N 2 O).

6. The restartable, hybrid-rocket system of claim 1 , wherein the oxygen-enriched compressed-air mixture is instead 90% hydrogen peroxide (H 2 O 2 ).

7. The restartable, hybrid-rocket system of claim 1 , wherein the localized arcing between the multiple layers of the ABS resulting in the joule heating and the pyrolysis of the internal surface of the ABS requires less than 3 joules of energy.

8. The restartable, hybrid-rocket system of claim 1 , wherein the housing formed through fused deposition modeling of multiple layers of ABS comprises a heterogeneous matrix containing between 15 and 50% of oxidizing additive.

9. The restartable, hybrid-rocket system of claim 8 , wherein the oxidizing additive is potassium permanganate (KMnO 4 ).

10. The restartable, hybrid-rocket system of claim 8 , wherein the oxidizing additive is potassium nitrate (KNO 3 ).

11. The restartable, hybrid-rocket system of claim 1 , wherein the housing formed through fused deposition modeling of multiple layers of ABS comprises a heterogeneous matrix containing up to 15% of oxidizing additives.

12. A method of firing a restartable, hybrid-rocket system, comprising:
providing a container configured to deliver an oxidizer flow containing an oxygen-enriched compressed-air mixture having an oxygen concentration greater than 32% molar (by volume);
forming a housing through fused deposition modeling of multiple layers of Acrylonitrile Butadiene Styrene (ABS); the housing having a proximal and a distal end, the housing defining a bore extending therethrough between the proximal and distal ends, the bore defined by an internal surface of the ABS within the housing, and the bore configured to pass the oxidizer flow therethrough;
providing at least two electrodes extending through the housing to the internal surface of the ABS, the at least two electrodes configured to provide an electrical potential field along the internal surface of the ABS between the at least two electrodes;
exposing the internal surface of the ABS to the electrical potential field from the at least two electrodes, thus producing localized arcing between the multiple layers of the ABS resulting in joule heating and pyrolysis of the internal surface of the ABS; and
configuring the pyrolysis of the internal surface of the ABS to produce spontaneous combustion of the internal surface of the ABS once the oxidizer flow provides a local oxygen partial pressure greater than two atmospheres within the bore at the internal surface of the ABS.

13. The method of ie-firing the restartable, hybrid-rocket system of claim 12 , further comprising:
stopping the oxidizer flow to the internal surface of the ABS sufficient to completely cease the combustion of the internal surface of the ABS;
re-exposing the internal surface of the ABS to the electrical potential field;
and restarting the oxidizer flow sufficient to produce the local oxygen partial pressure greater than two atmospheres within the bore at the internal surface of the ABS.

14. The method of firing the restartable, hybrid-rocket system of claim 13 , comprising repeating in the same order at least five times the steps of:
stopping the oxidizer flow to the internal surface of the ABS sufficient to completely cease the combustion of the internal surface of the ABS,
re-exposing the internal surface of the ABS to the electrical potential field, and
restarting the oxidizer flow sufficient to produce the local oxygen partial pressure greater than two atmospheres within the bore at the internal surface of the ABS.

15. The method of firing the restartable, hybrid-rocket system of claim 12 , wherein the oxygen concentration is between 32 and 40% molar (by volume).

16. The method of firing the restartable, hybrid-rocket system of claim 12 , wherein the oxygen-enriched compressed-air mixture is instead nitrous oxide (N 2 O).

17. The method of firing the restartable, hybrid-rocket system of claim 12 , wherein the oxygen-enriched compressed-air mixture is instead 90% hydrogen peroxide (H 2 O 2 ).

18. The method of firing the restartable, hybrid-rocket system of claim 12 , wherein the localized arcing between the multiple layers of the ABS resulting in the joule heating and the pyrolysis of the internal surface of the ABS requires less than 3 joules of energy.

19. The method of firing the restartable, hybrid-rocket system of claim 12 , wherein forming the housing through fused deposition modeling of multiple layers of ABS further comprises forming within the housing a heterogeneous matrix containing between 15 and 50% of oxidizing additive.

20. The method of firing the restartable, hybrid-rocket system of claim 19 , wherein the oxidizing additive is potassium permanganate (KMnO 4 ) or potassium nitrate (KNO 3 ).

Assignees

• Whitmore Stephen
• Bulcher Anthony Marc
• Lewis Zachary
• Inkley Nathan
• Univ Utah State

Inventors

• Whitmore Stephen
• Bulcher Anthony Marc
• Lewis Zachary
• Inkley Nathan

Classifications

• C06B45/10

  the organic component containing a resin · CPC title

• F02K9/95

  characterised by starting or ignition means or arrangements (safety devices F02K9/38) · CPC title

• C06B33/00

  Compositions containing particulate metal, alloy, boron, silicon, selenium or tellurium with at least one oxygen supplying material which is either a metal oxide or a salt, organic or inorganic, capable of yielding a metal oxide · CPC title

• B33Y80/00

  Products made by additive manufacturing · CPC title

• F02K9/94

  Re-ignitable or restartable rocket- engine plants; Intermittently operated rocket-engine plants · CPC title