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, 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.
1. An electroantimagnetic launch method for accelerating a launch vehicle to a high velocity, the method comprising electrically heating a propellant to form an expanding gas that accelerates the launch vehicle through a launch tube to a velocity of at least about 5,000 msec with an acceleration force of about 2 to about 2,000 G's while limiting a magnetic field within the tube to no more than about 2 Tesla.
2. The electroantimagnetic launch method according claim 1 , wherein the launch vehicle comprises:
a payload container;
a propellant tank containing the propellant;
an electrical heater separate from and in fluid connection with the propellant tank, the electrical heater being configured to receive the propellant from the propellant tank and being adapted for electrical heating of the propellant to form an exiting exhaust; and
one or more electrical contacts adapted for directing flow of electrical current through the electrical heater.
3. The electroantimagnetic launch method according to claim 2 , wherein the launch vehicle further comprises an expansion nozzle in fluid communication with the exiting exhaust from the electrical heater.
4. The electroantimagnetic launch method according to claim 2 , wherein the electrical heater is a resistive heater.
5. The electroantimagnetic launch method according to claim 4 , wherein the resistive heater comprises an electrically heated porous cylinder inside a containment vessel.
6. The electroantimagnetic launch method according to claim 5 , wherein the electrically heated porous cylinder comprises tungsten walls.
7. The electroantimagnetic launch method according to claim 2 , wherein the electrical heater is an arc heater.
8. The electroantimagnetic launch method according to claim 7 , wherein the arc is a swirl stabilized vortex arc.
9. The electroantimagnetic launch method according to claim 8 , wherein the arc heater comprises a swirl chamber inside a containment vessel.
10. The electroantimagnetic launch method according to claim 9 , wherein the arc heater comprises coaxial electrical terminals spaced apart by the swirl chamber.
11. The electroantimagnetic launch method according to claim 2 , wherein the electrical contacts comprise sliding electrical contacts.