Solid-fuel rocket propellants comprising an oxidizer, an oxophilic metal-halophilic metal formulation, and a binder are described herein. Further described are processes for preparing such propellants and methods of reducing hydrogen chloride production via the combustion of such propellants. Non-li
Solid-fuel rocket propellants comprising an oxidizer, an oxophilic metal-halophilic metal formulation, and a binder are described herein. Further described are processes for preparing such propellants and methods of reducing hydrogen chloride production via the combustion of such propellants. Non-limiting examples of such formulations include aluminum-lithium alloys.
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1. A solid-rocket propellant comprising an aluminum-lithium alloy, aluminum, an oxidizer, and a binder wherein the ratio of lithium to aluminum in the alloy is between 17% and about 34% by weight. 2. The solid-rocket propellant of claim 1, wherein the alloy is crystalline. 3. The solid-rocket propel
1. A solid-rocket propellant comprising an aluminum-lithium alloy, aluminum, an oxidizer, and a binder wherein the ratio of lithium to aluminum in the alloy is between 17% and about 34% by weight. 2. The solid-rocket propellant of claim 1, wherein the alloy is crystalline. 3. The solid-rocket propellant of claim 2, wherein the crystalline phase of the alloy is simple cubic. 4. The solid-rocket propellant of claim 1, wherein the amount of aluminum-lithium alloy in the propellant is between about 5% and about 40% by weight, the amount of oxidizer is between about 55% and about 79% by weight, and the amount of binder is between about 5% and about 25% by weight. 5. The solid-rocket propellant of claim 4, wherein the amount of aluminum-lithium alloy in the propellant is between about 20% and about 40% by weight, the amount of oxidizer is between about 55% and about 65% by weight, and the amount of binder is from about 8% to about 15%. 6. The solid-rocket propellant of claim 1, further comprising an additive. 7. The solid-rocket propellant of claim 6, wherein the additive is a high explosive, a catalyst, a burn-rate modifier, or a combination thereof. 8. The solid-rocket propellant of claim 1, wherein the oxidizer is ammonium perchlorate, and the binder is hydroxyl-terminated polybutadiene, carboxyl terminated polybutadiene, Polybutadiene acrylonitrile, dicyclopentadiene, Polyurethane, Plasticized nitrocellulose, Glycidyl Azide polymers, oxetane polymers, oxirane polymers, bis-azidomethyloxetane/azideomethylmethyloxetane or combinations thereof. 9. The solid-rocket propellant of claim 5, wherein the oxidizer is ammonium perchlorate, and the binder is hydroxyl-terminated polybutadiene, carboxyl terminated polybutadiene, Polybutadiene acrylonitrile, dicyclopentadiene, Polyurethane, Plasticized nitrocellulose, Glycidyl Azide polymers, oxetane polymers, oxirane polymers, bis-azidomethyloxetane/azideomethylmethyloxetane or combinations thereof and wherein the alloy is crystalline. 10. The solid-rocket propellant of claim 1, wherein the ratio of lithium to aluminum in the propellant is between about 14% and 24% by weight. 11. The solid-rocket propellant of claim 10, wherein the ratio of lithium to aluminum is between about 16% and 18% by weight and the alloy is crystalline. 12. The solid-rocket propellant of claim 11, wherein the oxidizer is ammonium perchlorate and the binder is hydroxyl-terminated polybutadiene, carboxyl terminated polybutadiene, Polybutadiene acrylonitrile, dicyclopentadiene, Polyurethane, Plasticized nitrocellulose, Glycidyl Azide polymers, oxetane polymers, oxirane polymers, bis-azidomethyloxetane/azideomethylmethyloxetane or combinations thereof. 13. The solid-rocket propellant of claim 1, wherein the ratio of lithium to aluminum is between about 19% and about 21% by weight and the alloy is crystalline. 14. The solid-rocket propellant of claim 13, wherein the oxidizer is ammonium perchlorate and the binder is hydroxyl-terminated polybutadiene, carboxyl terminated polybutadiene, Polybutadiene acrylonitrile, dicyclopentadiene, Polyurethane, Plasticized nitrocellulose, Glycidyl Azide polymers, oxetane polymers, oxirane polymers, bis-azidomethyloxetane/azideomethylmethyloxetane or combinations thereof. 15. A solid-rocket propellant comprising an aluminum-lithium alloy, wherein the ratio of lithium to aluminum in the alloy is between 17% and about 34% by weight, an oxidizer, and a binder. 16. The solid-rocket propellant of claim 15, further comprising neat aluminum. 17. The solid-rocket propellant of claim 16, wherein the alloy is crystalline. 18. The solid-rocket propellant of claim 17, wherein the crystalline phase of the alloy is simple cubic. 19. The solid-rocket propellant of claim 15, wherein the amount of aluminum-lithium alloy in the propellant is between about 5% and about 40% by weight, the amount of oxidizer is between about 55% and about 79% by weight, and the amount of binder is between about 5% and about 25% by weight. 20. The solid-rocket propellant of claim 19, wherein the amount of aluminum-lithium alloy in the propellant is between about 20% and about 40% by weight, the amount of oxidizer is between about 55% and about 65% by weight, and the amount of binder is from about 8% to about 15%. 21. The solid-rocket propellant of claim 15, further comprising an additive. 22. The solid-rocket propellant of claim 21, wherein the additive is a high explosive, a catalyst, a burn-rate modifier, or a combination thereof. 23. The solid-rocket propellant of claim 15, wherein the oxidizer is ammonium perchlorate, and the binder is hydroxyl-terminated polybutadiene, carboxyl terminated polybutadiene, Polybutadiene acrylonitrile, dicyclopentadiene, Polyurethane, Plasticized nitrocellulose, Glycidyl Azide polymers, oxetane polymers, oxirane polymers, bis-azidomethyloxetane/azideomethylmethyloxetane or combinations thereof. 24. The solid-rocket propellant of claim 20, wherein the oxidizer is ammonium perchlorate, and the binder is hydroxyl-terminated polybutadiene, carboxyl terminated polybutadiene, Polybutadiene acrylonitrile, dicyclopentadiene, Polyurethane, Plasticized nitrocellulose, Glycidyl Azide polymers, oxetane polymers, oxirane polymers, bis-azidomethyloxetane/azideomethylmethyloxetane or combinations thereof and wherein the alloy is crystalline. 25. The solid-rocket propellant of claim 16, wherein the ratio of lithium to aluminum in the propellant is between about 14% and 24% by weight. 26. The solid-rocket propellant of claim 25, wherein the ratio of lithium to aluminum is between about 16% and 18% by weight and the alloy is crystalline. 27. The solid-rocket propellant of claim 26, wherein the oxidizer is ammonium perchlorate and the binder is hydroxyl-terminated polybutadiene, carboxyl terminated polybutadiene, Polybutadiene acrylonitrile, dicyclopentadiene, Polyurethane, Plasticized nitrocellulose, Glycidyl Azide polymers, oxetane polymers, oxirane polymers, bis-azidomethyloxetane/azideomethylmethyloxetane or combinations thereof. 28. The solid-rocket propellant of claim 16, wherein the ratio of lithium to aluminum is between about 19% and about 21% by weight and the alloy is crystalline. 29. The solid-rocket propellant of claim 28, wherein the oxidizer is ammonium perchlorate and the binder is hydroxyl-terminated polybutadiene, carboxyl terminated polybutadiene, Polybutadiene acrylonitrile, dicyclopentadiene, Polyurethane, Plasticized nitrocellulose, Glycidyl Azide polymers, oxetane polymers, oxirane polymers, bis-azidomethyloxetane/azideomethylmethyloxetane or combinations thereof.
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이 특허에 인용된 특허 (8)
Scheffee Robert S. ; Wheatley Brian K., Gas-generative composition consisting essentially of ammonium perchlorate plus a chlorine scavenger and an organic fuel.
Lund Gary K. (Ogden UT) Spinti Mark J. (Salt Lake City UT) Doll Daniel W. (North Ogden UT), Solid propellant formualtions producing acid neutralizing exhaust.
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