Additive for solid rocket motor having perchlorate oxidizer

Patent metadata

Field	Value
Publication number	US-11023884-B2
Application number	US-201615762785-A
Country	US
Kind code	B2
Filing date	Nov 15, 2016
Priority date	Nov 18, 2015
Publication date	Jun 1, 2021
Grant date	Jun 1, 2021

Abstract

A method for enhanced validation of an entity associated with a COF token includes: storing at least transaction data, a token requester identifier (TRJD), and a COF token identifier; receiving payment credentials, wherein the payment credentials include at least a COF-specific payment token; generating a transaction message, wherein the transaction message is formatted based on one or more standards and includes at least a plurality of data elements including at least a first data element configured to store the COF-specific payment token, a second data element configured to store the COF token identifier, a third data element configured to store the TRID, and one or more additional data elements configured to store the transaction data; and electronically transmitting the generated transaction message to a financial institution via a payment network.

First claim

What is claimed is:

1. A solid rocket motor comprising:
a fuel;
a binder;
a perchlorate oxidizer that is thermally decomposable to perchlorate decomposition products; and
a salt compound that is reactive with one or more of the perchlorate decomposition products, wherein the salt compound is selected from the group consisting of sulfite, phosphite, borate, borite, perborate, and combinations thereof, and wherein there is a total combined weight of the fuel, the binder, the perchlorate oxidizer, and the salt compound, and the salt compound is 1% to 10% of the total combined weight.

2. The solid rocket motor as recited in claim 1 , wherein the metal of the metal salt is thermodynamically favored to react spontaneously with one or more of the perchlorate decomposition products.

3. The solid rocket motor as recited in claim 1 , wherein the salt compound is 1% to 5% of the total combined weight.

4. The solid rocket motor as recited in claim 1 , wherein the binder is hydroxyl-terminated polybutadiene, the perchlorate oxidizer includes at least one of ammonium perchlorate, sodium perchlorate, or potassium perchlorate, and the fuel includes at least one of aluminum, magnesium, or boron-based salts.

5. A solid rocket motor comprising:
a fuel;
a binder;
a perchlorate oxidizer that is thermally decomposable to perchlorate decomposition products; and
an additive that is thermodynamically favored to react spontaneously with one or more of the perchlorate decomposition products, wherein the additive is a salt compound selected from the group consisting of borate, borite, perborate, and combinations thereof, there is a total combined weight of the fuel, the binder, the perchlorate oxidizer, and the salt compound, and the salt compound is 1% to 10% of the total combined weight.

6. The solid rocket motor as recited in claim 5 , wherein there is a total combined weight of the fuel, the binder, the perchlorate oxidizer, and the salt compound, and the salt compound is 0.1% to 20% of the total combined weight.

7. A method for testing stability of a solid rocket motor, the method comprising:
gradually increasing an environment temperature around a solid rocket motor, wherein the solid rocket motor includes a fuel, a binder, a perchlorate oxidizer that is thermally decomposable to perchlorate decomposition products, and a salt compound that is reactive with one or more of the perchlorate decomposition products, wherein the salt compound is selected from the group consisting of sulfite, phosphite, borate, borite, perborate, and combinations thereof, there is a total combined weight of the fuel, the binder, the perchlorate oxidizer, and the salt compound, and the salt compound is 1% to 10% of the total combined weight; and
measuring at least one of i) the environment temperature at which the solid rocket motor burns, explodes, or detonates or ii) a time period at which the solid rocket motor burns, explodes, or detonates from the gradual increasing of the environment temperature.

8. The method as recited in claim 7 , wherein the binder is hydroxyl-terminated polybutadiene, the perchlorate oxidizer includes at least one of ammonium perchlorate, sodium perchlorate, or potassium perchlorate, and the fuel includes at least one of aluminum, magnesium, or boron-based salt.

9. The solid rocket motor as recited in claim 1 , wherein the salt is sulfite.

10. The solid rocket motor as recited in claim 1 , wherein the salt is phosphite.

11. The solid rocket motor as recited in claim 1 , wherein the salt is selected from the group consisting of borate, borite, perborate, and combinations thereof.

Assignees

• Aerojet Rocketyne Inc
• Aerojet Rocketdyne Inc

Inventors

• Dawley Scott K
• Doll Daniel

Classifications

• C06B23/001 Primary

  Fillers, gelling and thickening agents (e.g. fibres) , absorbents for nitroglycerine (binders, plasticisers for propellants C06B45/10; crosslinking or curing agents C06B45/10) · CPC title

• C06D5/06

  by reaction of two or more solids · CPC title

• G06Q20/38215

  Use of certificates or encrypted proofs of transaction rights · CPC title

• G06Q20/351 Primary

  Virtual cards · CPC title

• G06Q20/12

  specially adapted for electronic shopping systems · CPC title