Precursor compositions for an insulation and related methods

Patent metadata

Field	Value
Publication number	US-12560135-B2
Application number	US-202218064703-A
Country	US
Kind code	B2
Filing date	Dec 12, 2022
Priority date	Oct 25, 2017
Publication date	Feb 24, 2026
Grant date	Feb 24, 2026

Abstract

A precursor composition comprising, before curing, ethylene propylene diene monomer (EPDM), an aramid, and a carbon material comprising carbon nanotubes, graphite, or a combination thereof. A rocket motor including a reaction product of the precursor composition and a method of insulating a rocket motor are also disclosed.

First claim

What is claimed is:

1. A precursor composition, consisting of, before curing:
ethylene propylene diene monomer (EPDM);
an aramid;
multi-walled carbon nanotubes in an amount of from about 15.0 parts by weight to about 30.0 parts by weight of the precursor composition;
expandable graphite in an amount of from about 1.0 parts by weight to about 10.0 parts by weight of the precursor composition;
a plasticizer;
one or more of zinc oxide, silica, or magnesium hydroxide;
a chlorinated organic compound;
trimethylolpropane trimethacrylate or a poly(butadiene) resin;
an antioxidant;
a fatty acid; and
a peroxide,
wherein after curing, the precursor composition provides an insulation material exhibiting an ablative performance suitable for use in various regions of a rocket motor.

2. The precursor composition of claim 1 , wherein the plasticizer is an aliphatic resin.

3. The precursor composition of claim 1 , wherein the plasticizer is a five carbon petroleum hydrocarbon.

4. The precursor composition of claim 1 , wherein the chlorinated organic compound is a solid chlorinated paraffin.

5. The precursor composition of claim 1 , wherein the antioxidant is a hydroquinoline compound, an amine compound, a phenol compound, or a combination thereof.

6. The precursor composition of claim 1 , wherein the antioxidant is a polymerized 1,2 dihydro-2,2,4-trimethylquinoline.

7. The precursor composition of claim 1 , wherein the fatty acid is stearic acid.

8. The precursor composition of claim 1 , wherein the peroxide is 1,1-di-(t-butylperoxy)-3,3,5-trimethylcyclohexane or dicumyl peroxide.

9. A precursor composition, comprising, before curing:
ethylene propylene diene monomer (EPDM);
poly-p-phenylene terephthalamide;
multi-walled carbon nanotubes in an amount of from about 15.0 parts by weight to about 30.0 parts by weight of the precursor composition;
expandable graphite in an amount of from about 1.0 parts by weight to about 10.0 parts by weight of the precursor composition;
a five carbon petroleum hydrocarbon;
magnesium hydroxide;
a solid chlorinated paraffin;
a poly(butadiene) resin;
a hydroquinoline compound;
a fatty acid; and
1,1-di-(t-butylperoxy)-3,3,5-trimethylcyclohexane or dicumyl peroxide,
wherein after curing, the precursor composition provides an insulation material exhibiting an ablative performance suitable for use in various regions of a rocket motor.

10. The precursor composition of claim 9 , wherein the hydroquinoline compound is a polymerized 1,2 dihydro-2,2,4-trimethylquinoline.

11. The precursor composition of claim 9 , wherein the poly-p-phenylene terephthalamide is poly-p-phenylene terephthalamide fibers or poly-p-phenylene terephthalamide pulp.

12. A precursor composition, consisting of, before curing:
ethylene propylene diene monomer (EPDM);
poly-p-phenylene terephthalamide;
multi-walled carbon nanotubes in an amount of from about 15.0 parts by weight to about 30.0 parts by weight of the precursor composition;
expandable graphite in an amount of from about 1.0 parts by weight to about 10.0 parts by weight of the precursor composition;
a five carbon petroleum hydrocarbon;
magnesium hydroxide;
a solid chlorinated paraffin;
a poly(butadiene) resin;
a polymerized 1,2 dihydro-2,2,4-trimethylquinoline;
stearic acid; and
dicumyl peroxide,
wherein after curing, the precursor composition provides an insulation material exhibiting an ablative performance suitable for use in various regions of a rocket motor.

13. The precursor composition of claim 12 , wherein the poly(butadiene) resin is a high vinyl poly(butadiene).

14. A precursor composition, consisting of, before curing:
ethylene propylene diene monomer (EPDM);
an aramid;
multi-walled carbon nanotubes in an amount of from about 15.0 parts by weight to about 30.0 by weight of the precursor composition;
expandable graphite in an amount of from about 1.0 parts by weight to about 10.0 parts by weight of the precursor composition;
a plasticizer;
one or more of zinc oxide, silica, or magnesium hydroxide;
a chlorinated organic compound;
a co-agent;
an antioxidant;
a fatty acid; and
a peroxide,
wherein after curing, the precursor composition provides an insulation material exhibiting an ablative performance suitable for use in various regions of a rocket motor.

Assignees

• Northrop Grumman Systems Corp

Inventors

• Gajiwala Himansu M
• Hall Steven B

Classifications

• C08L23/16 Primary

  Ethylene-propylene or ethylene-propylene-diene copolymers · CPC title

• F02K9/34

  Casings; Combustion chambers; Liners thereof · CPC title

• C08L23/145

  with monomers having two or more carbon-to-carbon double bonds · CPC title

• C08L77/10

  Polyamides derived from aromatically bound amino and carboxyl groups of amino-carboxylic acids or of polyamines and polycarboxylic acids · CPC title

• C08L23/083

  with aliphatic polyenes, i.e. containing two or more carbon-to-carbon double bonds · CPC title