Anaerobic hybrid propulsion device with fuel present in the form of divided solids

Patent metadata

Field	Value
Publication number	US-9957919-B2
Application number	US-201314427963-A
Country	US
Kind code	B2
Filing date	Sep 10, 2013
Priority date	Sep 13, 2012
Publication date	May 1, 2018
Grant date	May 1, 2018

Abstract

An anaerobic propulsion device of hybrid type. The propulsion device includes a combustion chamber into which an oxidant is injected thereto comes into contact with a fuel. The chamber includes an orifice, notably a nozzle, to inject the combustion gases. The fuel takes the form of solids divided into granules, typically grains, powder or beads. The propulsion device further includes a segregation device arranged between a reservoir for granules of solid fuel, and the combustion chamber. The segregation device is configured to prevent granules of fuel in solid form from passing between the reservoir and the combustion chamber. The segregation device includes orifices to allow the passage of the fuel, once the fuel has become pasty, liquid or vaporized.

First claim

The invention claimed is:

1. An anaerobic propulsion device of a hybrid type, the device comprising a segregation device arranged between a reservoir of granules of fuel in a solid form and a combustion chamber; the segregation device is configured to prevent the granules of the fuel in the solid form from passing between the reservoir and the combustion chamber, the segregation device comprises orifices to allow a passage of the fuel that has become pasty, liquid or vaporized; the reservoir comprises a pressure device to apply pressure to the granules to push the granules toward the segregation device, the pressure device comprises a deformable membrane arranged at a surface of the reservoir of the granules, and wherein the segregation device further comprises a structure made of porous material with open pores, wettable by the fuel that is locally liquefied under an action of heat.

2. The anaerobic propulsion device as claimed in claim 1 , wherein the segregation device comprises a structure comprising holes, each of the holes having a dimension smaller than a predetermined dimension selected as a function of a mean diameter of the granules.

3. The anaerobic propulsion device as claimed in claim 1 , wherein the combustion chamber is substantially cylindrical in shape, the segregation device constitutes at least a part of a lateral surface of the combustion chamber.

4. The anaerobic propulsion device as claimed in claim 1 , wherein the segregation device constitutes at least a part of an upper surface of the combustion chamber.

5. The anaerobic propulsion device as claimed in claim 4 , wherein the segregation device constitutes the part of the upper surface of the combustion chamber opposite an ejection orifice for combustion gases.

6. The anaerobic propulsion device as claimed in claim 1 , wherein the propulsion device is a shape substantially exhibiting a symmetry of revolution about a vertical axis; and wherein the reservoir is arranged around the combustion chamber, at an opposite end thereof to an exhaust nozzle.

7. The anaerobic propulsion device as claimed in claim 1 , wherein the reservoir comprises an elastomer membrane configured to separate, within the reservoir, a space to store the granules and a pressurizing space, the pressurizing space comprises pressurizing orifices connected to at least one gas injection system.

8. The anaerobic propulsion device as claimed in claim 1 , wherein the reservoir comprises a set of radial dividers which are perpendicular to a surface of the segregation device, each of the radial dividers having a geometry with a capillary gradient to encourage the supply of the fuel in a paste or liquid form to the segregation device.

9. An anaerobic rocket engine, comprising the anaerobic propulsion device of the hybrid type as claimed in claim 1 , a volume of the fuel, and a volume of liquid oxidant, wherein the fuel is a form of solids divided into granules.

10. The rocket engine as claimed in claim 9 , wherein the fuel comprises beads made of at least one of a following: polyethylene, polybutadiene or paraffin.

11. The rocket engine as claimed in claim 10 , wherein the beads have a diameter of one to five millimeters.

12. A satellite comprising the rocket engine as claimed in claim 9 .

13. An anaerobic propulsion device of a hybrid type, the device comprising a segregation device arranged between a reservoir of granules of fuel in a solid form and a combustion chamber; the segregation device is configured to prevent the granules of the fuel in the solid form from passing between the reservoir and the combustion chamber, the segregation device comprises orifices to allow a passage of the fuel that has become pasty, liquid or vaporized; the reservoir comprises a pressure device to apply pressure to the granules to push the granules toward the segregation device, the pressure device comprises a deformable membrane arranged at a surface of the reservoir of the granules, and wherein the reservoir further comprises a set of radial dividers which are perpendicular to a surface of the segregation device, each of the radial dividers having a geometry with a capillary gradient to encourage the supply of the fuel in a paste or liquid form to the segregation device.

14. The anaerobic propulsion device as claimed in claim 13 , wherein the segregation device comprises a structure comprising holes, each of the holes having a dimension smaller than a predetermined dimension selected as a function of a mean diameter of the granules.

15. The anaerobic propulsion device as claimed in claim 13 , wherein the segregation device comprises a structure made of porous material with open pores, wettable by the fuel that is locally liquefied under an action of heat.

16. The anaerobic propulsion device as claimed in claim 13 , wherein the combustion chamber is substantially cylindrical in shape, the segregation device constitutes at least a part of a lateral surface of the combustion chamber.

17. The anaerobic propulsion device as claimed in claim 13 , wherein the segregation device constitutes at least a part of an upper surface of the combustion chamber.

18. The anaerobic propulsion device as claimed in claim 17 , wherein the segregation device constitutes the part of the upper surface of the combustion chamber opposite an ejection orifice for combustion gases.

19. The anaerobic propulsion device as claimed in claim 13 , wherein the propulsion device is a shape substantially exhibiting a symmetry of revolution about a vertical axis; and wherein the reservoir is arranged around the combustion chamber, at an opposite end thereof to an exhaust nozzle.

20. The anaerobic propulsion device as claimed in claim 13 , wherein the reservoir comprises an elastomer membrane configured to separate, within the reservoir, a space to store the granules and a pressurizing space, the pressurizing space comprises pressurizing orifices connected to at least one gas injection system.

21. An anaerobic rocket engine, comprising the anaerobic propulsion device of the hybrid type as claimed in claim 13 , a volume of the fuel, and a volume of liquid oxidant, wherein the fuel is a form of solids divided into granules.

22. The rocket engine as claimed in claim 21 , wherein the fuel comprises beads made of at least one of a following: polyethylene, polybutadiene or paraffin.

23. The rocket engine as claimed in claim 22 , wherein the beads have a diameter of one to five millimeters.

24. A satellite comprising the rocket engine as claimed in claim 21 .

Assignees

• Airbus Defence & Space Sas

Inventors

• Figus Christophe

Classifications

• F02K9/94

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

• F05D2300/514

  Porosity · CPC title

• F02K9/72 Primary

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

• F02K9/10

  Shape or structure of solid propellant charges · CPC title

• F05D2300/501

  Elasticity · CPC title