Balloon device for lowering space object orbits

• US 6,830,222 B1
• Filed: 03/21/2003
• Issued: 12/14/2004
• Est. Priority Date: 03/21/2002
• Status: Expired due to Term

• Current Assignee: Global Aerospace Corporation
• Original Assignee: Global Aerospace Corporation
• Inventors: McRonald, Angus D., Nock, Kerry T., Aaron, Kim Maynard
• Primary Examiner(s): DINH, TIEN QUANG
• Application Number:
  US10/394,477
• Time in Patent Office: 634 Days
• Field of Search: 244/158.R, 244/110.D, 244/160, 244/164
• US Class Current: 244/158.7
• CPC Class Codes: B64G 1/222 for deploying structures between a stowed and deployed state
• CPC Class Codes: B64G 1/2227 Inflating
• CPC Class Codes: B64G 1/242 Orbits and trajectories
• CPC Class Codes: B64G 1/2421 Aerobraking
• CPC Class Codes: B64G 1/2427 Transfer orbits

Abstract

An apparatus for lowering an orbit of a space object includes an envelope, an inflation system for inflating the envelope, an inflation control system for controlling the inflation system, and attachment hardware for connecting the apparatus and the space object. Inflating the envelope increases an effective drag area of the envelope for increasing atmospheric drag on the envelope.

Claims

1. An apparatus for lowering an orbit of a space object, comprising:

an envelope;

a spatial-separation element for providing a complete spatial separation between the envelope and the space object;

an inflation system for inflating the envelope;

an inflation control system for controlling the inflation system; and

attachment hardware for connecting the apparatus and the space object, wherein

inflating the envelope increases an effective drag area of the envelope for increasing atmospheric drag on the envelope.

2. An apparatus according to claim 1, wherein the spatial separation element includes a mast.

3. An apparatus according to claim 1, wherein the spatial separation element includes a tether.

4. An apparatus according to claim 1, wherein the inflation control system includes a timer having a reset mode.

5. An apparatus for lowering an orbit of space object, comprising:

an envelope;

an inflation system for inflating the envelope;

a spatial-deployment system for separating the apparatus and the space object in a deployed configuration, the spatial-deployment system including a reefing system that encloses a portion of the envelope before inflation and constrains the envelope during inflation;

a spatial-deployment control system for controlling the spatial-deployment system;

an inflation control system for controlling the inflation system; and

attachment hardware for connecting the apparatus and the space object, wherein

inflating the envelope increases an effective drag area of the envelope for increasing atmospheric drag on the envelope.

6. An apparatus according to claim 5, wherein the reefing system includes a reefing sleeve.

7. An apparatus according to claim 5, wherein the inflation control system includes a timer having a reset mode.

8. A method for lowering an orbit of a space object, comprising:

connecting an envelope to the space object;

using a spatial-separation element to provide a complete spatial separation between the envelope and the space object; and

controlling an inflating of the envelope, wherein

inflating the envelope increases an effective drag area of the envelope for increasing atmospheric drag on the envelope.

9. A method according to claim 8, wherein using the spatial separation element to provide the complete spatial separation includes:

connecting a first end of a mast to the envelope, and

connecting a second end of the mast to the space object.

10. A method according to claim 8, wherein using the spatial separation element to provide the complete spatial separation includes:

connecting a first end of a tether to the envelope, and

connecting a second end of the tether to the space object.

11. A method according to claim 8, further comprising:

controlling a deployment of the complete spatial separation between the envelope and the space object.

12. A method according to claim 11, wherein controlling the deployment of the complete spatial separation between the envelope and the space object includes:

connecting a first end of a mast to the envelope,

connecting a second and of the mast to the space object, and

extending a length of the mast.

13. A method according to claim 11, wherein controlling the deployment of the complete spatial separation between the envelope and the space object includes

connecting a first end of a tether to the envelope,

connecting a second end of the tether to the space object, and

extending a length of the tether.

14. A method according to claim 11, wherein controlling the inflating of the envelope includes constraining the envelope with a reefing system that encloses a portion of the envelope.

15. A method according to claim 8, wherein controlling the inflating of the envelope includes using a timer to begin the inflating of the envelope.

16. A method according to claim 15, wherein controlling the inflating of the envelope includes resetting the timer.

17. A method according to claim 8, further comprising:

lowering the orbit of the space object to an altitude where a dynamic pressure is about 0.01 torr.

18. A method for lowering an orbit of a space object, comprising:

connecting an envelope to the space object;

controlling a deployment of a spatial separation between the envelope and the space object; and

controlling an inflating of the envelope, wherein

controlling the inflating of the envelope includes constraining the envelope with a reefing system that encloses a portion of the envelope, and

inflating the envelope increases an effective drag area of the envelope for increasing atmospheric drag on the envelope.

19. A method according to claim 18, wherein controlling the deployment of the spatial separation between the envelope and the space object includes:

connecting a first end of a mast to the envelope,

connecting a second end of the mast to the space object, and

extending a length of the mast.

20. A method according to claim 18, wherein controlling the deployment of the spatial separation between the envelope and the space object includes

connecting a first end of a tether to the envelope,

connecting a second end of the tether to the space object, and

extending a length of the tether.

21. A method according to claim 18, wherein controlling the inflating of the envelope includes using a timer to begin the inflating of the envelope.

22. A method according to claim 18, wherein controlling the inflating of the envelope includes resetting the timer.

23. A method according to claim 18, further comprising:

lowering the orbit of the space object to an altitude where a dynamic pressure is about 0.01 torr.

24. A method according to claim 18, wherein the reefing system includes a reefing sleeve.