Insulation, insulation precursors, and rocket motors, and related methods

Patent metadata

Field	Value
Publication number	US-10870757-B2
Application number	US-201816045352-A
Country	US
Kind code	B2
Filing date	Jul 25, 2018
Priority date	Jul 25, 2018
Publication date	Dec 22, 2020
Grant date	Dec 22, 2020

Abstract

An insulation material includes a matrix comprising a reaction product formed from a silicon carbide precursor resin and a silicon dioxide precursor resin. At least one filler, such as hollow glass microspheres and/or carbon fiber is dispersed within the matrix. A rocket motor includes a case, the insulation material within and bonded to the case, and a solid propellant within the case. An insulation precursor includes a silicon carbide precursor resin, a silicon dioxide precursor resin, and the at least one filler. Related methods are also disclosed.

First claim

What is claimed is:

1. An insulation material, comprising:
a matrix comprising a reaction product formed from a silicon carbide precursor resin and a silicon dioxide precursor resin; and
at least one filler dispersed within the matrix, the at least one filler comprising at least one material selected from the group consisting of hollow glass microspheres, hollow polymeric microspheres, hollow ceramic microspheres, and hollow fibers.

2. The insulation material of claim 1 , wherein the matrix further comprises a catalyst.

3. The insulation material of claim 1 , wherein the insulation material exhibits a thermal conductivity of less than about 0.30 W/mK.

4. The insulation material of claim 1 , wherein the insulation material exhibits a density of less than about 0.8 g/cm 3 .

5. The insulation material of claim 1 , wherein the insulation material comprises from about 50% to about 85% silicon dioxide by weight.

6. The insulation material of claim 1 , wherein the at least one filler comprises the hollow glass microspheres.

7. The insulation material of claim 6 , wherein the insulation material comprises from about 5% to about 10% hollow glass microspheres by weight.

8. The insulation material of claim 6 , wherein the hollow glass microspheres exhibit a mean diameter from about 100 nm to about 5 mm.

9. The insulation material of claim 1 , wherein the at least one filler further comprises carbon fiber.

10. The insulation material of claim 9 , wherein the insulation material comprises from about 1% to about 5% carbon fiber by weight.

11. The insulation material of claim 1 , wherein the insulation material comprises from about 5% to about 10% silicon carbide by weight.

12. The insulation material of claim 1 , wherein the matrix comprises a reaction product formed from a silicon carbide precursor resin, a silicon dioxide precursor resin, and a crosslinking agent.

13. A rocket motor, comprising:
a case;
an insulation material within the case, the insulation material comprising:
a matrix comprising a reaction product formed from a silicon carbide precursor resin and a silicon dioxide precursor resin; and
at least one filler dispersed within the matrix, the at least one filler comprising at least one material selected from the group consisting of hollow glass microspheres, hollow polymeric microspheres, hollow ceramic microspheres, and hollow fibers; and

a solid propellant within the case.

14. The rocket motor of claim 13 , further comprising a nozzle secured to the case.

15. The rocket motor of claim 13 , wherein the insulation material is bonded to the case with a silicone adhesive.

16. A method of forming an insulation material, comprising:
combining a silicon carbide precursor resin, a silicon dioxide precursor resin, and at least one filler to form an insulation precursor, the at least one filler comprising at least one material selected from the group consisting of hollow glass microspheres, hollow polymeric microspheres, hollow ceramic microspheres, and hollow fibers; and
curing the insulation precursor to form an insulation material comprising the at least one filler dispersed within a solid matrix.

17. The method of claim 16 , wherein the combining comprises combining the silicon carbide precursor, the silicon dioxide precursor resin, and the at least one filler, the silicon dioxide precursor resin comprising an organically modified silicon dioxide preceramic polymer.

18. The method of claim 16 , wherein the combining comprises combining the silicon carbide precursor resin, the silicon dioxide precursor resin, the at least one filler, and a catalyst to form the insulation precursor.

19. The method of claim 16 , wherein the combining comprises combining the silicon carbide precursor resin, the silicon dioxide precursor resin, the at least one filler, and an adhesion promoter to form the insulation precursor.

20. The method of claim 16 , wherein the combining comprises combining the silicon carbide precursor resin, the silicon dioxide precursor resin, and the at least one filler, the silicon dioxide precursor resin exhibiting a density from about 0.95 g/cm 3 to about 1.05 g/cm 3 .

21. The method of claim 16 , wherein the combining comprises combining the silicon carbide precursor resin, the silicon dioxide precursor resin, and the at least one filler, the silicon carbide precursor resin exhibiting a density from about 1.10 g/cm 3 to about 1.25 g/cm 3 .

22. The method of claim 16 , wherein the combining comprises combining the silicon carbide precursor resin, the silicon dioxide precursor resin, the at least one filler, and a crosslinking agent to form the insulation precursor, the at least one filler comprising the hollow glass microspheres and carbon fiber, the insulation precursor comprising:
the silicon carbide precursor resin from about 5 weight % to about 10 weight %;
the silicon dioxide precursor resin from about 50 weight % to about 85 weight %;
the crosslinking agent from about 1 weight % to about 5 weight %;
the hollow glass microspheres from about 5 weight % to about 10 weight %; and
the carbon fiber from about 1 weight % to about 5 weight %.

23. The method of claim 16 , wherein the combining comprises combining the silicon carbide precursor resin, the silicon dioxide precursor resin, the at least one filler, a crosslinking agent, a catalyst, and an adhesion promoter to form the insulation precursor, the at least one filler comprising the hollow glass microspheres and carbon fiber, the insulation precursor consisting essentially of:
the silicon carbide precursor resin;
the silicon dioxide precursor resin;
the crosslinking agent;
the hollow glass microspheres;
the carbon fiber;
the catalyst; and
the adhesion promoter.

24. The method of claim 16 , wherein the combining to form the insulation precursor comprises forming the insulation precursor to exhibit a viscosity of less than about 100,000 cP at 25° C.

25. The method of claim 16 , wherein the combining to form the insulation precursor comprises forming the insulation precursor to exhibit a pot life of at least about 30 days at 25° C.

26. The method of claim 16 , wherein curing the insulation precursor comprises heating the insulation precursor to a temperature of at least about 150° C.

27. The method of claim 16 , wherein curing the insulation precursor comprises heating the insulation precursor to a temperature of at least about 250° C.

28. The method of claim 16 , further comprising heating the insulation material to a temperature of at least about 400° C.

29. A method of insulating a rocket motor, comprising:
forming an insulation material, comprising:
combining a silicon carbide precursor resin, a silicon dioxide precursor resin, and at least one filler to form an insulation precursor, the at least one filler comprising at least one material selected from the group consisting of hollow glass microspheres, hollow polymeric microspheres, hollow ceramic microspheres, and hollow fibers; and
curing the insulation precursor to form the insulation material comprising the at least one filler dispersed within a solid matrix;

applying the insulation material to an interior surface of a case of a rocket motor; and
casting a propellant within the case.

30. The method of claim 29 , further comprising:
burning the propellant within th

Assignees

• Northrop Grumman Innovation Systems Inc

Inventors

• Garcia Benjamin W C
• Larson Robert S

Classifications

• C08J5/042

  with carbon fibres · CPC title

• F02K9/34 Primary

  Casings; Combustion chambers; Liners thereof · CPC title

• C08K2201/005

  Additives being defined by their particle size in general · CPC title

• C08K7/06

  Elements · CPC title

• C09D183/16

  in which all the silicon atoms are connected by linkages other than oxygen atoms · CPC title