Structural Propellant for ion rockets (SPIR)

Patent metadata

Field	Value
Publication number	US-10428806-B2
Application number	US-201615004818-A
Country	US
Kind code	B2
Filing date	Jan 22, 2016
Priority date	Jan 22, 2016
Publication date	Oct 1, 2019
Grant date	Oct 1, 2019

Abstract

Systems, methods, and apparatus for a structural propellant for ion rockets (SPIR) are disclosed. In one or more embodiments, a method for in-space propulsion of a spacecraft involves removing, by a removal device, a portion of a structure of the spacecraft. The method further involves feeding, by the removal device, the portion into a Hall thruster system. Further, the method involves utilizing, by the Hall thruster system, the portion as propellant to produce thrust. In one or more embodiments, the structure is an upper stage of the spacecraft. In at least one embodiment, the upper stage comprises at least one structural support and/or at least one upper stage housing. In some embodiments, the structure is manufactured from magnesium, bismuth, zinc, and/or indium.

First claim

We claim:

1. A method for in-space propulsion of a spacecraft, the method comprising:
removing, by a removal device, a portion of a structure, which provides housing and/or structural support for the spacecraft, to re-purpose the portion of the structure as propellant;
feeding, by the removal device, the portion into a Hall thruster system; and
utilizing, by the Hall thruster system, the portion as propellant to produce thrust.

2. The method of claim 1 , wherein the removal device comprises at least one of at least one mechanical cutter and at least one laser cutter.

3. The method of claim 2 , wherein the at least one mechanical cutter comprises at least one of at least one cutting wheel and at least one scissors mechanism.

4. The method of claim 1 , wherein the structure is an upper stage of the spacecraft.

5. The method of claim 4 , wherein the structure comprises a structural support and/or an upper stage housing.

6. The method of claim 1 , wherein the structure is manufactured from at least one of magnesium, bismuth, zinc, and indium.

7. The method of claim 1 , wherein the portion of the structure is removed by the removal device in the form of a ribbon.

8. The method of claim 1 , wherein the removal device is tethered to the spacecraft via at least one cord.

9. The method of claim 1 , wherein the removal device is a robotic device that moves about the spacecraft.

10. The method of claim 1 , wherein the removal device comprises at least one of at least one wheel and at least one thruster.

11. A system for in-space propulsion of a spacecraft, the system comprising:
a removal device to remove a portion of a structure, which provides housing and/or structural support for the spacecraft, to re-purpose the portion of the structure as propellant, and to feed the portion into a Hall thruster system; and
the Hall thruster system to utilize the portion as propellant to produce thrust.

12. The system of claim 11 , wherein the removal device comprises at least one of at least one mechanical cutter and at least one laser cutter.

13. The system of claim 12 , wherein the at least one mechanical cutter comprises at least one of at least one cutting wheel and at least one scissors mechanism.

14. The system of claim 11 , wherein the structure is an upper stage of the spacecraft.

15. The system of claim 14 , wherein the structure comprises a structural support and/or an upper stage housing.

16. The system of claim 11 , wherein the structure is manufactured from at least one of magnesium, bismuth, zinc, and indium.

17. The system of claim 11 , wherein the portion of the structure is removed by the removal device in the form of a ribbon.

18. The system of claim 11 , wherein the removal device is tethered to the spacecraft via at least one cord.

19. The system of claim 11 , wherein the removal device is a robotic device that moves about the spacecraft.

20. The system of claim 11 , wherein the removal device comprises at least one of at least one wheel and at least one thruster.

Assignees

• Boeing Co

Inventors

• Childress Jamie J
• Kessler Thomas L

Classifications

• B64G1/403 Primary

  Solid propellant rocket engines · CPC title

• F03H1/0075

  with an annular channel; Hall-effect thrusters with closed electron drift · CPC title

• F03H1/0037

  Electrostatic ion thrusters · CPC title

• B64G4/00

  Tools specially adapted for use in space · CPC title

• F03H1/0012 Primary

  Means for supplying the propellant · CPC title