Hybrid rocket motor having a precombustion chamber

• US 6,679,049 B2
• Filed: 01/22/2002
• Issued: 01/20/2004
• Est. Priority Date: 01/22/2002
• Status: Expired due to Fees

• Current Assignee: HY Pat Corporation
• Original Assignee: HY Pat Corporation
• Inventors: Smith, Kevin W., Kline, Korey R.
• Primary Examiner(s): Gartenberg, Ehud
• Application Number:
  US10/054,644
• Publication Number:
  US 20030136107A1
• Time in Patent Office: 728 Days
• Field of Search: 602/07, 602/19, 602/51
• US Class Current: 60/207
• CPC Class Codes: F02K 9/72 using liquid and solid propellants, i.e. hybrid rocket-engine plants
• CPC Class Codes: F02K 9/94 Re-ignitable or restartable rocket- engine plants; Intermittently operated rocket-engine plants

Abstract

A hybrid rocket motor is provided with a precombustion chamber supplied with propellant from separate fuel and oxidizer sources. The propellant can be in the form of gas or liquid and injected substantially tangentially into the head end of the hybrid motor adjacent the oxidizer injector to form a propellant swirl. As the hybrid motor oxidizer is injected into the swirl, it is heated and gasified, and assumes a swirling motion which increases the oxidizer path length and thereby increases the dwell time of the oxidizer. The increased dwell time increases combustion efficiency and permits multiple restarts of the hybrid motor. The propellant may also be a combination of solid and fluid reactants. In one embodiment, the oxidizer injector is extended into the combustion chamber to form a toroidal precombustion chamber which has an annular nozzle adjacent a face of the oxidizer injector.

Claims

1. A hybrid rocket motor, comprising:

a) a container having a first fluid reactant therein and an outlet;

b) a main combustion chamber containing a first solid reactant therein;

c) a first fluid reactant injector between said container and said main combustion chamber through which said first fluid reactant is injected into said main combustion chamber to be combusted with said first solid reactant;

d) a precombustion chamber at a head end of said main combustion chamber;

e) a second fluid reactant which is injected into said precombustion chamber; and

f) a third reactant which is contacted with said second fluid reactant in said precombustion chamber to form a combustible propellant, wherein heat generated from combustion of combustible propellant heats said injected first fluid reactant.

2. A hybrid rocket motor according to claim 1, wherein:

said third reactant is fluid.

3. A hybrid rocket motor according to claim 2, wherein:

said second and third reactants are in a swirl in said precombustion chamber.

4. A hybrid rocket motor according to claim 1, wherein:

at least one of said second and third reactants is injected substantially tangentially into said precombustion chamber.

5. A hybrid rocket motor according to claim 1, wherein:

said injector extends along substantially an entirety of a length of said precombustion chamber, such that an annular nozzle for said precombustion chamber is defined around said injector.

6. A hybrid rocket motor according to claim 5, wherein:

said third reactant is solid.

7. A hybrid rocket motor according to claim 1, wherein:

said first and second fluid reactants are the same.

8. A hybrid rocket motor according to claim 7, wherein:

said second fluid reactant is plumbed from said first container.

9. A hybrid rocket motor according to claim 7, wherein:

said second fluid reactant is tapped from holes in said first fluid reactant injector into said precombustion chamber.

10. A hybrid rocket motor according to claim 1, wherein:

said precombustion chamber is located around or adjacent said first fluid reactant injector.

11. A hybrid rocket motor according to claim 10, wherein:

said precombustion chamber includes a recirculation zone forward of said first fluid reactant injector.

12. A hybrid rocket motor according to claim 1, wherein:

said first fluid reactant is an oxidizer, and said first solid reactant is a fuel.

13. A hybrid rocket motor, comprising:

a) a container having a first fluid reactant therein and an outlet;

b) a main combustion chamber containing a first solid reactant therein;

c) a first fluid reactant injector between said container and said main combustion chamber through which said first fluid reactant is injected into said main combustion chamber to be combusted with said first solid reactant; and

d) a precombustion chamber around at least a portion of said first fluid reactant injector, said precombustion chamber having,

i) a first inlet for a second fluid reactant, and

ii) one of (A) a second solid reactant and (B) a second inlet for a third fluid reactant which when combined with said second fluid reactant forms a combustible propellant.

14. A hybrid rocket motor according to claim 13, wherein:

said second fluid reactant is an oxidizer, and said precombustion chamber includes said second solid reactant which is a fuel.

15. A hybrid rocket motor according to claim 13, wherein:

said second fluid reactant is an oxidizer, and said precombustion chamber includes said at least one inlet, wherein said third fluid reactant is a fuel.

16. A hybrid rocket motor according to claim 15, further comprising:

e) a second fluid reactant tank including said second fluid reactant, said second fluid reactant tank in communication with said first inlet.

17. A hybrid rocket motor according to claim 16, further comprising:

f) a third fluid reactant tank including said third fluid reactant, said third fluid reactant tank in communication with said second inlet.

18. A hybrid rocket motor according to claim 16, further comprising:

f) said second inlet is in communication with said container, wherein said third fluid reactant is said first fluid reactant.

19. A hybrid rocket motor, comprising:

a) a container having a first fluid reactant therein and an outlet;

b) a main combustion chamber containing a solid reactant therein;

c) a main injector between said container and said main combustion chamber, said main injector having a face with a plurality of pathways through which said first fluid reactant is injected into said main combustion chamber to be combusted with said solid reactant;

d) a second fluid reactant;

e) a third fluid reactant stored separately from said second fluid reactant;

f) a precombustion chamber at a head end of said main combustion chamber, said second and third reactants being combined and combusted in said precombustion chamber to generate heat adjacent said face of said main injector.

20. A hybrid rocket motor according to claim 19, wherein:

said first fluid reactant is an oxidizer, and said solid reactant is a fuel.

21. A hybrid rocket motor according to claim 19, wherein:

said second fluid reactant is an oxidizer, and said third fluid is a fuel.

22. A hybrid rocket motor according to claim 20, wherein:

said first and second fluid reactants are the same.

23. A hybrid rocket motor according to claim 22, wherein:

said second fluid reactant is stored in said first container.

24. A hybrid rocket motor according to claim 19, wherein:

said second fluid reactant is selected from the group of gaseous oxygen, liquid oxygen, triethyl aluminum, trimethlyl aluminum, and triethyl borine, and

said third fluid reactant is selected from the group of propane, ethane and ethylene.

25. A hybrid rocket motor according to claim 19, wherein:

a mixture of said second and third fluid reactants is hypergolic.

26. A hybrid rocket motor according to claim 25, wherein:

said second fluid reactant is nitric acid and said third fluid reactant is aniline.

27. A hybrid rocket motor according to claim 19, wherein:

said main injector extends substantially through an entirety of a length of said precombustion chamber such that an annular exit nozzle for said precombustion chamber is defined about said face of said main injector.

28. A hybrid rocket motor according to claim 19, wherein:

said precombustion chamber includes a recirculation zone forward of said face of said main injector.

29. A hybrid rocket motor according to claim 19, wherein:

said second and third fluid reactants are swirled together.

30. A projectile, comprising:

a) a motor having a forward end and an aft end, said motor including,

i) a container having a first fluid reactant therein and an outlet,

ii) a main combustion chamber containing a first solid reactant therein,

iii) a first fluid reactant injector between said container and said main combustion chamber through which said first fluid reactant is injected into said main combustion chamber to be combusted with said first solid reactant,

iv) a precombustion chamber at a head end of said main combustion chamber,

v) a second fluid reactant which is injected into said precombustion chamber, and

vi) a third reactant which is contacted with said second fluid reactant in said precombustion chamber to form a combustible propellant, wherein heat generated from combustion of combustible propellant heats said injected first fluid reactant;

b) a tubular body around said motor;

c) a nose portion coupled to said forward end of said motor; and

d) a nozzle coupled to said aft end of said motor.

31. A method of igniting a hybrid rocket motor, comprising:

a) providing a hybrid rocket motor having a forward end and an aft end, said motor including,

i) a container having a fluid first reactant therein and an outlet,

ii) a combustion chamber containing a solid second reactant combustible with said fluid first reactant and having a head end and an aft end,

iii) an injector between the container and the head end of the combustion chamber;

b) providing third and fourth reactants which when mixed together form a propellant;

c) mixing the third and fourth reactants at the head end of the combustion chamber to form the propellant;

d) combusting the propellant such that the head end of the combustion chamber is heated;

e) injecting the fluid first reactant through the injector;

f) heating the fluid first reactant by combustion of the propellant; and

g) combusting the heated fluid first reactant with the solid first reactant such that the hybrid rocket motor is ignited.

32. A method according to claim 31, wherein:

the fluid first reactant is an oxidizer and the solid second reactant is a fuel.

33. A method according to claim 31, wherein:

the second and third reactants are fluids.

34. A method according to claim 33, wherein:

said mixing includes swirling the second and third reactants together.

35. A method according to claim 31, wherein:

the second reactant is a fluid and the third reactant is a solid.