Use of high energy propellant in gas generators

• US 4,115,999 A
• Filed: 03/13/1975
• Issued: 09/26/1978
• Est. Priority Date: 03/13/1975
• Status: Expired due to Term

• Current Assignee: the united states of america as represented by the secretary of the navy
• Original Assignee: the united states of america as represented by the secretary of the navy
• Inventors: Diebold, James P.
• Primary Examiner(s): Sebastian, Leland A.
• Application Number:
  US05/558,194
• Time in Patent Office: 1,293 Days
• Field of Search: 149/11, 149/19.1, 149/19.4, 149/19.5, 149/19.9, 149/20, 149/44, 102/103, 60/205, 60/219
• US Class Current: 60/219
• CPC Class Codes: C06B 45/12 having contiguous layers or zones
• CPC Class Codes: C06D 5/06 by reaction of two or more solids
• CPC Class Codes: F23R 5/00 Continuous combustion chambers using solid or pulverulent fuel

Abstract

Thin pieces of high energy propellant are potted in a potting material suchs isocyanates cured hydroxy terminated polybutadiene, hydroxy terminated polybutadiene, polyurethane, polyester or polysulfide so that they will primarily end burn. The result is a composite structure that can be used to produce cool gases suitable for use in gas generator applications.

Claims

1. In a method for doing work wherein a gas generating material within a housing is ignited and burned to produce a gas which does said work without damaging said housing by means of heat, the improvement residing in utilizing as said material a composite consisting essentially of a potting material and one or more pieces of conventional solid rocket propellant potted in said potting material in a way such that said pieces will primarily end burn when ignited and will endothermically pyrolyze sufficient potting material to lower the flame temperature and the oxidativeness of the propellant combustion gases.

2. A method according to claim 1 wherein said potting material is selected from the group consisting of polybutadienes, polyurethanes, polyesters and polysulfides and wherein said solid rocket propellant is selected from the group of composite solid rocket propellants utilizing a material selected from the group consisting of polybutadienes, polyurethanes, polyesters, polysulfides, or nitroglycerin-nitrocellulose mixtures as a binder, a material selected from the group consisting of ammonium perchlorate, ammonium nitrate, cyclotetramethylenetetranitramine (HMX) or cyclotrimethylenetrinitramine (RDX) as an oxidizer, and optionally a material selected from the group consisting of aluminum, magnesium, and carbon as a fuel.

3. A method according to claim 2 wherein said pieces of solid rocket propellant are in the geometrical form of sheets, slabs or strands.