SYSTEM, APPARATUS, AND METHOD FOR ACTIVE DEBRIS REMOVAL

• US 20140107865A1
• Filed: 10/12/2012
• Published: 04/17/2014
• Est. Priority Date: 10/12/2012
• Status: Active Grant

• Current Assignee: Aerospace Corporation, Government of The United States As Represented by The Administrator of the National Aeronautics and Space Administration, United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration
• Original Assignee: Aerospace Corporation, National Aeronautics and Space Administration (Government of the United States of America)
• Inventors: Griffith, Anthony D. Sr., Kohli, Rajiv, Burns, Susan H., Damico, Stephen J., Gruber, David J., Hickey, Christsopher J., Lee, David E., Robinson, Travis M., Smith, Jason T., Spehar, Peter T., Adlis, David S., Kent, Brian M.
• Granted Patent: US 9,187,189 B2
• Time in Patent Office: Days
• US Class Current: 701/2
• CPC Class Codes: B64G 1/002 Launch systems
• CPC Class Codes: B64G 1/1078 Maintenance satellites refueling in space B64G1/4024
• CPC Class Codes: B64G 1/24 Guiding or controlling apparatus, e.g. for attitude control
• CPC Class Codes: B64G 1/242 Orbits and trajectories
• CPC Class Codes: B64G 1/244 Spacecraft control systems
• CPC Class Codes: B64G 1/283 using reaction wheels
• CPC Class Codes: B64G 1/36 using sensors, e.g. sun-sensors, horizon sensors
• CPC Class Codes: B64G 1/361 using star sensors
• CPC Class Codes: B64G 1/363 using sun sensors
• CPC Class Codes: B64G 1/401 Liquid propellant rocket engines Ion or plasma engines B64G1/413; Arcjets and other resistojets B64G1/415
• CPC Class Codes: B64G 1/402 Propellant tanks; Feeding propellants
• CPC Class Codes: B64G 1/425 Power storage
• CPC Class Codes: B64G 1/428 Power distribution and management
• CPC Class Codes: B64G 1/44 using radiation, e.g. deployable solar arrays
• CPC Class Codes: B64G 1/62 Systems for re-entry into the earth's atmosphere; Retarding or landing devices
• CPC Class Codes: B64G 1/64 Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
• CPC Class Codes: B64G 1/646 Docking or rendezvous systems refueling in space B64G1/4024
• CPC Class Codes: B64G 1/66 Arrangements or adaptations of apparatus or instruments, not otherwise provided for
• CPC Class Codes: G05D 1/00 Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots drive control systems specially adapted for autonomous road vehicles B60W60/00
• CPC Class Codes: G05D 1/0005 with arrangements to save energy
• CPC Class Codes: G05D 1/0094 : involving pointing a payload, e.g. camera, weapon, sensor, towards a fixed or moving target
• CPC Class Codes: G06F 17/00 : Digital computing or data processing equipment or methods, specially adapted for specific functions information retrieval, database structures or file system structures therefor G06F16/00

Abstract

Systems, apparatuses, and methods for removal of orbital debris are provided. In one embodiment, an apparatus includes a spacecraft control unit configured to guide and navigate the apparatus to a target. The apparatus also includes a dynamic object characterization unit configured to characterize movement, and a capture feature, of the target. The apparatus further includes a capture and release unit configured to capture a target and deorbit or release the target. The collection of these apparatuses is then employed as multiple, independent and individually operated vehicles launched from a single launch vehicle for the purpose of disposing of multiple debris objects.

Claims

1. An apparatus, comprising:

a spacecraft, control unit configured to guide and navigate the apparatus to a target;

a dynamic object characterization unit configured to characterize movement, and a capture feature, of the target; and

a capture and release unit configured to capture the target and release the target.

2. The apparatus of claim 1, wherein the capture and release unit comprises:

a mast, a plurality of throat sensors, and a plurality of tip sensors.

3. The apparatus of claim 2, wherein the mast is configured to extend into the capture feature of the target.

4. The apparatus of claim 2, wherein the mast is further configured to retract after capturing the target.

5. The apparatus of claim 2, wherein the mast comprises a snare configured to inflate within the capture feature of the target to facilitate capture of the target.

6. The apparatus of claim 2, wherein the mast comprises a plurality of rollers configured to guide the mast within the capture feature of the target.

7. The apparatus of claim 2, wherein the plurality of throat sensors are configured to detect whether the mast has entered the capture feature of the target.

8. The apparatus of claim 2, wherein the plurality of tip sensors are configured to detect whether the mast is in physical contact with the capture feature of the target.

9. The apparatus of claim 1, wherein the capture and release unit further comprises a plurality of airbags configured to inflate within the capture feature of the target to align the apparatus with the target.

10. The apparatus of claim 1, further comprising a cowcatcher configured to protect the capture and release unit and react launch loads of the apparatus.

11. The apparatus of claim 1, further comprising a plurality of rollers configured to guide the apparatus within the capture feature of the target.

12. The apparatus of claim 1, further comprising:

a plurality of pressurized helium tanks containing pressurized helium.

13. The apparatus of claim 12, wherein at least one of the plurality of pressurized helium tanks is configured to release the pressurized helium into a mast to cause the mast to extend into the capture feature of the target.

14. The apparatus of claim 1, further comprising:

a power unit configured to power the apparatus prior to, during, and after, capture of the target.

15. The apparatus of claim 14, wherein the power unit comprises a solar array configured to provide energy to the apparatus.

16. The apparatus of claim 15, wherein the solar array is further configured to expand when collecting energy.

17. The apparatus of claim 15, wherein the solar array is further configured to retract when the apparatus performs a rendezvous and capture sequence on the target.

18. The apparatus of claim 14, wherein the power unit further comprises at least one battery configured to provide energy to the apparatus.

19. The apparatus of claim 1, further comprising:

a propulsion unit configured to drive and rotate the apparatus.

20. The apparatus of claim 19, wherein the propulsion unit comprises a main engine configured to drive the apparatus in a forward direction.

21. The apparatus of claim 19, wherein the propulsion unit further comprises a plurality of thrusters to rotate the apparatus.

22. The apparatus of claim 1, wherein the spacecraft control unit is further configured to perform an autonomous approach to a target and control the target when the target is captured.

23. The apparatus of claim 1, wherein the dynamic object characterization unit is further configured to analyze physical and motion characteristics of the target to enable the spacecraft control unit to produce an approach and capture solution.

24. The apparatus of claim 23, wherein the physical and motion characteristics of the target are analyzed based on data received from a plurality of sensors.

25. The apparatus of claim 1, further comprising:

a plurality of noise radars configured to provide, data with respect to a motion of the target.

26. The apparatus of claim 1, further comprising:

an infrared camera configured to provide bearing data when rendezvousing with the target.

27. The apparatus of claim 1,

an infrared camera configured to capture media of a target, and provide the media to a ground control unit when rendezvousing with the target, wherein

the media comprises video data, image data or both.

28. A method, comprising:

performing. by an apparatus, a rendezvous procedure with a target;

analyzing, by the apparatus, the target prior to capturing the target; and

capturing, by the apparatus, the target based on the analysis of the target.

29. The method of claim 28, further comprising:

separating from a launch vehicle at lower earth orbit.

30. The method of claim 28, further comprising:

loitering in lower earth orbit until the target is near the apparatus.

31. The method of claim 28, wherein the rendezvous procedure is performed when orbital planes of the target and apparatus match.

32. The method of claim 28, further comprising:

calculating an approach to the target based on the analysis of the target.

33. The method of claim 28, wherein the capturing of the target comprises performing a translation and rotation thrust to place the apparatus in proper orientation on a radial pattern with an X-axis of the apparatus positioned near a capture feature of the target.

34. The method of claim 28, wherein the capturing of the target comprises adjusting and stabilizing the apparatus to position the apparatus in a proper relative position and attitude on a radial pattern with an X-axis position on a centerline of a capture feature.

35. The method of claim 28, wherein the capturing of the target comprises matching a plane of the apparatus with a plane of the target, and matching a rotation rate of the apparatus with the rotation rate of the target.

36. The method of claim 28, wherein the capturing of the target comprises connecting with the target, such that the apparatus and target are structurally connected.

37. The method of claim 28, further comprising:

deorbiting the target when the target is captured.

38. A system, comprising;

a plurality of vehicles, each vehicle comprising a cowcatcher configured to protect instruments and react launch loads on the vehicle; and

a single launch vehicle comprising a payload, the payload comprising the plurality of vehicles, wherein

each of the plurality of vehicles are oriented upside down on the payload.

39. The system of claim 38, wherein the launch vehicle releases each of the plurality of vehicles in succession.

40. The system of claim 38, wherein each of the plurality of vehicles loiters in orbit until a target plane assigned to the respective vehicle is near the respective vehicle plane.

41. The system of claim 38, wherein each of the plurality of vehicles is further configured to rendezvous with an assigned target.

42. The system of claim 38, wherein each of the plurality of vehicles is further configured to analyze an assigned target prior to capturing the assigned target.

43. The system of claim 38, wherein each of the plurality of vehicles is further configured to capture the assigned target.

44. The system of claim 42, wherein each of the plurality of vehicles is further configured to capture another pre-assigned target when the assigned target is not capturable.

45. The system of claim 38, wherein each of the plurality of vehicles is further configured to deorbit an assigned captured target.

46. The system of claim 38, wherein each vehicle is further configured to deorbit itself when failure to capture the target occurs.

47. The system of claim 38, further comprising:

a ground support and operations unit configured to simultaneously plan, navigate and perform operations on a plurality of vehicles to capture and deorbit a plurality of targets.

48. The system of claim 38 wherein each of the plurality of vehicles are clustered on the payload, and are independently targeted and independently operated.