Ambient Cured Smokeless Liner/Inhibitor for Propellants.
DEPARTMENT OF THE ARMY WASHINGTON DC
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A liner composition is employed as a linerinhibitor for a solid propellant grain while functioning as a liner-binder between the propellant grain and insulation or the motor case. The liner and inhibitor composition is prepared from the conventional binder systems e.g., hydroxy terminated polybutadiene HTPB, polysulfide, polyurethane, and polyester. The composition employs a cool burning oxidizer selected from oxamide and nitroguanidine. The type of solid propellant grain, particularly the crosslinking or reaction mechanism to form a chemical bond between the binder of the liner composition and the binder of the propellant, dictates the type formulation of the linerinhibitor composition. A representative linerinhibitor for a HTPB propellant grain contains from about 10 to about 70 weight percent oxidizer, from about 0.1 to about 1.0 weight percent cure catalyst selected from ferric acetyl acetonate and triphenyl bismuth, an isocyanate curing agent selected from toluene diisocyanate, hexamethylene diisocyanate, and isophorone diisocyanate from about 1 to about 10 weight percent, and the balance of formulation hydroxy terminated polybutadiene. The use of the proper cure catalyst will produce a cured system at ambient 70 F. or higher in 24 hours. Author
- Solid Propellant Rocket Engines
- Solid Rocket Propellants