Solid propellants with biradical burning rate catalysts

Claim 2

A SOLID PROPELLANT COMPOSITION COMPRISING A BINDER, AN OXIDIZER, A BURNING RATE CATALYST SELECTED FROM THE BIRADICAL COMPOUNDS CONSISTING OF P, P''-BIPHENYLENE-BIS(DIPHENYLMETHYL) AND P, P''-PHENYLENE-BIS(DIPHENYLMETHYL), AND A CROSSLINKING AGENT.

Claim 3

The propellant composition of claim 1 wherein said binder is present in an amount from about 6 to about 23 percent by weight of said propellant composition, said binder being constituted of about 10.1 parts nitrocellulose, about 0.95 parts nitroglycerin, and about 0.20 parts of 2-nitrodiphenylamine; said oxidizer is cyclotetramethylenetetranitramine which is present in an amount from about 30 to about 50 percent by weight of said propellant composition; said catalyst selected is p, p''-biphenylene-bis(diphenylmethyl) which is present in an amount from about 2 to about 8 percent by weight of said propellant composition; said composition includes the plasticizer, triethylene glycol dinitrate in an amount from about 20 to about 35 percent by weight of said propellant composition and the plasticizer, butanetriol trinitrate in an amount from about 10 to about 20 percent by weight of said propellant composition; said propellant composition additionally includes an agent for stabilizing which is resorcinol which is present in an amount from about 0.5 to about 1.0 percent by weight of said propellant composition; and wherein said crosslinking agent is toluene diisocyanate which is added in an amount of about 1.0 percent by weight of the total weight of all the other propellant ingredients.

Claim 4

The proPellant composition of claim 2 wherein said binder is present in an amount of about 11.25 percent by weight of said propellant composition; said cyclotetramethylenetetranitramine is present in an amount of about 36 to about 40 percent by weight of said propellant composition; said triethylene glycol dinitrate is present in an amount of about 28.75 percent by weight of said propellant composition; said butanetriol trinitrate is present in an amount of about 15.5 percent by weight of said propellant composition; said p, p''-biphenylene-bis(diphenylmethyl) is present in an amount of about 4.0 percent by weight of said propellant composition; and said resorcinol is present in an amount of about 0.5 percent by weight of said propellant composition.

Claim 5

The propellant composition of claim 3 wherein said cyclotetramethylenetetranitramine is present in an amount of about 36 percent by weight of said propellant composition; and wherein said composition additionally contains the ballistic modifier, lead peroxide, in an amount of about 4.0 percent by weight of said propellant composition.

Claim 6

The propellant composition of claim 1 wherein said binder is hydroxyl-terminated polybutadiene which is present in an amount from about 7 to about 15 percent by weight of said propellant composition; said oxidizer is ammonium perchlorate which is present in an amount from about 65 to about 75 percent by weight of said propellant composition; said catalyst selected is p, p''-biphenylene-bis(diphenylmethyl) which is present in an amount from about 2 to about 8 percent by weight of said propellant composition; said crosslinking agent is dimeryl diisocyanate which is present in an amount from about 0.5 to about 2.0 percent by weight of said propellant composition; said composition contains a bonding agent formulated of equimolar quantities of tris(1-(2-methyl)-aziridinyl)phosphine oxide, tartaric acid, and adipic acid, said bonding agent is present in an amount from about 0.1 to about 0.3 percent by weight of said propellant composition; and wherein said propellant composition additionally contains aluminium metal fuel in an amount from about 5 to about 20 percent by weight of said propellant composition.

Claim 7

The propellant composition of claim 5 wherein said binder is present in an amount of about 9.84 percent by weight of said propellant composition; said ammonium perchlorate is present in an amount of about 71 percent by weight of said propellant composition; said p, p''-biphenylene-bis(diphenylmethyl) is present in an amount of about 2 percent by weight of said propellant composition; said dimeryl diisocyanate is present in an amount of about 1.92 percent by weight of said propellant composition; said bonding agent is present in an amount of about 0.24 percent by weight of said propellant composition; and said aluminium metal fuel is present in an amount of about 15 percent by weight of said propellant composition.

Claim 8

The propellant composition of claim 1 wherein said binder is carboxyl-terminated polybutadiene which is present in an amount from about 7 to about 15 percent by weight of said propellant composition; said oxidizer is ammonium perchlorate which is present in an amount from about 60 to about 70 percent by weight of said propellant composition; said catalyst selected is p, p''-biphenylene-bis(diphenylmethyl) which is present in an amount from about 2 to about 8 percent by weight of said propellant composition; said crosslinking agent is tris(1-(2-methyl)aziridinyl)-phosphine oxide which is present in an amount from about 0.5 to about 2.0 percent by weight of said propellant composition; said propellant composition includes aluminum metal fuel in an amount from about 5 to about 15 percent by weight of said propellant composition; and wherein said propellant composition additionally includes the curatives consisting of tris(oxiranyl)-para-aminophenol and iron linoleate which are each added to said propellant composition in an amount from about 0.1 to about 0.5 percent by weight of the total weight of all the other propellant ingredients.

Claim 9

The propellant composition of claim 7 wherein said binder is present in an amount of about 12.5 percent by weight of said propellant composition; said ammonium perchlorate is present in an amount of about 66 percent by weight of said perchlorate composition; said p, p''-biphenylene-bis(diphenylmethyl) is present in an amount of about 7 percent by weight of said propellant composition; said tris(1-(2-methyl)aziridinyl)phosphine oxide is present in an amount of about 0.5 percent by weight of said propellant composition; said aluminium metal fuel is present in an amount of about 14 percent by weight of said propellant composition; and said tris(oxiranyl)-para-aminophenol and iron linoleate are each present in an amount of about 0.1 percent by weight of all the other propellant ingredients.