Non-provisional patent application for a projectile

Abstract

The subject application is directed to a projectile apparatus and method for use of the same, wherein the apparatus has a first tubular component formed with a lumen and defines an axis, wherein the first component has an open end and a closed end, a second component engaged with the first component to create an assembly, wherein the assembly provides for a sliding axial movement of the second component in the lumen of the first tubular component, and the assembly establishes a gas-filled compression chamber in the lumen of the first component between the second component and the closed end of the first component, a payload mounted on a selected component of the assembly, and a release valve for regulating the gas-filled compression chamber for safety purposes.

1 . A projectile apparatus comprising:
 a first tubular component formed with a lumen and defines an axis, wherein the first component has an open end and a closed end;   a second component engaged with the first component to create an assembly,   wherein the assembly provides for a sliding axial movement of the second component in the lumen of the first tubular component, and the assembly establishes a gas-filled compression chamber in the lumen of the first component between the second component and the closed end of the first component;   a payload mounted on a selected component of the assembly; and   a release valve for regulating the gas-filled compression chamber.   
     
     
         2 . The projectile of  claim 1 , further comprising a launcher for generating an axially-directed driving force on the assembly to propel the assembly from the launcher and onto a flight path in the axial direction with an initial relative movement between the first component and the second component to compress gas in the compression chamber and generate potential energy in the compressed gas for use in separating the payload from the assembly in flight. 
     
     
         3 . The projectile of  claim 2 , wherein, during an initial acceleration of the assembly by the driving force, a first kinetic energy is generated for the first component and a second kinetic energy is generated for the second component of the assembly, and a potential energy is generated for the gas in the gas-filled chamber of the assembly. 
     
     
         4 . The projectile of  claim 3 , wherein, after the initial acceleration of the assembly, the potential energy of the gas is transferred into kinetic energy with an expansion of the gas to accelerate the payload for separation of the payload from the assembly and to decelerate any remainder of the separated assembly. 
     
     
         5 . The projectile of  claim 1 , further comprising a pump for filling the gas-filled compression chamber, wherein the pump is attached to the projectile such that only the pump can fill the gas-filled compression chamber. 
     
     
         6 . The projectile of  claim 5 , wherein the pump is configured for filling the gas-filled compression chamber up to three-hundred pounds-force per square inch. 
     
     
         7 . The projectile of  claim 1 , wherein the release valve for regulating the gas-filled compression chamber is configured to release pressured air exceeding three-hundred pounds-force per square inch. 
     
     
         8 . The projectile of  claim 1 , wherein the second component is a cartridge for holding the payload, and the driving force is generated on the first component, and the payload is separated from the second component, in flight. 
     
     
         9 . The projectile of  claim 1 , wherein the payload is mounted on the first component and the driving force is applied to the second component. 
     
     
         10 . The projectile of  claim 1  wherein the launcher is man-powered, and selected from the group consisting of a vertical bow, a crossbow, a compound bow, a longbow, and combinations thereof. 
     
     
         11 . The projectile of  claim 1 , further comprising a compression spring in communication with the first tubular component and/or second component, wherein the compression spring acts to communicate a change in a pressure of gas in the gas-filled compression chamber. 
     
     
         12 . The projectile of  claim 11 , wherein the change in a pressure of gas in the gas-filled compression chamber corresponds with an expansion or contraction of the second component housed in the first tubular component. 
     
     
         13 . The projectile of  claim 12 , wherein the expansion or contraction of the second component housed in the first tubular component is measured from zero to one eighth of an inch as pressure increases from zero pounds-force per square inch to two-hundred and fifty pounds-force per square inch. 
     
     
         14 . A method for employing a projectile, the method comprising:
 providing a projectile, the projectile comprising:
 a first tubular component formed with a lumen and defines an axis, wherein the first component has an open end and a closed end; 
 a second component engaged with the first component to create an assembly, 
 wherein the assembly provides for a sliding axial movement of the second component in the lumen of the first tubular component, and the assembly establishes a gas-filled compression chamber in the lumen of the first component between the second component and the closed end of the first component; 
 a payload mounted on a selected component of the assembly; and 
 a release valve for regulating the gas-filled compression chamber, 
   providing a launcher configured to launch the projectile;   inserting the projectile onto the launcher; and   enacting the launcher to launch the projectile.   
     
     
         15 . The method of  claim 14 , wherein, after enactment, the launcher generates an axially-directed driving force on the assembly to propel the assembly from the launcher and onto a flight path in the axial direction with an initial relative movement between the first component and the second component to compress gas in the compression chamber and generate potential energy in the compressed gas for use in separating the payload from the assembly in flight. 
     
     
         16 . The method of  claim 15 , wherein, after enactment, an initial acceleration of the assembly by the driving force, a first kinetic energy is generated for the first component and a second kinetic energy is generated for the second component of the assembly, and a potential energy is generated for the gas in the gas-filled chamber of the assembly. 
     
     
         17 . The method of  claim 14 , further comprising a pump for filling the gas-filled compression chamber, wherein the pump is attached to the projectile such that only the pump can fill the gas-filled compression chamber. 
     
     
         18 . The method of  claim 17 , wherein filing the gas-filled compression chamber with the pump is limited to three-hundred pounds-force per square inch. 
     
     
         19 . The method of  claim 14 , wherein the release valve for regulating the gas-filled compression chamber releases pressured air when the pressurized air exceeds three-hundred pounds-force per square inch, 
     
     
         20 . The method of  claim 14 , wherein the projectile further comprises a compression spring in communication with the first tubular component and/or second component, wherein the compression spring communicates a change in a pressure of gas in the gas-filled compression chamber.