The invention relates generally to burn rate modifiers and propellants comprising a burn rate modifier. The invention also relates to methods of producing a propellant comprising a burn rate modifier as well as an ammunition cartridge comprising the propellant. The burn rate modifier comprises a compound of formula 1 and the propellant comprises a compound of formula 1 and an energetic material. ##STR00001##

The invention relates generally to burn rate modifiers and propellants comprising a burn rate modifier. The invention also relates to methods of producing a propellant comprising a burn rate modifier as well as an ammunition cartridge comprising the propellant. The burn rate modifier comprises a compound of formula 1 and the propellant comprises a compound of formula 1 and an energetic material. ##STR00001##

The invention relates generally to burn rate modifiers, plasticizers and propellants comprising a burn rate modifier and/or a plasticizer. The invention also relates to methods of producing a propellant comprising a burn rate modifier and/or a plasticizer as well as an ammunition cartridge comprising the propellant. The burn rate modifier and/or plasticiser comprises a compound of formula (1) (Formula (1)) and the propellant comprises a compound of formula 1 and an energetic material. ##STR00001##

The invention relates generally to burn rate modifiers, plasticizers and propellants comprising a burn rate modifier and/or a plasticizer. The invention also relates to methods of producing a propellant comprising a burn rate modifier and/or a plasticizer as well as an ammunition cartridge comprising the propellant. The burn rate modifier and/or plasticiser comprises a compound of formula (1) (Formula (1)) and the propellant comprises a compound of formula 1 and an energetic material. ##STR00001##

A rocket propellant includes a hydrocarbon blend having a total aromatic compounds content less than 0.5 mass percent, a specific energy of at least 18.4 KBtu/lb, and a mass density of at least 0.8150 grams per cubic centimeter. The propellant, which can be prepared by blending a refined kerosene with an isoparaffin and/or a cycloparaffin, exhibits a high volumetric heat of combustion and excellent thermal stability. This combination of properties is especially useful for fueling reusable launch vehicles employing regenerative cooling of engine components.

A rocket propellant includes a hydrocarbon blend having a total aromatic compounds content less than 0.5 mass percent, a specific energy of at least 18.4 KBtu/lb, and a mass density of at least 0.8150 grams per cubic centimeter. The propellant, which can be prepared by blending a refined kerosene with an isoparaffin and/or a cycloparaffin, exhibits a high volumetric heat of combustion and excellent thermal stability. This combination of properties is especially useful for fueling reusable launch vehicles employing regenerative cooling of engine components.

The present disclosure is directed to a nitrocellulose-based propellant composition comprising: (a) a nitrate ester based propellant comprising nitrocellulose; and (b) a stabiliser consisting of a tocopherol compound with a general formula (I),

##STR00001##

wherein: X is oxygen; R.sup.1 is selected from the group consisting of hydrogen, alkyl, alkenyl, alkynyl, aryl, heteroaryl, carboxylic acid, carboxylate, ester, saccharide, alkoxy-linked saccharide, alcohol, and ethers; R.sup.2 is selected from the group consisting of hydrogen methyl, benzyl carboxylic acid, benzyl carboxylate, benzylester and saccharide; R.sup.3 is selected from the group consisting of hydrogen, methyl, benzyl carboxylic acid, benzyl carboxylate, benzylester and saccharide; R.sup.4 is selected from the group consisting of methyl, benzyl carboxylic acid, benzyl carboxylate, benzylester and saccharide; and R.sup.5 is selected from the group consisting of alkyl and alkenyl.

The present disclosure is directed to a nitrocellulose-based propellant composition comprising: (a) a nitrate ester based propellant comprising nitrocellulose; and (b) a stabiliser consisting of a tocopherol compound with a general formula (I),

##STR00001##

wherein: X is oxygen; R.sup.1 is selected from the group consisting of hydrogen, alkyl, alkenyl, alkynyl, aryl, heteroaryl, carboxylic acid, carboxylate, ester, saccharide, alkoxy-linked saccharide, alcohol, and ethers; R.sup.2 is selected from the group consisting of hydrogen methyl, benzyl carboxylic acid, benzyl carboxylate, benzylester and saccharide; R.sup.3 is selected from the group consisting of hydrogen, methyl, benzyl carboxylic acid, benzyl carboxylate, benzylester and saccharide; R.sup.4 is selected from the group consisting of methyl, benzyl carboxylic acid, benzyl carboxylate, benzylester and saccharide; and R.sup.5 is selected from the group consisting of alkyl and alkenyl.

The present disclosure is directed to a nitrocellulose-based propellant composition comprising: (a) a nitrate ester-based propellant comprising nitrocellulose; and (b) a stabiliser comprising a non-aromatic compound (12) consisting of a general ionone formula (12-I), (12-II), (12-III) or (12-IV):

##STR00001##

wherein le represents a ketone, hydroxyl, carboxyl, aldehyde or an unsaturated alkyl group, preferably C(O)CH.sub.3 (corresponding to alpha, beta, gamma and pseudo ionone).

The present disclosure is directed to a nitrocellulose-based propellant composition comprising: (a) a nitrate ester-based propellant comprising nitrocellulose; and (b) a stabiliser comprising a non-aromatic compound (12) consisting of a general ionone formula (12-I), (12-II), (12-III) or (12-IV):

##STR00001##

wherein le represents a ketone, hydroxyl, carboxyl, aldehyde or an unsaturated alkyl group, preferably C(O)CH.sub.3 (corresponding to alpha, beta, gamma and pseudo ionone).