초록 ▼

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

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.

대표청구항 ▼

1. A launch vehicle adapted for high velocity delivery of a payload, the launch vehicle comprising: a payload container;a propellant tank containing a propellant;an electrical heater in fluid connection with the propellant tank and adapted for electrical heating of the propellant to form an exiting

1. A launch vehicle adapted for high velocity delivery of a payload, the launch vehicle comprising: a payload container;a propellant tank containing a propellant;an electrical heater in fluid connection with the propellant tank and adapted for electrical heating of the propellant to form an exiting exhaust, the electrical heater being a resistive heater that comprises an electrically heated porous cylinder inside a containment vessel; andone or more electrical contacts adapted for directing flow of electrical current to the electrical heater. 2. The launch vehicle according to claim 1, further comprising an expansion nozzle in fluid communication with the exiting exhaust from the electrical heater. 3. The launch vehicle according to claim 1, wherein the electrically heated porous cylinder comprises carbon walls with an optional coating comprising a material selected from the group consisting of diamond, tungsten, and hafnium carbide. 4. The launch vehicle according to claim 1, wherein the electrical heater is an arc heater. 5. The launch vehicle according to claim 4, wherein the arc is a swirl stabilized vortex arc. 6. The launch vehicle according to claim 5, wherein the arc heater comprises a swirl chamber inside a containment vessel. 7. The launch vehicle according to claim 6, wherein the arc heater comprises coaxial electrical terminals spaced apart by the swirl chamber. 8. The launch vehicle according to claim 1, wherein the electrical contacts comprise sliding electrical contacts. 9. The launch vehicle according to claim 1, wherein the electrical heater comprises a heater wall that is cooled by transpiration. 10. A launch system comprising: a launch vehicle comprising: a payload container;a propellant tank containing a propellant;an electrical heater in fluid connection with the propellant tank and adapted for electrical heating of the propellant to form an exiting exhaust, the electrical heater being a resistive heater that comprises an electrically heated porous cylinder inside a containment vessel; andone or more electrical contacts adapted for directing flow of electrical current to the electrical heater;a launch tube comprising two or more concentric, electrically conductive tubes separated by an insulator, the launch tube being adapted for acceleration of the launch vehicle therethrough; andan electrical energy source. 11. The launch system according to claim 10, wherein the electrical energy source comprises a battery bank. 12. The launch system according to claim 11, wherein the electrical energy source further comprises an inductor. 13. The launch system according to claim 10, wherein the one or more electrical contacts are conductive sliding contacts. 14. The launch system according to claim 13, wherein the conductive sliding contacts are configured to make an arcing sliding contact with the electrically conductive tubes. 15. The launch system according to claim 13, wherein the conductive sliding contacts are transpiration cooled. 16. The launch system according to claim 10, wherein one or both of the electrically conductive tubes comprises one or more slotted tracks. 17. The launch system according to claim 10, wherein the launch tube is evacuated. 18. The launch system according to claim 10, wherein the launch tube is moveable in one dimension to change launch elevation or launch azimuth. 19. The launch system according to claim 10, wherein the launch tube is moveable in two dimensions to enable change in both elevation and azimuth. 20. A method for launching a payload, the method comprising: providing the payload in a launch vehicle comprising: a payload container;a propellant tank containing a propellant;an electrical heater in fluid connection with the propellant tank and adapted for electrical heating of the propellant to form an exiting exhaust; andone or more electrical contacts adapted for directing flow of electrical current to the electrical heater;providing the launch vehicle in a launch tube comprising two or more concentric, electrically conductive tubes separated by an insulator, the launch tube being adapted for acceleration of the launch vehicle therethrough, and the conductive tubes defining one or more current outbound paths in series with one or more return current paths; andelectrically heating the propellant in the electrical heater to form the exiting exhaust at a velocity sufficient to accelerate the payload out of the launch tube. 21. The method for launching a payload according to claim 20, wherein the method comprises electrically heating the propellant in the electrical heater to form the exiting exhaust and accelerate the launch vehicle through the launch tube at a velocity of about 2,000 to about 50,000 meters per second (m/s) 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. 22. The method of launching a payload according to claim 20, wherein the propellant comprises one or more of hydrogen gas, lithium hydride, and water. 23. The method of launching a payload according to claim 20, wherein the exiting exhaust comprises one or more of molecular hydrogen, atomic hydrogen, and hydrogen plasma. 24. The method of launching a payload according to claim 20, wherein the payload is accelerated in the launch tube and not in free flight outside of the launch tube. 25. The method of launching a payload according to claim 20, comprising passing electrical energy through the electrically conductive tubes and to the electrical heater via the one or more electrical contacts. 26. The method of launching a payload according to claim 25, comprising passing the electrical energy through one or more aligning arms positioned between the electrical heater and the one or more electrical contacts. 27. The method of launching a payload according to claim 20, wherein electrically heating the propellant in the electrical heater to form the exiting exhaust comprises expanding the propellant in a heater such that the expanding propellant transpires through pores in walls of the electrical heater, fills an expansion chamber, and exits the electrical heater. 28. The method of launching a payload according to claim 20, wherein electrically heating the propellant in the electrical heater to form the exiting exhaust comprises heating the propellant in a swirl chamber via an electrical arc and expanding the heated propellant through a gas discharge.