Low smoke rocket motor liner compositions

• US 6,051,087 A
• Filed: 12/16/1992
• Issued: 04/18/2000
• Est. Priority Date: 01/29/1992
• Status: Expired due to Fees

• Current Assignee: Orbital ATK Inc.
• Original Assignee: Cordant Technologies, Inc. (Howmet Aerospace, Inc.)
• Inventors: Cohen, Norman, Hutchens, Dale E.
• Primary Examiner(s): Miller, Edward A.
• Application Number:
  US07/991,467
• Time in Patent Office: 2,680 Days
• Field of Search: 102/290, 149/19.4, 149/19.1, 149/19.5, 149/19.6, 523/180
• US Class Current: 149/19.4
• CPC Class Codes: C06B 45/12 having contiguous layers or zones

Abstract

A formulation is provided which is capable of performing as a liner layer between a rocket motor casing and the propellant grain disposed within the interior of the rocket motor casing. The composition produces relatively little smoke during the operation of the rocket motor and is capable of securely bonding a wide range of conventional propellants to a wide range of conventional casings. In one preferred formulation, the liner consists of from from about 50% to about 75% oxygen containing polymer; from about 3% to about 15% curing agent; from about 5% to about 50% filler and from about 0.01% to about 0.5% cure catalyst.

Claims

1. A rocket motor liner composition comprising:

from about 50% to about 75% polymer selected from the group consisting of polyethers, polyglycols, polyesters, polyamides, and polycarbonates;

from about 3% to about 15% curing agent; and

from about 20% to about 40% filler selected from the group consisting of dicyandiamide, ammonium nitrate, and silica;

wherein said composition is formulated such that it is capable of providing an adhesive and insulation layer between a propellant and a rocket motor case.

2. A rocket motor liner composition as defined in claim 1 further comprising from about 0.01% to about 0.5% dibutyltin dilaurate.

3. A rocket motor liner composition as defined in claim 1 wherein said polymer comprises polythioglycol.

4. A rocket motor liner composition as defined in claim 1 wherein said curing agent is an isocyanate curing agent selected from the group consisting of toluene diisocyanate, methylene bis di phenyl isocyanate, hexamethylene diisocyanate, dimer diisocyanate, isophorone diisocyanate, and tetramethylxylene diisocyanate.

5. A rocket motor liner composition consisting essentially of:

from about 50% to about 75% polymer selected from the group consisting of polyethers, polyglycols, polyesters, polyamides, and polycarbonates;

from about 3% to about 15% isocyanate curing agent; and

from about 5% to about 50% filler selected from the group consisting of dicyandiamide, ammonium nitrate, and silica;

wherein said composition is formulated such that it is capable of providing an adhesive and insulation layer between a propellant and a rocket motor case.