Rocket motors having controlled autoignition propellant systems

Abstract

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.

Claims

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).

Description

BRIEF DESCRIPTION OF THE ACCOMPANYING DRAWINGS

(1) Reference will hereinafter be made to the accompanying drawing

(2) FIG. 1 which schematically depicts a cross-sectional view of a rocket motor which employs the controlled autoignition system of the present invention.

DETAILED DESCRIPTION OF THE INVENTION

(3) The accompanying drawing FIG. 1 depicts in schematic fashion a cross-sectional view of a rocket motor 10 which embodies the present invention. In this regard, as is conventional, the rocket motor includes an elongate, motor casing 12 (typically formed of a graphite-epoxy material) which has a generally tubular section between its forward and rearward ends so as to define a generally cylindrical interior space having a substantially circular cross-sectional configuration. The rear end of the motor casing 12 is closed by a rearward directed nozzle assembly 14. A solid main propellant is contained within the motor casing interior in a manner well known to those skilled in the art. In accordance with the present invention, a relatively narrow strip or ring of a secondary propellant 16 in contact with the main propellant 18, most preferably at about midway of the motor casing 12.

(4) The main propellant 18 is most preferably a conventional ammonium perchlorate (AP) based propellant which includes an inert binder HTPB, and optionally aluminum powder. In this regard, the AP will be present in the main propellant 18 in an amount between about 65-92 wt. % while the binder is present in amounts between about 8 to about 25 wt. %, based on the total weight of the main propellant composition. If present, the aluminum powder will typically be employed in amounts ranging from about 5 to about 20 wt. %, based on the total weight of the main propellant composition, in which case the AP is present in amounts preferably ranging from about 70 to about 85 wt. % with binder being employed as the balance of the composition weight.

(5) The secondary propellant strip 16 is most preferably in the form of a compressed mass of a powdered composition containing (i) at least one nitramine selected from nitroguanidine (NQ), cyclotrimethylenetrinitramine (RDX), and cyclotetramethylenetetranitramine (HMX), and (ii) a binder system selected from at least one of hydroxyl-terminated polybutadiene (HTPB), HTPE and glycidyl azide polymer (GAP). Most preferably, the nitramine will be present in the secondary propellant in an amount between about 50 to about 95 wt. %, and more preferably in an amount between about 65 to about 90 wt. %, and sometimes in amounts ranging from about 65 wt. % to about 75 wt. %, based on the total weight of the secondary propellant composition. In such compositions, the binder will be present as the balance of the composition, that is, typically between about 5 to about 50 wt. %, preferably between about 10 to about 35 wt. %, and sometimes between about 25 to about 35 wt. %, based on the total weight of the secondary propellant composition.

(6) Most preferably, the secondary propellant will include a combination of nitramines which includes NQ and one of RDX or HMX. In such preferred formulations, NQ will be present in the secondary propellant formulations in amount between about 30 to about 55 wt. %, and preferably between about 35 wt. % to about 50 wt. %, based on the total weight of the secondary propellant composition. The HMX or RDX components in such preferred formulations will be present in an amount ranging from 25 to about 50 wt. %, and preferably between about 30 to about 40 wt. %, based on the total weight of the secondary propellant composition. Especially preferred formulations in accordance with the present invention are shown below:

(7) TABLE-US-00001 Component Amt. (wt. %) Formulation A: NQ 40-50 HMX 35-40 HTPB Balance Formulation B: NQ 35-40 HMX 30-35 GAP Balance

(8) The present invention will be further described by reference to the following non-limiting Examples.

EXAMPLES

Example 1 (Comparative)

(9) A composite case measuring 5 inches by 10 inches long and being approximately 0.1 inch thick was loaded with a high energy composite propellant containing ammonium perchlorate, aluminum, HMX in a hydroxyl-terminated polybutadiene binder and having a 1-inch cylindrical bore. The loaded case was then subjected to slow cook-off testing at a temperature rise rate of 6° F. per hour. The motor exploded in a violent reaction 44 hours after the test was begun, and at a bore temperature of 380° F. The test hardware and oven were destroyed, and only tiny shred vestiges remained of the motor case.

Example 2 (Invention)

(10) Example 1 was repeated except that a 1-inch wide x. 0.1 inch thick mitigation strip of AFX-960 (HMX, nitroguanidine and HTPB) was placed between the motor case and the high-energy propellant. In the slow cook-off testing that ensued, the test item reacted at 35.7 hours after the test was begun and at a temperature of 297° F., yielding a burning-only type of reaction. The oven was opened and most of the metal test hardware was reusable. The case split into two major parts at the location of the mitigation strip.

Example 3 (Invention)

(11) Example 2 was repeated except that GAP-960 (HMX, nitroguanidine and GAP binder) was employed for the mitigation strip. Identical results to those obtained in Example 2 were obtained.

(12) While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not to be limited to the disclosed embodiment, but on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims.