Thrust augmentation of an additively manufactured hybrid rocket system using secondary oxidizer injection

Patent metadata

Field	Value
Publication number	US-11408376-B2
Application number	US-202016990586-A
Country	US
Kind code	B2
Filing date	Aug 11, 2020
Priority date	Jul 30, 2012
Publication date	Aug 9, 2022
Grant date	Aug 9, 2022

Abstract

A hybrid rocket includes a housing having first and second ends, a solid-grain fuel material in the housing and defining a bore extending from end to end, two electrodes positioned adjacent to the fuel material to ignite the fuel material at the first end, a primary oxidizer port positioned at the first end to inject a primary oxidizer to flow in a downstream direction from the first end to the second end, a nozzle positioned at the second end and having a converging portion and a diverging portion, and a secondary oxidizer port to inject a secondary oxidizer downstream of the converging portion. The bore has a geometry configured to produce a hot-gas, fuel-rich mixture at the nozzle as the fuel material and primary oxidizer burn while flowing downstream. The diverging portion of the nozzle is configured to spontaneously combust the secondary oxidizer and the hot-gas, fuel-rich mixture.

First claim

What is claimed is:

1. A hybrid rocket, comprising:
a housing having a first end and a second ends;
a solid-grain fuel material positioned in the housing and defining a bore that extends from the first end to the second end, the bore in the solid-grain fuel material defining an internal surface of the solid-grain fuel material exposed within the housing;
at least two electrodes positioned adjacent to the solid-grain fuel material and extending through the housing to the internal surface of the solid-grain fuel material to ignite the solid-grain fuel material at the first end;
a primary oxidizer port positioned at the first end to inject a primary oxidizer to flow in a downstream direction from the first end to the second end;
a nozzle positioned at the second end and having a converging portion and a diverging portion; and
a secondary oxidizer port to inject a secondary oxidizer downstream of the converging portion; wherein:
the bore has a geometry configured to produce a hot-gas, fuel-rich mixture at the nozzle as the solid-grain fuel material and the primary oxidizer burn while flowing downstream, and
the diverging portion is configured to spontaneously combust the secondary oxidizer and the hot-gas, fuel-rich mixture.

2. The hybrid rocket of claim 1 , wherein the solid-grain fuel material includes a plurality of flat layers of the solid-grain fuel material.

3. The hybrid rocket of claim 1 , wherein the secondary oxidizer includes H 2 O 2 .

4. The hybrid rocket of claim 1 , wherein the bore geometry is a helix.

5. The hybrid rocket of claim 1 , wherein the at least two electrodes produce localized electrical arcing to ignite the solid-grain fuel material.

6. The hybrid rocket of claim 1 , wherein the at least two electrodes are configured to be spaced apart so as to provide an electrical potential field along a surface of the solid-grain fuel material that is positioned between the at least two electrodes.

7. The hybrid rocket of claim 1 , wherein the internal surface of the solid-grain fuel material includes has a plurality of exposed ridges, and the at least two electrodes are configured to concentrate an electrical charge on the ridges to ignite the internal surface of the solid-grain fuel material; and
the hybrid rocket is configured such that as the solid-grain fuel material at the internal surface of the solid-grain fuel material is initially consumed or removed through combustion of the solid-grain fuel material, newly exposed ridges are available for re-igniting the solid-grain fuel material upon being subjected to the electrical charge.

8. The hybrid rocket of claim 1 , wherein the solid-grain fuel material is an Acrylonitrile Butadiene Styrene (ABS) material.

9. A hybrid rocket, comprising:
a housing having a first end and a second end;
a solid-grain fuel material positioned in the housing and defining a bore that extends from the first end to the second end, the bore in the solid-grain fuel material defining an internal surface of the solid-grain fuel material exposed within the housing;
at least two electrodes positioned adjacent to the solid-grain fuel material and extending through the housing to the internal surface of the solid-grain fuel material to ignite the solid-grain fuel material at the first end;
a primary oxidizer port positioned at the first end to inject a primary oxidizer to flow in a downstream direction from the first end to the second end;
a nozzle positioned at the second end and having a converging portion and a diverging portion;
an additive oxidizer port to inject an additive oxidizer downstream of the converging portion, the additive oxidizer comprising at least 85% H 2 O 2 ; wherein:
the bore has a geometry configured to produce a hot-gas, fuel-rich mixture at the nozzle as the solid grain fuel material and the primary oxidizer burn while flowing downstream, and
the diverging portion is configured to spontaneously combust the additive oxidizer and the hot-gas, fuel-rich mixture.

10. The hybrid rocket of claim 9 , wherein the bore geometry is a helix.

11. The hybrid rocket of claim 9 , wherein the solid-grain fuel material includes a plurality of flat layers of solid-grain fuel material.

12. The hybrid rocket of claim 9 , wherein the at least two electrodes produce localized electrical arcing to ignite the solid-grain fuel material.

13. The hybrid rocket of claim 9 , wherein the internal surface of the solid-grain fuel material includes a plurality of exposed ridges, and the at least two electrodes are configured to concentrate an electrical charge on the ridges to ignite the internal surface of the solid-grain fuel material; and
the hybrid rocket is configured such that as the solid-grain fuel material at the internal surface of the solid-grain fuel material is initially consumed or removed through combustion of the solid-grain fuel material, newly exposed ridges are available for re-igniting the solid-grain fuel material upon being subjected to the electrical charge.

14. A method of augmenting combustion in a hybrid rocket, comprising:
providing a housing having a first end and a second end, a solid-grain fuel material positioned in the housing and defining a bore that extends from the first end to the second end, the bore in the solid-grain fuel material defining an internal surface of the solid-grain fuel material exposed within the housing, at least two electrodes positioned adjacent to the solid-grain fuel material and extending through the housing to the internal surface of the solid-grain fuel material at the first end, a nozzle positioned at the second end and having a converging portion and a diverging portion, a primary oxidizer port positioned at the first end, and a secondary oxidizer port positioned downstream of the converging portion;
delivering a primary oxidizer into the bore at the primary oxidizer port;
igniting the solid-grain fuel material at the first end with the at least two electrodes;
delivering a hot-gas, fuel-rich mixture to the nozzle through the bore, the bore has a geometry configured to produce the hot-gas, fuel-rich mixture at the nozzle as the solid-grain fuel material and the primary oxidizer burn while flowing downstream;
delivering a secondary oxidizer through the secondary oxidizer port to spontaneously combust the additive oxidizer and the hot-gas, fuel-rich mixture in the diverging portion.

15. The method of claim 14 , further comprising:
providing the internal surface of the solid-grain fuel material with a plurality of exposed ridges, and the at least two electrodes are configured to concentrate an electrical charge on the ridges to ignite the internal surface of the solid-grain fuel material; and
the hybrid rocket is configured such that as the solid-grain fuel material at the internal surface is initially consumed or removed through combustion of the solid-grain fuel material, newly exposed ridges are available for re-igniting the solid-grain fuel material upon being subjected to the electrical charge.

16. The method of claim 14 , wherein the secondary oxidizer comprises at least 85% H 2 O 2 , and the solid-grain fuel material comprises Acrylonitrile Butadiene Styrene (ABS) material.

17. The method of claim 14 , wherein the secondary oxidizer port includes a plurality of secondary oxidizer ports positioned circumferentially around the divergent portion of the nozzle.

18. The method of claim 14 , wherein the bore is helical.

Assignees

• Whitmore Stephen
• Heiner Mark C
• Univ Utah State

Inventors

• Whitmore Stephen
• Heiner Mark C

Classifications

• F02K9/72 Primary

  using liquid and solid propellants, i.e. hybrid rocket-engine plants · CPC title

• F02K9/14

  made from sheet-like materials, e.g. of carpet-roll type, of layered structure · CPC title

• F02K9/52

  Injectors · CPC title

• F02K9/26

  Burning control {(F02K9/10, F02K9/34, F02K9/86, F02K9/92 and F02K9/94 take precedence)} · CPC title