[특허]Method of producing solid propellant element

Raytheon Company

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Method of producing solid propellant element

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	C06B-021/00 C06B-045/00 F02K-009/10 B29C-064/106 B33Y-010/00
출원번호	US-0057587 (2016-03-01)
등록번호	US-10023505 (2018-07-17)
발명자 / 주소	Danforth, Jeremy C. Summers, Matt H. Garrett, David G.
출원인 / 주소	Raytheon Company
대리인 / 주소	Renner, Otto, Boisselle & Sklar, LLP
인용정보	피인용 횟수 : 0 인용 특허 : 9

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A method of producing a propellant material element, such as an electrically-operated propellant material, includes extruding a propellant material through a heated nozzle. The nozzle may be heated to a temperature that is above the boiling point of a solvent that is part of the propellant material, yet is below a decomposition temperature of the propellant material. This allows some of the solvent to be driven off during the extruding process, while still preventing initiation of an energy-creating reaction within the material. The heating of the materi...

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1. A method of additively manufacturing a solid propellant element, the method comprising: heating a nozzle to produce a heated nozzle;extruding through the heated nozzle a propellant material that includes a fuel and a solvent, to form the solid propellant element;wherein the extruding occurs when the heated nozzle is at a temperature that is above a boiling point of the solvent and below a decomposition temperature of the propellant material;wherein the extruding removes some of the solvent from the propellant material;wherein the solvent is water and/or glycerol; andwherein the extruding through the heated nozzle removes some of the water and/or glycerol from the propellant material. 2. The method of claim 1, wherein the extruding includes extruding through a heated nozzle that is between 100 and 210 degrees C. 3. The method of claim 2, wherein the extruding includes extruding through a heated nozzle that is between 150 and 210 degrees C. 4. The method of claim 1, wherein the extruding includes directing the propellant material from a reservoir of the propellant material, to the heated nozzle. 5. The method of claim 4, wherein the directing includes using a stepper motor to control flow of the propellant material from the reservoir to the heated nozzle. 6. The method of claim 5, wherein the using includes using software to control the stepper motor. 7. The method of claim 1, wherein the propellant material is an electrically-operated propellant material; andwherein the extruding produces an electrically-operated solid propellant element as the solid propellant element. 8. The method of claim 1, wherein the extruding, by removing some of the solvent from the propellant material, makes the propellant material suitable for curing into the propellant element. 9. The method of claim 1, wherein the propellant element is built up in layers on a platform, by the extruding. 10. The method of claim 9, wherein the platform is a heated platform. 11. The method of claim 9, wherein the layers each have a thickness of on the order of 0.1 mm. 12. The method of claim 1, wherein the extruding is performed in a heated chamber. 13. A method of additively manufacturing a solid propellant element, the method comprising: heating a nozzle to produce a heated nozzle;extruding through the heated nozzle a propellant material that includes a solvent, to form the solid propellant element;embedding one or more devices in the propellant element during the extruding;wherein the extruding occurs when the heated nozzle is at a temperature that above a boiling point of the solvent and below a decomposition temperature of the propellant material; andwherein the extruding removes some of the solvent from the propellant material. 14. The method of claim 13, wherein the propellant material is an electrically-operated propellant material; andwherein the embedding includes embedding electrodes as at least some of the one or more devices. 15. A method of additively manufacturing a solid propellant element, the method comprising: heating a nozzle to produce a heated nozzle;extruding through the heated nozzle a propellant material that includes a solvent, to form the solid propellant element;prior to the heating and the extruding, mixing the propellant material, combining together a fuel, the solvent, an oxidizer, and a binder;wherein the extruding occurs when the heated nozzle is at a temperature that above a boiling point of the solvent and below a decomposition temperature of the propellant material;wherein the extruding removes some of the solvent from the propellant material; andwherein the mixing includes combining an excess amount of the solvent, beyond that that would be used to form a cast or molded cured propellant element. 16. A method of additively manufacturing a solid propellant element, the method comprising: heating a nozzle to produce a heated nozzle;extruding through the heated nozzle a propellant material that includes a solvent, to form the solid propellant element;wherein the extruding occurs when the heated nozzle is at a temperature that above a boiling point of the solvent and below a decomposition temperature of the propellant material;wherein the extruding removes some of the solvent from the propellant material; andwherein the extruding includes extruding the propellant material in a partially cured state. 17. The method of claim 16, wherein the solvent is water and/or glycerol; andwherein the extruding through the heated nozzle removes some of the water and/or glycerol from the propellant material. 18. The method of claim 16, wherein the extruding includes extruding through a heated nozzle that is between 100 and 210 degrees C. 19. The method of claim 16, wherein the extruding includes extruding through a heated nozzle that is between 150 and 210 degrees C. 20. The method of claim 15, wherein the solvent is water and/or glycerol; andwherein the extruding through the heated nozzle removes some of the water and/or glycerol from the propellant material.

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Method of producing solid propellant element

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Method of producing solid propellant element

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