Systems and methods for improving efficiency of electroantimagnetic launchers

Patent metadata

Field	Value
Publication number	US-2018251237-A1
Application number	US-201815910230-A
Country	US
Kind code	A1
Filing date	Mar 2, 2018
Priority date	Mar 2, 2017
Publication date	Sep 6, 2018
Grant date	—

Abstract

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.

First claim

1 . A method for improving efficiency of an electroantimagnetic launch system, the method comprising:
accelerating a launch vehicle through a launch tube by conducting electrical current from a power source through conductors positioned in the launch tube to electrical contacts on the launch vehicle so as to power a propulsion system of the launch vehicle; and substantially preventing flow of electrical current in the launch tube other than between the launch tube conductors and the launch vehicle electrical contacts.

2 . The method of claim 1 , wherein the launch tube comprises a starting end and an exit end, wherein the power source is positioned proximate the exit end of the launch tube so as to deliver the electrical current from the exit end toward the starting end, and wherein the launch tube comprises a plurality of elements that sequentially terminate delivery of the electrical current rearward of the launch vehicle as the launch vehicle accelerates through the launch tube.

3 . The method of claim 2 , wherein the plurality of elements that sequentially terminate delivery of the electrical current rearward of the launch vehicle are selected from the group consisting of solid state switches, explosive switches, fuses, and combinations thereof.

4 . The method of claim 2 , wherein the plurality of elements that sequentially terminate delivery of the electrical current rearward of the launch vehicle are defined by one or more of the following configurations: time-based switching; controlled by a defined computer algorithm; mechanically triggered; optically triggered.

5 . The method of claim 1 , comprising forming a sheath of ionization quenching gas that is effectively positioned between in a space between the launch tube and the launch vehicle as the launch vehicle accelerates through the launch tube.

6 . The method of claim 5 , wherein the sheath of ionization quenching gas is formed substantially around a circumference of the launch vehicle by venting of the gas from the launch vehicle.

7 . The method of claim 5 , wherein the sheath of ionization quenching gas is formed substantially around a circumference of the launch tube by venting of the gas from the launch tube.

8 . The method of claim 7 , wherein venting of ionization quenching gas at any given section of the launch tube begins prior to the launch vehicle accelerating past said given section of the launch tube, and the venting of the ionization quenching gas terminates after the launch vehicle has accelerated past said given section of the launch tube.

9 . The method of claim 1 , comprising generating a magnetic force following the launch vehicle as the launch vehicle accelerates through the launch tube, said magnetic force being effective to force any electrical current forming behind the accelerating launch vehicle to move forward and merge with the electrical current conducted through the conductors in the launch tube to the electrical contacts on the launch vehicle.

10 . The method of claim 9 , wherein the launch tube provides an inductance gradient that exceeds the minimal inductance gradient required for operation of the launch tube.

11 . The method of claim 1 , comprising a plurality of power sources spaced along the launch tube and configured to separately conduct electrical current to the launch tube only in defined sections of the launch tube, and wherein each of the plurality of power sources is activated for power delivery only during the time that the launch vehicle accelerates past the defined section of the launch tube powered by the respective power source.

12 . A launch system comprising:
a launch tube including a power source and conductors configured for conducting electrical current from the power source; a launch vehicle including a propulsion system configured for accelerating the launch vehicle through the launch tube and electrical contacts configured for transferring the electrical current from the conductors of the launch tube to the propulsion system; wherein the launch system is configured to substantially prevent flow of electrical current in the launch tube other than between the launch tube conductors and the launch vehicle electrical contacts.

13 . The launch system of claim 12 , wherein the launch tube comprises a starting end and an exit end, wherein the power source is positioned proximate the exit end of the launch tube and is configured to deliver the electrical current from the exit end toward the starting end, and wherein the launch tube comprises a plurality of elements configured to sequentially terminate delivery of the electrical current rearward of the launch vehicle as the launch vehicle accelerates through the launch tube.

14 . The launch system of claim 13 , wherein the plurality of elements configured to sequentially terminate delivery of the electrical current rearward of the launch vehicle are selected from the group consisting of solid state switches, explosive switches, fuses, and combinations thereof.

15 . The launch system of claim 13 , wherein the plurality of elements configured to sequentially terminate delivery of the electrical current rearward of the launch vehicle are defined by one or more of the following configurations: time-based switching; controlled by a defined computer algorithm; mechanically triggered; optically triggered.

16 . The launch system of claim 12 , comprising a source of an ionization quenching gas and one or more vents configured to emit the ionization quenching gas in a space between the launch tube and the launch vehicle.

17 . The launch system of claim 16 , wherein the one or more vents are included on the launch vehicle.

18 . The launch system of claim 16 , wherein the one or more vents are included on the launch tube.

19 . The launch system of claim 18 , comprising a plurality of the vents positioned along the launch tube and a control element configured to open and close the vents sequentially in combination with passage of the launch vehicle thereby.

20 . The launch system of claim 12 , wherein the launch tube is configured to have an inductance gradient that exceeds the minimal inductance gradient required for operation of the launch tube.

21 . The launch system of claim 12 , comprising a plurality of power sources spaced along the launch tube and configured to separately conduct electrical current to the launch tube only in defined sections of the launch tube, and wherein each of the plurality of power sources is configured to be active for power delivery only when the launch vehicle is in the defined section of the launch tube powered by the respective power source.

Assignees

• 8 Rivers Capital Llc

Inventors

• Palmer Miles R
• Hosie Cam

Classifications

• F42B6/006

  Projectiles for electromagnetic or plasma guns · CPC title

• B64G5/00

  Ground equipment for vehicles, e.g. starting towers, fuelling arrangements (B64G3/00 takes precedence) · CPC title

• B64F1/04 Primary

  for launching aircraft · CPC title

• F41B6/00

  Electromagnetic launchers {; Plasma-actuated launchers (projectiles for electromagnetic or plasma guns F42B6/006)} · CPC title

• F41F3/0406

  Rail launchers · CPC title