A launch tube 100 of a flying object 1 has a tube 110, a plurality of rails 120 and a plurality of guides 130. The tube 110 stores the flying object 1. The plurality of rails 120 are fixed on an inner wall of the tube 110 to touch the flying object 1. The plurality of guides 130 are provided on the inner wall of the tube 110. A first guide of the plurality of guides 130 is provided to touch the flying object 1, and evacuates from a region of movement of the flying object 1 when the flying object 1 moves to leave the first guide.

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.

Methods and apparatus for a brace for attachment to a launch rail for a projectile for distributing loading of the projectile when supported by the launch rail. A height of the brace can be adjusted to distribute loading. In embodiments, a release mechanism can allow movement of a wear plate during launch of the projectile.

In a method of carrying a munition on a munition launcher platform, the munition launcher platform is provided with a data tag activator and a data tag reader. A munition is attached to the munition launcher platform, the munition being provided with a data tag. An activation signal is transmitted from the data tag activator to the data tag. As a result of receiving the activation signal, the data tag returns a data response to the data tag reader. The receiving of the data response provides the munition launcher platform with an indication that the munition is still attached to the munition launcher platform.

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, an exhaust nozzle from which the heated propellant expands to provide an exhaust velocity of, for example, 7-16 km/sec, and sliding electrical contacts in electrical connection with the electrical heater. The launch vehicle can be utilized with the launch system, which can further comprise a launch tube formed of concentric electrically conductive tubes, as well as an electrical energy source, such as a battery bank and associated inductor.

The present disclosure relates launch systems, launch vehicles for use with the launch system, and methods of launching articles utilizing the launch vehicle and/or the launch system. In particular, various improvements for electroantimagnetic launch systems, vehicles, and methods are 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, an exhaust nozzle from which the heated propellant expands to provide an exhaust velocity of, for example, 7-16 km/sec, and sliding electrical contacts in electrical connection with the electrical heater. The launch vehicle can be utilized with the launch system, which can further comprise a launch tube formed of concentric electrically conductive tubes, as well as an electrical energy source, such as a battery bank and associated inductor.

In a method of carrying a munition on a munition launcher platform, the munition launcher platform is provided with a data tag activator and a data tag reader. A munition is attached to the munition launcher platform, the munition being provided with a data tag. An activation signal is transmitted from the data tag activator to the data tag. As a result of receiving the activation signal, the data tag returns a data response to the data tag reader. The receiving of the data response provides the munition launcher platform with an indication that the munition is still attached to the munition launcher platform.

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, an exhaust nozzle from which the heated propellant expands to provide an exhaust velocity of, for example, 7-16 km/sec, and sliding electrical contacts in electrical connection with the electrical heater. The launch vehicle can be utilized with the launch system, which can further comprise a launch tube formed of concentric electrically conductive tubes, as well as an electrical energy source, such as a battery bank and associated inductor.

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.