Robust propellant liner and interfacial propellant burn rate con

Details Robust propellant liner and interfacial propellant burn rate con Robust propellant liner and interfacial propellant burn rate con

1998-04-16

1999-11-16

Bell, Janyce

Coating processes

Interior of hollow article coating

427214, 427215, 427216, 427221, 4274071, 427409, 4273855, 4273881, B05D 722

Patent

active

059853611

ABSTRACT:
A robust polyurethane liner is disclosed for solid propellant rocket motors which is insensitive to large variations in stoichiometry, exhibits increased cohesive strength and, when used in combination with a unique two coat (wet coat) liner process described below, modifies the ballistic properties of the adjacent interfacial propellant layer. The liner compositions include a polymeric binder having a plurality of reactive hydroxyl functional groups and a curing agent having a plurality of reactive isocyanate functional groups. The quantity of binder and curing agent is selected such that the NCO/OH ratio is in the range from 1.5 to 4.5. Diisocyanate curing agents are particularly useful. A bonding agent, such as a polyfunctional aziridine compound, is typically present in the liner composition in an amount ranging from about 3% to about 5%, by weight. An oligomer catalyst is included in the liner composition in an amount ranging from about 15% to about 50%, by weight. Diammonium phosphate ((NH.sub.4).sub.2 HPO.sub.4) functions as an oligomer catalyst and as a ballistic modifier to inhibit propellant burn rate when the liner is cured concurrently with the propellant. A colorant, such as rhodamine B, may optionally be included to assist in determining coverage or thickness of the liner coating.

REFERENCES:
patent: 4009130 (1977-02-01), Zimmerman et al.
patent: 4187215 (1980-02-01), Wrightson
patent: 4331871 (1982-05-01), Allinikov
patent: 4663196 (1987-05-01), Byrd et al.
patent: 5273785 (1993-12-01), Sinclair et al.

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