LAUNCH VEHICLE AND SYSTEM AND METHOD FOR ECONOMICALLY EFFICIENT LAUNCH THEREOF

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, o...

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Bibliographische Detailangaben
1. Verfasser:	Palmer, Miles R
Format:	Patent
Sprache:	eng
Schlagworte:	AIRCRAFT AMMUNITION AMMUNITION FUZES APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS,e.g. CANNONS ARMING OR SAFETY MEANS THEREFOR AVIATION BLASTING COMBUSTION ENGINES COSMONAUTICS EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS ANDORDNANCE, e.g. CANNONS HARPOON GUNS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LAUNCHERS FOR ROCKETS OR TORPEDOES LIGHTING MECHANICAL ENGINEERING MOUNTINGS FOR SMALLARMS OR ORDNANCE PERFORMING OPERATIONS TRANSPORTING VEHICLES OR EQUIPMENT THEREFOR WEAPONS WEAPONS FOR PROJECTING MISSILES WITHOUT USE OF EXPLOSIVE ORCOMBUSTIBLE PROPELLANT CHARGE WEAPONS NOT OTHERWISE PROVIDED FOR
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Beschreibung
Zusammenfassung:	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.