Method and apparatus for mitigating space debris

• US 5,082,211 A
• Filed: 10/31/1990
• Issued: 01/21/1992
• Est. Priority Date: 10/31/1990
• Status: Expired due to Term

• Current Assignee: Teledyne Industries Incorporated (Teledyne Technologies Incorporated)
• Original Assignee: Teledyne Industries Incorporated (Teledyne Technologies Incorporated)
• Inventors: Werka, Robert O.
• Primary Examiner(s): Peters, Jr., Joseph F.
• Assistant Examiner(s): Mattix, Carla
• Application Number:
  US07/606,897
• Time in Patent Office: 447 Days
• Field of Search: 244/1 TD, 244/158 R, 244/159, 244/164, 244/167, 89/36.16
• US Class Current: 244/158.2
• CPC Class Codes: B64G 1/1078 Maintenance satellites refueling in space B64G1/4024
• CPC Class Codes: B64G 1/242 Orbits and trajectories
• CPC Class Codes: B64G 1/40 Arrangements or adaptations of propulsion systems
• CPC Class Codes: B64G 1/648 Tethers

Abstract

A method and apparatus for mitigating space debris having special applicability for use with anti-satellite weapons testing. To mitigate debris in a controlled and predictable fashion a first body is tethered to a lower altitude body. A suitable length of tether is chosen to correlate with the orbital characteristics of the higher altitude body such that the lower altitude body has a relatively low velocity for its orbital altitude. Upon release of the target from the tether or upon debris production by the lower altitude target, the reduced velocity of the body or debris produced for its altitude results in rapid deorbiting of the target or debris. To offset any momentum increase created when the debris is the result of an impact of an object with the lower altitude body, the orbital characteristics are controlled to ensure the proper deorbiting velocity is achieved. A counter rotation of the tether system can also be used to negate an increase in velocity due to impact.

Claims

1. A method of mitigating space debris in a controllable fashion, comprising:

placing a first body of mass M₁ in orbit about a planet;

positioning a second body of mass M₂, which is subject to producing debris, in a lower altitude orbit by extending a tether line joining said first and second body out an essentially predetermined distance away from said first body, whereby said first body brakes said second body such that any debris produced by said second body deorbits at a rapid rate, and the step of extending said tether out away from said first body includes extending said tether a distance away from said first body which results in placing the debris in a controlled deorbit that is less than about one half orbital periods in duration.

2. A method as recited in claim 1 wherein said first body of mass M₁ is placed in a controlled, essentially circular orbit about the planet, and said second body is maintained in a tracking relationship with the center of gravity of said first body essentially in alignment with a line extending from the center of the orbit of said first body to the center of gravity of said first body.

3. A method as recited in claim 1 wherein mass M₁ is about 5 times greater than mass M₂.

4. A method as recited in claim 1 wherein said first body is placed in an elliptical orbit about said planet.

5. A method as recited in claim 1 wherein said tether is extended out away from said first body at a distance which is greater than 5 nmi and less than 1,000 nmi.

6. A method as recited in claim 1 wherein said first body is at an altitude above 140 nmi.

7. A method as recited in claim 6 wherein said second body is at an altitude of above 110 nmi.

8. A method as recited in claim 1 wherein said second body is at an altitude of above 140 nmi.

9. A method as recited in claim 8 wherein said tether length is greater than 5 nmi and less than 1,000 nmi.

10. A method for mitigating debris released from an orbiting target following impact by an interceptor, comprising:

placing a satellite in essentially a predetermined orbit about a planet;

positioning a target at a lower altitude with respect to said planet by extending a tether attached to said target out an essentially predetermined distance away from said satellite such that any debris resulting from intercept of said target experiences a deorbit which is more rapid than the target would assume had the target been orbiting at the same altitude about the planet in an untethered state and the length of said tether being sufficient to cause at least a majority of the debris resulting from intercept of said target to deorbit within 0.5 orbital periods.

11. A method for mitigating space debris as recited in claim 10 wherein said predetermined orbit is circular and of an altitude greater than about 100 nmi and said tether is extended out a distance greater than 5 nmi.

12. A method for mitigating space debris as recited in claim 10 wherein said target and tethered satellite, in combination, have a center of mass and said target and tethered satellite are rotated about the center of mass while orbiting about said planet, such that the direction of rotation for said target at the time of intercept impact is essentially opposite in direction to the direction said center of mass is travelling.

13. A method as recited in claim 10 wherein said predetermined orbit is elliptical and said tether is of sufficient length to ensure deorbit of essentially all of any debris produced following impact of said target by the interceptor at a time when said tethered satellite is about at an apogee position in the elliptical orbit of said tethered satellite.

14. A method as recited in claim 13 further comprising rotating said satellite, target and tether about a common point while said satellite, target and tether orbit about the planet such that the direction of rotation for said target at the time of intercept impact is essentially opposite in direction to the direction of travel of the common point.

15. An apparatus for mitigating space debris which develops during anti-satellite intercept testing, comprising:

a satellite;

an anti-satellite intercept target;

a tether line connected at one end to said target and at another end to said satellite;

said satellite including tether dispensing means for extending and retracting said tether out away from said satellite; and

said tether having a length which is in the range of 675 nmi to 1000 nmi.

16. An apparatus as recited in claim 15 wherein said tether is tapered.

17. An apparatus as recited in claim 16 wherein said tether has a 5:

1 taper.

18. An apparatus as recited in claim 15 wherein the mass of said satellite is about 5 times greater than the mass of said target.

19. An apparatus as recited in claim 15 wherein said tether is of a length which is sufficient to cause the deorbiting of at least a majority of any debris created by said target upon impact with an interceptor within less than 0.5 orbital periods.

20. An apparatus as recited in claim 15 wherein said target includes an inflatable main body.

21. An apparatus as recited in claim 15 further comprising attachment means for releasably attaching said target to said tether.

22. An apparatus as recited in claim 21 wherein said attachment means is remotely controlled from said satellite and said tether line is formed of a conducting material.

23. An apparatus as recited in claim 15 wherein said satellite includes means for placing said satellite, target and tether in rotation about the center of gravity for the combination of said satellite, target and tether.

24. A method of mitigating space debris in a controllable fashion, comprising:

placing a first body of mass M₁ in orbit about a planet;

positioning a second body of mass M₂, which is subject to producing debris and is of a mass 5 times less than mass M₁, in a lower altitude orbit by extending a tether line joining said first and second body out an essentially predetermined distance away from said first body, whereby said first body brakes said second body such that any debris produced by said second body deorbits at a rapid rate.

25. A method as recited in claim 24 wherein said first body of mass M₁ is placed in a controlled, essentially circular orbit about the planet, and said second body is maintained in a tracking relationship with the center of gravity of said first body essentially in alignment with a line extending from the center of the orbit of said first body to the center of gravity of said first body.

26. A method as recited in claim 24 wherein said first body is placed in an elliptical orbit about said planet.

27. A method as recited in claim 24 wherein said tether is extended out away from said first body at a distance which is greater than 5 nmi and less than 1,000 nmi.

28. A method as recited in claim 24 wherein said first body is at an altitude above 140 nmi.

29. A method as recited in claim 28 wherein said second body is at an altitude of above 110 nmi.

30. A method as recited in claim 24 wherein said second body is at an altitude of above 140 nmi.

31. A method of mitigating space debris in a controllable fashion, comprising:

placing a first body of mass M₁ in orbit about a planet;

positioning a second body of mass M₂, which is subject to producing debris, in a lower altitude orbit by extending a tether line joining said first and second body out an essentially predetermined distance away from said first body, whereby said first body brakes said second body such that any debris produced by said second body deorbits at a rapid rate and said step of placing said first body includes placing said first body at an altitude above 140 nmi.

32. A method as recited in claim 31 wherein said first body of mass M₁ is placed in a controlled, essentially circular orbit about the planet, and said second body is maintained in a tracking relationship with the center of gravity of said first body essentially in alignment with a line extending from the center of the orbit of said first body to the center of gravity of said first body.

33. A method as recited in claim 31 wherein said first body is placed in an elliptical orbit about said planet.

34. A method as recited in claim 31 wherein said second body is at an altitude of above 110 nmi.

35. A method as recited in claim 31 wherein said second body is at an altitude of above 140 nmi.

36. A method of mitigating space debris in a controllable fashion, comprising:

placing a first body of mass M₁ in orbit about a planet;

positioning a second body of mass M₂, which is subject to producing debris, in a lower altitude orbit by extending a tether line joining said first and second body out an essentially predetermined distance away from said first body, whereby said first body brakes said second body such that any debris produced by said second body deorbits at a rapid rate and said step of positioning said second body includes positioning said second body at an altitude of above 140 nmi.

37. A method as recited in claim 36 wherein said first body of mass M₁ is placed in a controlled, essentially circular orbit about the planet, and said second body is maintained in a tracking relationship with the center of gravity of said first body essentially in alignment with a line extending from the center of the orbit of said first body to the center of gravity of said first body.

38. A method as recited in claim 36 wherein said first body is placed in an elliptical orbit about said planet.

39. An apparatus for mitigating space debris which developed during anti-satellite intercept testing, comprising:

a satellite;

an anti-satellite intercept target;

a tether line connected at one end to said target and at another end to said satellite;

said satellite including tether dispensing means for extending and retracting said tether out away from said satellite and said satellite having a mass which is about 5 times greater than the mass of said target.

40. An apparatus as recited in claim 39 wherein said tether is of a length which is sufficient to cause the deorbiting of at least a majority of any debris created by said target upon impact with an interceptor within less than 0.5 orbital periods.

41. An apparatus as recited in claim 39 further comprising attachment means for releasably attaching said target to said tether.

42. An apparatus as recited in claim 41 wherein said attachment means is remotely controlled from said satellite and said tether line is formed of a conducting material.

43. An apparatus as recited in claim 39 wherein said satellite includes means for placing said satellite, target and tether in rotation about the center of gravity for the combination of said satellite, target and tether.

44. An apparatus for mitigating space debris which developed during anti-satellite intercept testing, comprising:

a satellite;

an anti-satellite intercept target;

a tether line connected at one end to said target and at another end to said satellite;

said satellite including tether out away from dispensing means for extending and retracting said tether out away from said satellite wherein said tether is of a length which is sufficient to cause the deorbiting of at least a majority of any debris created by said target upon impact with an interceptor within less than 0.5 orbital periods.

45. An apparatus as recited in claim 44 further comprising attachment means for releasably attaching said target to said tether.

46. An apparatus as recited in claim 45 wherein said attachment means is remotely controlled from said satellite and said tether line is formed of a conducting material.

47. An apparatus as recited in claim 44 wherein said satellite includes means for placing said satellite, target and tether in rotation about the center of gravity for the combination of said satellite, target and tether.

48. An apparatus for mitigating space debris which developed during anti-satellite intercept testing, comprising:

a satellite;

an anti-satellite intercept target;

a tether line connected at one end to said target and at another end to said satellite;

said satellite including tether dispensing means for extending and retracting said tether out away from said satellite, and said apparatus further comprising attachment means for releasably attaching said target to said tether.

49. An apparatus as recited in claim 48 wherein said attachment means is remotely controlled from said satellite and said tether line is formed of a conducting material.