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.

An effector is provided with an expandable fuel volume that when filled with liquid fuel from an external source expands both the fuel volume axially and moves a module positioned forward or aft of the fuel volume axially to extend the length of the effector. The extension serves both to improve the aerodynamics of the effector and its range without requiring retrofitting or replacement of the storage, transport or launch platform infrastructure. The effector may be a munition such as ground, tube or air launched munitions such as missiles, submunitions, UAVs or drones. The airframe may be, for example, the main body, wing or rotor of the munition.