Air as conventionally known is comprised of about 78% nitrogen and 21% oxygen with other trace gases such as carbon dioxide, neon, and hydrogen. Other gases (e.g. helium) and partial vacuums have both a lower density and a higher speed-of-sound from that of conventional air or even some highly utilized propellant gases. The present application and described embodiments take advantage of these principles to provide a purge gas mixture and system to increase the speed of a projectile exiting the muzzle-end of a gun barrel. A partial vacuum may also be used in certain applications.

Air as conventionally known is comprised of about 78% nitrogen and 21% oxygen with other trace gases such as carbon dioxide, neon, and hydrogen. Other gases (e.g. helium) and partial vacuums have both a lower density and a higher speed-of-sound from that of conventional air or even some highly utilized propellant gases. The present application and described embodiments take advantage of these principles to provide a purge gas mixture and system to increase the speed of a projectile exiting the muzzle-end of a gun barrel. A partial vacuum may also be used in certain applications.

The present disclosure relates to a launch system, a launch vehicle for use with the launch system, and methods of launching a payload utilizing the launch vehicle and/or the launch system. The disclosure can provide for delivery of the payload at a terrestrial location, an Earth orbital location, or an extraorbital location. The launch vehicle can comprise a payload, a propellant tank, an electrical heater wherein propellant, such as a light gas (e.g., hydrogen) is electrically heated to significantly high temperatures, and an exhaust nozzle from which the heated propellant expands to provide an exhaust velocity of, for example, 7-16 km/sec. The launch vehicle can be utilized with the launch system, which can further comprise a launch tube formed of at least one tube, which can be electrically conductive and which can be combined with at least one insulator tube. An electrical energy source, such as a battery bank and associated inductor, can be provided.

A hole in geologic material, such as a wellbore, may be extended by impacting the working face of the hole with high velocity projectiles. A tube may be placed within the hole, and the lower end of the tube may be sealed to prevent ingress of material from the hole into the tube. A projectile may be accelerated through the tube, such as by igniting a combustible gas mixture to impart a force to the projectile. The impact of the projectile may extend the hole. In some cases, accelerated projectiles may be used in conjunction with a drill bit to drill a wellbore or other type of hole.

A hole in geologic material, such as a wellbore, may be extended by impacting the working face of the hole with high velocity projectiles. A tube may be placed within the hole, and the lower end of the tube may be sealed to prevent ingress of material from the hole into the tube. A projectile may be accelerated through the tube, such as by igniting a combustible gas mixture to impart a force to the projectile. The impact of the projectile may extend the hole. In some cases, accelerated projectiles may be used in conjunction with a drill bit to drill a wellbore or other type of hole.

The present disclosure relates to a launch system, a launch vehicle for use with the launch system, and methods of launching a payload utilizing the launch vehicle and/or the launch system. The disclosure can provide for delivery of the payload at a terrestrial location, an Earth orbital location, or an extraorbital location. The launch vehicle can comprise a payload, a propellant tank, an electrical heater wherein propellant, such as a light gas (e.g., hydrogen) is electrically heated to significantly high temperatures, and an exhaust nozzle from which the heated propellant expands to provide an exhaust velocity of, for example, 7-16 km/sec. The launch vehicle can be utilized with the launch system, which can further comprise a launch tube formed of at least one tube, which can be electrically conductive and which can be combined with at least one insulator tube. An electrical energy source, such as a battery bank and associated inductor, can be provided.

The present disclosure relates to a launch system, a launch vehicle for use with the launch system, and methods of launching a payload utilizing the launch vehicle and/or the launch system. The disclosure can provide for delivery of the payload at a terrestrial location, an Earth orbital location, or an extraorbital location. The launch vehicle can comprise a payload, a propellant tank, an electrical heater wherein propellant, such as a light gas (e.g., hydrogen) is electrically heated to significantly high temperatures, and an exhaust nozzle from which the heated propellant expands to provide an exhaust velocity of, for example, 7-16 km/sec. The launch vehicle can be utilized with the launch system, which can further comprise a launch tube formed of at least one tube, which can be electrically conductive and which can be combined with at least one insulator tube. An electrical energy source, such as a battery bank and associated inductor, can be provided.

Gas generators may be utilized for launching a projectile. Launch tubes may include gas generators. Methods of launching a projectile may include utilizing gas generators to impart an initial velocity to a projectile.

Gas generators may be utilized for launching a projectile. Launch tubes may include gas generators. Methods of launching a projectile may include utilizing gas generators to impart an initial velocity to a projectile.

A fuel powered paint marker having a first stage and a second stage comprising: a housing; a combustion chamber; a piston; a compression chamber; a fuel system; an oxidizing system; an oxidizing agent; a fuel assembly included in the fuel system; a separation assembly included in the fuel system and separating the oxidizing agent from the fuel assembly in the first stage; a bolt drive system; a fuel nozzle included in the fuel system for injecting fuel into the combustion chamber during the second stage; and, an ignition for igniting the fuel and oxidating agent in the combustion chamber driving the piston forward and compressing a gas in the compression chamber thereby ejecting a projectile wherein the fuel and oxidizing agent are separated during the first stage and mixed in the combustion chamber.