# US 2019/0169083 A1 · Solid combustible propellant composition

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- Number: US 2019/0169083 A1
- Document ID: US20190169083A1
- Status: Published application
- Kind: A1
- Application number: 16/146,154
- Filed: 2018-09-28
- Published: 2019-06-06
- Earliest claimed: 2016-03-18
- Assignees: Goodrich Corporation
- Applicants: Goodrich Corporation
- Inventors: Karl G. Reimer; Jean C. Rodriguez
- Web page: https://patentgrep.com/patent/US20190169083A1

## CPC

- C06B 45/10: the organic component containing a resin
- C06B 21/0025: {the ingredient being a polymer bonded explosive or thermic component}
- C06B 43/00: Compositions characterised by explosive or thermic constituents not provided for in groups C06B25/00 - C06B41/00
- C06B: EXPLOSIVES OR THERMIC COMPOSITIONS (blasting F42D); MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES (compounds in general C01, C07 or C08; {demolition agents based on cementitious or like materials C04B41/0009})

## Abstract

A combustible solid propellant composition is disclosed that includes an oxidizer of the reaction product under vacuum of potassium periodate and isocyanate, a polymer binder, a plasticizer, and a fuel.

## Claims

### Claim 1

A method of making a solid combustible propellant composition, comprising
reacting potassium periodate with isocyanate under a vacuum; and
mixing the reaction product of the potassium periodate and isocyanate with a polymer binder, a plasticizer, and a fuel.

### Claim 2 (depends on 1)

The method of claim 1, further comprising reacting a polyol with a polyisocyanate to form the polymer binder.

### Claim 3 (depends on 2)

The method of claim 2, comprising reacting the polyol with the polyisocyanate in the presence of the potassium periodate.

### Claim 4 (depends on 2)

The method of claim 2, wherein the polyol, polyisocyanate, and potassium periodate are reacted together under vacuum.

### Claim 5 (depends on 2)

The method of claim 2, wherein the plasticizer comprises a nitrate ester plasticizer.

### Claim 6 (depends on 1)

The method of claim 1, wherein the vacuum is at a pressure of less than 20 mm Hg.

### Claim 7 (depends on 1)

The method of claim 1, wherein the vacuum is at a pressure of less than 5 mm Hg.

### Claim 8 (depends on 1)

The method of claim 1, wherein the oxidizer comprises potassium periodate particles with an outer surface that comprises the reaction product of potassium periodate and isocyanate.

### Claim 9 (depends on 1)

The method of claim 1, wherein the fuel comprises a metal powder.

### Claim 10 (depends on 1)

The method of claim 1, wherein the fuel comprises titanium hydride.

### Claim 11 (depends on 1)

The method of claim 1, wherein the fuel comprises a dodecaborate salt.

### Claim 12 (depends on 1)

The method of claim 1, wherein the fuel comprises boron.

### Claim 13 (depends on 1)

The method of claim 1, wherein the fuel comprises titanium hydride, a dodecaborate salt, and aluminum.

### Claim 14 (depends on 1)

The method of claim 1, wherein the solid combustible propellant composition comprises 40-72 wt. % oxidizer, 9-14.5 wt. % polymer binder, and 22-30 wt. % fuel, based on the total weight of the composition.

### Claim 15 (depends on 14)

The method of claim 14, wherein the oxidizer comprises 100 wt. % potassium periodate, based on the total weight of oxidizer.

### Claim 16 (depends on 1)

The method of claim 1, wherein the solid combustible propellant composition comprises 45-58 wt. % potassium periodate, 9.2-14.2 wt. % binder comprising the reaction product of a polyol and a polyisocyanate, 4-16.2 wt. % nitrate ester plasticizer, 0.4-12 wt. % aluminum, 5-20 wt. % titanium hydride, 1-15 wt. % dodecaborate salt, and 0-10 wt. % boron, based on the total weight of the composition.