Propellant plasticizer

• US 4,482,406 A
• Filed: 05/03/1983
• Issued: 11/13/1984
• Est. Priority Date: 05/03/1983
• Status: Expired due to Fees

• Current Assignee: United States Of America As Represented By The Secretary Of The Air Force
• Original Assignee: United States Of America As Represented By The Secretary Of The Air Force
• Inventors: Stephens, William D., Nieder, Erin G.
• Primary Examiner(s): Miller, Edward A.
• Application Number:
  US06/491,111
• Time in Patent Office: 560 Days
• Field of Search: 149/19.1, 149/19.9, 149/19.4, 149/20, 560/263
• US Class Current: 149/19.4
• CPC Class Codes: C06B 45/10 the organic component containing a resin
• CPC Class Codes: C08G 18/284 Compounds containing ester groups, e.g. oxyalkylated monocarboxylic acids
• CPC Class Codes: C08G 18/69 Polymers of conjugated dienes hydrogenated polymers of conjugated dienes C08G18/6208
• CPC Class Codes: C08K 5/101 of monocarboxylic acids
• CPC Class Codes: C08L 75/04 Polyurethanes

Abstract

A plasticizer for propellant compositions is 2-hydroxy-3-butoxypropyl oleate. The plasticizer can be incorporated into propellants which conventionally include a binder fuel component, oxidizer component, isocyanate curing agent as well as other conventional components as desired such as bonding agents, curing catalysts and ballistic modifiers. Specifically, a preferred propellant having the internal plasticizer therein includes ammonium perchlorate oxidizer, HTPB binder, aluminum powder fuel, isophorone diisocyanate curing agent, a bonding agent and a delayed quick-cure catalyst. The migration of the plasticizer is substantially reduced so as to extend the shelf-life of rocket motors having the plasticized propellant therein.

Claims

1. A solid propellant for use in a rocket motor comprising a mixture of:

a fuel;

an oxidizer for combusting said fuel;

a binder for holding said fuel and said oxidizer comprising hydroxy-terminated polybutadiene;

a nonmigrating plasticizer attaching to said binder and having the structural formula;

##STR2## a bonding agent;

a curing agent comprising a polyisocyanate; and

a cure catalyst to react with said curing agent to solidify said mixture.

2. A solid propellant as defined in claim 1 wherein said mixture comprises about 22.0% parts by weight of aluminum powder fuel;

about 68.0% parts by weight of ammonium percholorate oxidizer;

about 7.45% parts by weight of hydroxy-terminated polybutadiene binder;

about 2.0% parts by weight of 2-hydroxy-3-butoxpropyl oleate plasticizer; and

a polyisocyanate curing agent.

3. A solid propellant as defined in claim 2 wherein said mixture includes 0.30% parts by weight of said bonding agent, about 0.25% parts by weight of isophorone diisocyanate curing agent, and about 0.075% parts by weight of equal parts of magnesium oxide, triphenyl bismuth, and maleic anhydride as a delayed quick cure catalyst.