Methods and apparatus for performing propulsion operations using electric propulsion systems

Patent metadata

Field	Value
Publication number	US-9643739-B2
Application number	US-201514828462-A
Country	US
Kind code	B2
Filing date	Aug 17, 2015
Priority date	May 11, 2012
Publication date	May 9, 2017
Grant date	May 9, 2017

Abstract

Methods and apparatus to methods and apparatus for performing propulsion operations using electric propulsion system are disclosed. An example method includes deploying a space vehicle including an electric propulsion system; and using the electric propulsion system for attitude control and orbit control, no other propulsion system provided to enable the attitude control and the orbit control.

First claim

What is claimed is:

1. A method, comprising:
deploying a space vehicle including an electric propulsion system; and
using the electric propulsion system for attitude control, momentum control, and orbit control of the space vehicle, no other propulsion system provided on the space vehicle to enable any of the attitude control, the momentum control, or the orbit control.

2. The method of claim 1 , wherein the space vehicle is a satellite.

3. The method of claim 1 , further including launching a launch vehicle in which the space vehicle is disposed.

4. The method of claim 1 , further including independently moving thrusters of the electric propulsion system.

5. The method of claim 1 , wherein the electric propulsion system includes first thrusters adjacent a first side of the space vehicle and second thrusters adjacent a second side of the space vehicle opposite the first side.

6. The method of claim 5 , wherein no other thrusters are positioned on the space vehicle between the first thrusters and the second thrusters.

7. A method, comprising:
launching a launch vehicle including a first space vehicle and a second space vehicle, the first space vehicle including a first electric propulsion system, the second space vehicle including a second electric propulsion system;
deploying the first space vehicle and the second space vehicle from the launch vehicle; and
using the first electric propulsion system for attitude control, momentum control, and orbit control of the first space vehicle, no other propulsion system provided on the first space vehicle to enable any of the attitude control, the momentum control, or the orbit control.

8. The method of claim 7 , further including using the second electric propulsion system for attitude control, momentum control, and the orbit control of the second space vehicle, no other propulsion system provided on the second space vehicle to enable any of the attitude control, the momentum control, or the orbit control.

9. The method of claim 7 , further including independently moving thrusters of the first electric propulsion system.

10. The method of claim 7 , wherein the electric propulsion system of the first space vehicle includes first thrusters adjacent a first side of the first space vehicle and second thrusters adjacent a second side of the first space vehicle opposite the first side, and wherein no other thrusters are positioned on the first space vehicle between the first thrusters and the second thrusters.

11. An apparatus, comprising:
a space vehicle, including:
an electric propulsion system; and
a processor to cause the electric propulsion system to enable attitude control, momentum control and orbit control of the space vehicle, no other propulsion system provided on the space vehicle to enable any of the attitude control, the momentum control, or the orbit control.

12. The apparatus of claim 11 , wherein the orbit control includes orbit maintaining, orbit changing, orbit raising, orbit insertion, orbit re-positioning, and de-orbit maneuvers of the apparatus.

13. The apparatus of claim 11 , wherein the electric prolusion system includes a first thruster coupled to a first side of the space vehicle and a second thruster coupled to a second side of the space vehicle.

14. The apparatus of claim 11 , wherein the electric propulsion system includes a Xenon ion propulsion system, a plasma propulsion system, or a Hall Effect propulsion system.

15. The apparatus of claim 11 , wherein the electric prolusion system includes a first thruster, a second thruster, a third thruster, and a fourth thruster, the first, second, third, and fourth thrusters being disposed adjacent respective corners of the space vehicle.

16. The apparatus of claim 11 , wherein the electric propulsion system of the space vehicle includes first thrusters adjacent a first side of the space vehicle and second thrusters adjacent a second side of the space vehicle opposite the first side, and wherein no other thrusters are positioned on the space vehicle between the first thrusters and the second thrusters.

17. The apparatus of claim 11 , wherein the electric propulsion system includes a tank to receive a propellant, the propellant including an inert gas propellant, a Xenon gas propellant, an Argon gas propellant, or a Krypton gas propellant.

18. The apparatus of claim 17 , wherein the tank is positioned along a longitudinal axis of the space vehicle.

19. The apparatus of claim 11 , further including a power source, the power source to provide power to one or more components of the space vehicle.

20. The apparatus of claim 19 , wherein the power source includes a solar array fixed or movable between a stowed configuration and a deployed configuration.

Assignees

• Boeing Co

Inventors

• Peterka Iii James J
• Caplin Glenn N
• Aston Richard W

Classifications

• B64G1/002 Primary

  Launch systems · CPC title

• B64G1/422

  Nuclear power generation · CPC title

• B64G1/44

  using radiation, e.g. deployable solar arrays · CPC title

• B64G1/503

  Radiator panels · CPC title

• B64G1/361

  using star sensors · CPC title