초록 ▼

Solid propellant systems include a main propellant and a secondary propellant in contact with the first propellant that exhibits autoignition temperatures of at least about 100° F. lower than the autoignition temperature of the main propellant. The secondary propellant of the present invention is mo

Solid propellant systems include a main propellant and a secondary propellant in contact with the first propellant that exhibits autoignition temperatures of at least about 100° F. lower than the autoignition temperature of the main propellant. The secondary propellant of the present invention is most advantageously employed with conventional AP-containing solid propellant formulations as the main propellant, especially formulations containing both AP, an energetic solid, and a binder. In especially preferred forms, the secondary propellant will include a nitramine which is at least one selected from nitroguanidine (NQ), cyclotrimethylene trinitramine (RDX) and cyclotetramethylenetetranitramine (HMX), and a binder which is at least one selected from HTPB, HTPE or glycidyl azide polymer (GAP). Most preferably, the secondary propellant will include a combination of nitramines which includes NQ and one of RDX or HMX.

대표청구항 ▼

1. A rocket motor which comprises: (a) a motor casing,(b) a main propellant which contains ammonium perchlorate positioned in an interior space of said casing, and(c) a secondary propellant in localized contact with said main propellant and including (i) a nitramine and (ii) a binder in amounts suff

1. A rocket motor which comprises: (a) a motor casing,(b) a main propellant which contains ammonium perchlorate positioned in an interior space of said casing, and(c) a secondary propellant in localized contact with said main propellant and including (i) a nitramine and (ii) a binder in amounts sufficient to exhibit an autoignition temperature which is at least about 100° C. lower than the autoignition temperature of the main propellant. 2. The rocket motor as in claim 1, wherein said secondary propellant is in the form of a circumferential ring near said motor casing in contact with said main propellant. 3. The rocket motor as in claim 2, wherein said circumferential ring is disposed substantially midway of said motor casing. 4. The rocket motor of claim 3, wherein said nitramine of said secondary propellant includes nitroguanidine (NQ) and at least one of cyclotrimethylenetrinitramine (RDX), and cyclotetramethylene tetranitramine (HMX). 5. The rocket motor of claim 1 or 4, wherein said binder is selected from at least one of hydroxyl-terminated polybutadiene (HTPB) and glycidyl azide polymer (GAP). 6. The rocket motor of claim 5, wherein said nitramine is present in an amount between about 50 to about 95 wt. %. 7. The rocket motor of claim 6, wherein said binder is present in an amount between about 10 to about 35 wt. %. 8. A rocket motor which comprises a generally tubular motor casing defining an interior space, and a solid rocket motor comprising (a) a main propellant which contains ammonium perchlorate, and (b) a secondary propellant in localized contact with said main propellant and including (i) a nitramine system consisting essentially of nitroguanidine (NQ) and at least one of cyclotrimethylenetrinitramine (RDX) and cyclotetramethylene tetranitramine (HMX), and (ii) a binder system which consists essentially of hydroxyl-terminated polybutadiene (HTPB) and glycidyl azide polymer (GAP).