Solid propellant additive manufacturing method and system

Patent metadata

Field	Value
Publication number	US-10287218-B2
Application number	US-201615232339-A
Country	US
Kind code	B2
Filing date	Aug 9, 2016
Priority date	Aug 9, 2016
Publication date	May 14, 2019
Grant date	May 14, 2019

Abstract

A method of additively manufacturing propellant elements, such as for rocket motors, includes partially curing a propellant mixture before extruding or otherwise dispensing the material, such that the extruded propellant material is deposited on the element in a partially-cured state. The curing process for the partially-cured extruded material may be completed shortly after the material is put into place, for example by the material being heated at or above its cure temperature, such that it finishes curing before it fully cools. The propellant material may be prepared by first mixing together, a fuel, an oxidizer, and a binder, such as in an acoustic mixer. After that mixing a curative may be added to the mixture. The propellant mixture may then be directed to an extruder (or other dispenser), in which the mixture is heated to or above a cure temperature prior to the deposition, and then deposited.

First claim

What is claimed is:

1. A method of additively manufacturing a propellant element, the method comprising:
mixing together fuel, oxidizer, and a binder, to form a propellant mixture;
after the mixing, adding a curative to the propellant material to produce a curable propellant mixture;
after the adding the curative, partially curing the curable propellant mixture; and
after the partially curing, dispensing the curable propellant mixture as part of the propellant element;
wherein the mixing, the adding, the partially curing, and the dispensing are all parts of a continuous process, with material proceeding from one step directly to subsequent steps; and
wherein the partially curing includes heating the curable propellant mixture above a cure temperature of the curable propellant mixture.

2. The method of claim 1 , wherein the mixing includes mixing the fuel, the oxidizer, and the binder in an acoustic mixer, to produce the propellant mixture.

3. The method of claim 2 , wherein the adding the curative occurs in a second mixer, downstream from the acoustic mixer.

4. The method of claim 1 , further comprising heating the propellant mixture after the adding the curative to produce a curable propellant mixture, and before the dispensing.

5. A method of additively manufacturing a propellant element, the method comprising:
mixing together fuel, oxidizer, and a binder, to form a propellant mixture;
after the mixing, adding a curative to the propellant material to produce a curable propellant mixture;
after the adding the curative, partially curing the curable propellant mixture; and
after the partially curing, dispensing the curable propellant mixture as part of the propellant element;
wherein the partially curing includes heating the curable propellant mixture above a cure temperature of the curable propellant mixture;
wherein the heating includes heating the curable propellant mixture prior to the dispensing, such that the curing of the curable propellant mixture is completed while the curable propellant mixture cools after the dispensing; and
wherein the mixing, the adding, and the dispensing are all parts of a continuous process, with material proceeding from one step directly to subsequent steps.

6. The method of claim 1 , wherein the heating includes heating the propellant mixture to a constant temperature that is above the cure temperature of the curable propellant material.

7. The method of claim 1 , wherein the heating includes heating the propellant mixture to time-varying temperatures that are above the cure temperature.

8. The method of claim 1 , wherein the partially curing includes curing the curable propellant mixture at least 50% before the dispensing.

9. The method of claim 1 , wherein the partially curing includes curing the curable propellant mixture at least 90% before the dispensing.

10. The method of claim 1 , wherein the partially curing includes curing the curable propellant mixture at least 95% before the dispensing.

11. The method of claim 1 , wherein the dispensing includes extruding the curable propellant mixture.

12. The method of claim 1 , further comprising, after the dispensing, finishing curing of the curable propellant mixture, during build-up of the propellant piece.

Assignees

• Raytheon Co

Inventors

• Summers Matthew H
• Danforth Jeremy C
• Garrett David G
• Langhenry Mark T

Classifications

• C06B21/0008

  Compounding the ingredient · CPC title

• C06B21/0025 Primary

  the ingredient being a polymer bonded explosive or thermic component · CPC title

• B33Y10/00

  Processes of additive manufacturing · CPC title

• C06B21/0033

  Shaping the mixture · CPC title

• B29L2031/20

  Fuel-blocks, e.g. nuclear fuel elements · CPC title