US2012318123A1PendingUtilityA1

Muzzle Loader Powder Increment using Celluloid Combustible Container

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Assignee: WORRELL WILLIAM JPriority: Jun 14, 2011Filed: Jun 14, 2011Published: Dec 20, 2012
Est. expiryJun 14, 2031(~4.9 yrs left)· nominal 20-yr term from priority
F42B 5/188F42B 30/12F42B 5/192F42B 5/38F42B 5/18
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Claims

Abstract

An encapsulated propellant charge comprised a sealed combustible container comprised of a consumable material and having a substantially cylindrical shape. The sealed combustible container comprises a top wall, a bottom wall, and a side wall therebetween. The top wall, the bottom wall and the side wall define a chamber; which contains a propellant composition.

Claims

exact text as granted — not AI-modified
1 . A propellant charge comprising a sealed combustible container comprised of a consumable material and having a generally cylindrical shape, the sealed combustible container comprising a top wall, a bottom wall, and a side wall therebetween; the top wall, the bottom wall and the side wall defining a chamber; wherein the chamber contains a measured amount of propellant composition, wherein the propellant composition is a different material than the consumable material. 
     
     
         2 . The propellant charge of  claim 1 , wherein the consumable material is a foamed celluloid. 
     
     
         3 . The propellant charge of  claim 1 , wherein the side wall has a thickness of less than 0.05 inches. 
     
     
         4 . The propellant charge of  claim 1 , wherein the propellant composition is selected from the group consisting of: smokeless propellant, single base nitrocellulose, nitrocellulose propellant, black powder propellant, pyrotechnic propellant, non-pyrotechnic propellant, and any combination thereof. 
     
     
         5 . The propellant charge of  claim 1 , wherein the sealed combustible container has a length that is greater than its diameter. 
     
     
         6 . The propellant charge of  claim 5 , wherein the ratio of the length of the sealed combustible container to the diameter of the sealed combustible container is at least 2:1. 
     
     
         7 . The propellant charge of  claim 5 , wherein the ratio of the length of the sealed combustible container to the diameter of the combustible is at least 3:1. 
     
     
         8 . The propellant charge of  claim 1 , wherein the consumable material is water resistant. 
     
     
         9 . A muzzle-loader ammunition round comprising:
 a bullet held in place with a sabot; and   at least one propellant charge engaged with the sabot, the at least one propellant charge having an outer wall constructed from a consumable material, the outer wall defining a chamber that is at least partially filled with at least one propellant composition having a charge weight, wherein the propellant composition is a different material than the consumable material.   
     
     
         10 . The propellant charge of  claim 1 , wherein the outer wall is water resistant. 
     
     
         11 . The propellant charge of  claim 1 , wherein the consumable material is a foamed celluloid. 
     
     
         12 . The propellant charge of  claim 1 , wherein the propellant composition is selected from the group consisting of smokeless propellant, single base nitrocellulose, nitrocellulose propellant, black powder propellant, pyrotechnic propellant, non-pyrotechnic propellant, and any combination thereof. 
     
     
         13 . A method of manufacturing a propellant charge comprising:
 forming a cylinder of a desired diameter from a sheet of consumable material, the sheet having sides and ends, wherein the sides of the sheet are adhered to each other and the cylinder has an open end;   at least partially filling a chamber defined by the cylinder with a propellant composition;   sealing the open end of the cylinder by adhering a circular disc to the open end.   
     
     
         14 . The method of  claim 12 , wherein the consumable material is a foamed celluloid. 
     
     
         15 . The method of  claim 12 , wherein the propellant composition is selected from the group consisting of: smokeless propellant, single base nitrocellulose, nitrocellulose propellant, black powder propellant, pyrotechnic propellant, non-pyrotechnic propellant, and any combination thereof.

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