High energy propellant with reduced pollution
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IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
C06B-045/08
C06B-045/10
출원번호
US-0449883
(2003-05-22)
발명자
/ 주소
Reed, Jr., Russell
Ciaramitaro, David A.
출원인 / 주소
The United States of America as represented by the Secretary of Navy
대리인 / 주소
Haley Charlene A.
인용정보
피인용 횟수 :
0인용 특허 :
3
초록▼
This invention relates to energetic compositions, which offer increased performance in conjunction with a total absence of hydrogen chloride in the combustion products. The formulation avoids the use of halogen based oxidizers to prevent the formation of halogen based byproducts. The formulations di
This invention relates to energetic compositions, which offer increased performance in conjunction with a total absence of hydrogen chloride in the combustion products. The formulation avoids the use of halogen based oxidizers to prevent the formation of halogen based byproducts. The formulations disclosed herein use ammonium dinitramide as a primary oxidizer, which is a more energetic molecule than ammonium perchlorate. The solid propellant formulations disclosed herein comprise about 5 to about 10 weight % of at least one energetic binder, about 20 to about 35 weight % of an energetic plasticizer; about 25 to about 45 weight % of ammonium dinitramide as a primary oxidizer; about 0 to about 20 weight % of particulate aluminum having a particle size of about 1 μm to about 60 μm; and about 0 to about 20 weight % of ultrafine aluminum having a particle size of less than 1 μm.
대표청구항▼
1. A solid propellant formulation comprising:about 5 to about 10 weight % of at least one energetic binder;about 20 to about 35 weight % of an energetic plasticizer;about 25 to about 45 weight % of ammonium dinitramide as a primary oxidizer;about 10 to about 20 weight % of a metal fuel, wherein said
1. A solid propellant formulation comprising:about 5 to about 10 weight % of at least one energetic binder;about 20 to about 35 weight % of an energetic plasticizer;about 25 to about 45 weight % of ammonium dinitramide as a primary oxidizer;about 10 to about 20 weight % of a metal fuel, wherein said metal fuel comprises particulate aluminum having a particle size of about 1 μm to about 60 μm and ultrafine aluminum having a particle size of less than 1 μm. 2. The solid propellant formulation of claim 1, wherein said energetic plasticizer is selected from the group consisting of butanetriol trinitrate, triethylene glycol dinitrate, nitroglycerine, glycidyl azide polymer terminated with azide, bis-(2,2-dinitropropyl) acetal/formal and butyl nitratoethylnitramine. 3. The solid propellant formulation of claim 1, wherein said energetic plasticizer is butanetriol trinitrate. 4. The solid propellant formulation of claim 1, wherein said energetic binder is selected from the group consisting of glycidyl azide polymer, a copolymer of (bis-azidoethyl) oxetane with (3-nitratomethyl-3-methyl) oxetane, 3-azidomethyl-3-methyl oxetane, bis-(nitratomethyl) oxetane, polyglycidyl nitrate, polypropylene glycol, hydroxy-terminated polycaprolactones, hydroxy-terminated polyesters, hydroxy-terminated polyethers, hydroxy-terminated polycaprolactone ether and hydroxy-terminated polyalkylene oxide. 5. The solid propellant formulation of claim 1, wherein said energetic binder is a hydroxy-terminated polyalkylene oxide having a molecular weight of about 24,000 daltons. 6. The solid propellant formulation of claim 1, wherein said metal fuel comprises about 10 weight % of said particulate aluminum having a particle size of about 1 μm to about 60 μm; andabout 10 weight % of said ultrafine aluminum having a particle size of less than 1 μm. 7. The solid propellant formulation of claim 1, further comprising at least one member selected from a curative, a crosslinker, a stabilizer, a cure catalyst, a bum rate catalyst, a bum rate modifier, an opacifier and a bonding agent. 8. The solid propellant formulation of claim 6, wherein said crosslinker is selected from the group consisting of hexamethylene diisocyanate, isophorone diisocyanate, toluene diisocyanate and polymeric hexamethylene diisocyanate. 9. The solid propellant formulation of claim 6, wherein said bum rate catalyst is aluminum oxide. 10. The solid propellant formulation of claim 6, wherein said cure catalyst is selected from the group consisting of triphenyl bismuth, triphenyltin chloride, dibutyltin diacetate, and dibutyltin dilaurate. 11. The solid propellant formulation of claim 6, wherein said curative is selected from the group consisting of hexamethylene diisocyanate, isophorone diisocyanate, toluene diisocyanate and the polymeric hexmethylene diisocyanate.
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이 특허에 인용된 특허 (3)
Lund Gary K. (Ogden UT) Highsmith Tom K. (North Ogden UT) Braithwaite Paul C. (Brigham City UT) Wardle Robert B. (Logan UT), Insensitive high performance explosive compositions.
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