Method and apparatus for disposal/recovery of orbiting space debris

• US 5,421,540 A
• Filed: 08/26/1992
• Issued: 06/06/1995
• Est. Priority Date: 08/26/1992
• Status: Expired due to Fees

• Current Assignee: Paul C. Ting
• Original Assignee: Paul C. Ting
• Inventors: Ting, Paul C.
• Primary Examiner(s): Huppert, Michael S.
• Assistant Examiner(s): MARQUIS, LISSI MOJICA
• Application Number:
  US07/937,057
• Time in Patent Office: 1,014 Days
• Field of Search: 244/158 R, 244/158 A, 244/159, 244/160, 244/161, 244/163
• US Class Current: 244/158.1
• CPC Class Codes: B64G 1/1078 Maintenance satellites refueling in space B64G1/4024
• CPC Class Codes: B64G 1/1081 for debris removal
• CPC Class Codes: B64G 1/22 Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
• CPC Class Codes: B64G 1/62 Systems for re-entry into the earth's atmosphere; Retarding or landing devices
• CPC Class Codes: B64G 1/623 Retarding devices, e.g. retrorockets
• CPC Class Codes: B64G 1/646 Docking or rendezvous systems refueling in space B64G1/4024

Abstract

Method and apparatus for elimination of space debris from Earth orbit to thus minimize the hazards to space personnel and equipment that are now present as increasing as space exploration and use continues. As a first aspect space debris is collected and deorbited where it is completely burned by the heat developed by the kinetic energy of its reentry through the Earth'"'"'s atmosphere. As a second aspect, valuable space debris is collected and deorbited in a recovery reentry vehicle and which lands at a designated site on the Earth'"'"'s surface. A third method includes parking collected space debris in a designated parking orbit at a location well away from traveled orbit zones, including a high, relatively unused orbit sector. A fourth method includes solar and laser energy destruction of the non-valuable space debris while in orbit. A fifth aspect of this invention contemplates ejecting collected, containerized space debris from Earth orbit to an interplanetary orbit that does not intersect any planet of this solar system. The last method is to immediately remove the space debris after any new activities in space.

Claims

1. A method for disposal of orbiting space debris, comprising:

(a) placing a space debris vehicle in orbit, said space debris vehicle having a space debris capture subsystem and a power subsystem in releasable assembly, said space debris capture subsystem having a receptacle for receiving space debris and dampers and damper control sensors for receiving said space debris within said receptacle;

(b) placing in orbit a debris container of a dimension for containing a predetermined volume of space debris;

(c) maneuvering said space debris vehicle by means of said power subsystem for collection of space debris within said receptacle of said space debris capture subsystem;

(d) by manipulation of said space debris dampers by means of said damper control sensors transferring collected space debris from said space debris capture subsystem into said debris container;

(e) decoupling said power subsystem from said space debris capture subsystem;

coupling said debris container in powering and maneuvering assembly with said space debris vehicle

(g) initiating deorbiting maneuvering of said debris container;

for entry into the Earth'"'"'s atmosphere and for total destruction of said debris container and the space debris contained therein by means of heat developed by kinetic energy during entry into the Earth'"'"'s atmosphere;

(h) decoupling said power subsystem from said debris container when predetermined deorbiting of said debris container is assured; and

(i) reorbiting said power subsystem for further handling of space debris.

2. The method of claim 1, wherein a space vehicle in Earth orbit executes a maneuver to change Earth orbit or to escape Earth orbit and generates space debris, said method further comprising:

(a) immediately following said maneuver, with said power module, maneuvering said space debris vehicle to the orbital region of said maneuver; and

(b) capturing said newly generated space debris from said orbital region before wide dispersal thereof within said orbital region.

3. The method of claim 1, wherein said space debris capture subsystem is adapted for containing a space debris receptacle and at least one space debris receptacle being in orbit along with said space debris vehicle, said method including:

(a) during said maneuvering of said space debris vehicle, collecting space debris within a space debris receptacle separably located within said space debris capture subsystem;

(b) closing said dampers by manipulation of said damper control sensors to retain said space debris within said space debris receptacle; and

(c) accomplishing said transferring by jettisoning said space debris receptacle and the space debris contained therein from said space debris capture subsystem of said space debris vehicle and into said space debris container.

4. The method of claim 3, including:

(a) prior to said deorbiting of said space debris container, jettisoning a number of space debris filled space debris receptacles from said space debris vehicle into said space debris container; and

(b) closing said space debris container to prevent inadvertent separation of space debris or space debris receptacles therefrom.

5. The method of claim 1, including:

(a) providing video inspection of said space debris to assist in acquisition thereof by said space debris vehicle.

6. The method of claim 5, said space debris vehicle incorporates robotic arms having robot gripping hands and having at least one debris sweeper for manipulation by said robotic arms, said method further including:

with said robotic arms and said gripping robotic hands, establishing gripping of said space debris and moving said space debris into said space debris receptacle.

7. The method of claim 1, wherein said space debris capture subsystem includes a space debris receptacle removably located within said internal compartment and further includes a receptacle ejector for discharging said space debris receptacle from said internal chamber into said debris container, said method further comprising:

with said space debris vehicle in discharge orientation with said debris container, activating said receptacle ejector, thus ejecting a debris filled space debris receptacle from said internal compartment of said debris capture subsystem into said debris container for orbital storage and future deorbiting.

8. The method of claim 1, wherein said space debris capture subsystem incorporates a plurality of video cameras being specifically oriented relative to said space debris capture subsystem for differential angle viewing of space debris and providing differential angle signals enabling steering of said space debris vehicle for approach and alignment with said space debris and for controlled operation of said robotic arm and hand assembly for acquisition and handling of said space debris, said method further comprising:

(a) viewing said orbiting space debris with said video cameras during approach of said space debris vehicle thereto;

(b) generating electronic differential camera angle signals;

(c) transmitting said differential camera angle signals by telemetry to a signal processing facility; and

(d) transmitting electronic steering signals from said signal processing facility to said power subsystem for maneuvering said space debris vehicle into debris capturing relation with said orbiting space debris.

9. The method of claim 1, further comprising:

initiating an Earth atmosphere entry sequence by controlled retrothrust of said power subsystem for deorbiting said debris container and causing the same to fly an entry trajectory toward an Earth zone of low population density during which said debris container and the captured space debris within said debris container will be melted and vaporized by heat induced thereto by the kinetic energy of atmospheric reentry.

10. A method for disposal of orbiting space debris, comprising:

(a) placing a space debris vehicle in Earth orbit said space debris vehicle having a power subsystem and a space debris capture subsystem said space debris capture subsystem having an internal compartment for receiving space debris and further having at least one robotic arm and hand assembly for capturing space debris and placing it within said internal compartment and having retainer means for securing space debris within said internal compartment;

(b) placing in orbit a debris container of a dimension for containing a predeterminated volume of space debris;

(c) maneuvering said space debris vehicle by means of said power subsystem to orbiting space debris for collection thereof within said debris capture subsystem;

(d) with said robotic arm and hand assembly capturing space debris to which said space debris vehicle has maneuvered and placing it within said internal compartment;

(e) repeating said maneuvering and capturing of (c) and (d) above until said internal compartment is desirably filled with captured space debris;

(f) after said internal compartment has been suitably filled with captured space debris, maneuvering said space debris vehicle to rendezvous with said debris container;

(g) transferring said captured space debris from said internal compartment into said debris container; and

(h) after said debris container has been sufficiently filled with space debris. deorbiting said space debris container and its contained space debris for entry. into the Earth'"'"'s atmosphere and for total destruction of said debris container and the space debris contained therein by means of heat developed by kinetic energy during entry. into the Earth'"'"'s atmosphere.

11. The method of claim 10, wherein said capture subsystem further incorporates at least one space debris sweeper for manipulation by said robotic arm and hand assembly, said method further comprising:

with said debris capture subsystem selectively positioned relative to orbiting space debris of insufficient size for grasping by said robotic arm and hand assembly, manipulating said space debris sweeper for contacting said space debris and directing it into said internal compartment.

12. The method of claim 10 wherein a space debris vehicle in an initial Earth orbit region executes a maneuver to change Earth orbit or to escape Earth orbit and said maneuver generates space debris which begins to disperse within said initial Earth orbit region, said method further comprising:

(a) immediately following said maneuver, with said power module, maneuvering said space debris vehicle to said initial Earth orbit region; and

(b) capturing said newly generated space debris by means of said debris capture subsystem prior to wide dispersal thereof within said initial Earth orbit region.

13. A method for eliminating orbiting space debris from a designated orbit zone, comprising:

(a) placing in said designated orbit zone at least one space debris vehicle having a power subsystem and a debris capture subsystem and at least one space debris receptacle, said space debris vehicle having the capability of being controllably maneuvered within said designated orbit zone to rendezvous with orbiting space debris therein;

(b) placing a space debris container in an Earth orbit, said space debris container capable of receiving a plurality of said space debris receptacles;

(c) coupling said space debris vehicle in powering and maneuvering assembly with said space debris container after said space debris container has been suitably filled with space debris receptacles containing space debris;

(d) maneuvering said space debris vehicle with said space debris container for rendezvous with selected space debris;

(e) capturing said orbiting space debris; and

(f) controllably energizing said power subsystem for changing the altitude and orbit zone of said space debris vehicle thus removing said space debris from said designated orbit zone.

14. The method of claim 13, wherein said removing comprises:

causing controlled entry of said space debris into the Earth'"'"'s atmosphere for complete destruction of said space debris by heat induced thereto by kinetic energy.

15. Apparatus for removing orbiting space debris from a designated orbital zone about the earth, comprising:

(a) a space debris vehicle having a power subsystem incorporating a primary source of motive thrust and a plurality of directional control thrusters for orbital maneuvering and having a debris capture subsystem being separably connected to said power subsystem and defining an internal chamber and means for selectively closing said internal chamber, said debris capture subsystem further having means for directing space debris into said internal chamber and having a plurality of video cameras for differential angle visualization of space debris being approached and captured, said space debris vehicle further having an on board computer for controlling power and operational functions of said power subsystem and said debris capture subsystem; and

(b) a space debris container adapted to receive and contain a plurality of space debris receptacles containing space debris captured and deposited therein by said debris capture subsystem of said space debris vehicle, said space debris container being further adapted to receive said power subsystem in maneuvering connection therewith for selective power energized removal thereof from said designated orbit zone about the earth by selective deorbiting thereof for kinetic energy destruction upon Earth atmosphere reentry, by selective boosting thereof to a high parking orbit, by selective ejection thereof from Earth orbit and by selective destruction thereof while in orbit.

16. The apparatus of claim 15, wherein said space debris vehicle further includes:

(a) a debris receptacle being removably retained within said internal chamber and a debris receptacle ejector for displacing a filled debris receptacle from said internal chamber into said space debris container;

(b) said space debris container adapted to receive a plurality of space debris receptacles in retained relation therein; and

(c) said space debris vehicle having at least one robotic arm and hand assembly for gripping space debris and placing it within said space debris receptacle and a space debris sweeper adapted for manipulation by said robotic arm and hand assembly for sweeping small space debris into said space debris receptacle.

17. A method for removing space debris from Earth orbit, comprising:

(a) placing a space debris vehicle in Earth orbit, said space debris vehicle having a space debris capture subsystem and a power subsystem;

(b) placing in Earth orbit a debris container of a dimension for containing a predetermined volume of space debris;

(c) maneuvering said space debris vehicle by means of said power subsystem for collection of space debris;

(d) depositing said space debris within said debris container by means of said space debris capture subsystem and said power subsystem; and

(e) placing said debris container with said space debris therein in solar orbit by controlled thrust of said power subsystem.

18. The method of claim 17, including:

(a) after placing said debris container in Solar orbit, separating said space debris vehicle from said debris container; and

(b) returning said space debris vehicle to a desired Earth orbit by controlled thrust of said power subsystem.

19. A method for removing space debris from Earth orbit, comprising:

(a) placing a space debris vehicle in Earth orbit, said space debris vehicle having a space debris capture subsystem and a power subsystem, said power subsystem being capable of controlled reentry of the Earth'"'"'s atmosphere and controlled soft landing on the Earth and capable of protecting said space debris and said space debris vehicle from damage during reentry and soft landing;

(b) placing in Earth orbit a modified recovery module of a dimension for containing and protecting a predetermined volume of space debris;

(c) maneuvering said space debris vehicle by means of said power subsystem for collection of space debris;

(d) by means of said capture subsystem acquiring said space debris and placing said space debris within said modified recovery module;

(e) separating said capture subsystem from said space debris vehicle;

(f) coupling said power subsystem with said modified recovery module; and

(g) by controlled activation of said power subsystem causing reentry and soft landing of said space debris vehicle and said modified recovery module and said space debris contained therein.

20. The method of claim 19, wherein:

said space debris vehicle incorporates a landing system having a parachute system for stabilization and Earth atmosphere braking and a landing system for said soft Earth landing, said method further comprising;

causing controlled reentry and soft Earth landing of said space debris vehicle and said modified recovery module to permit undamaged recovery and salvage of said space debris.

21. The method of claim 19 wherein said space debris vehicle incorporates an auxiliary power supply and a thermal control system, said method further comprising:

controlling the temperature within said modified recovery module to protect valuable space debris during said Earth atmosphere reentry and soft landing by controlled activation of said thermal control system by said auxiliary power supply.

22. A method for capture and recovery of space debris from selected earth orbit zones, comprising:

(a) placing a space debris vehicle in a designated earth orbit, said space debris vehicle having a space debris capture subsystem and a power subsystem, said space debris capture subsystem having a robotic system including robotic arm and hand assemblies for establishing physical connection with said space debris and for moving said space debris relative to said space debris capture subsystem, said space debris capture subsystem further having a video camera system for use in identifying the location of space debris relative to said space debris capture subsystem and monitoring connection of said robotic arms and hand assemblies with and positioning of space debris by means of said robotic arm and hand assemblies;

(b) placing in earth orbit a modified recovery module of a dimension for containing and protecting said space debris;

(c) maneuvering said space debris vehicle by means of said power subsystem for selective collection of space debris by said robotic arm and hand assemblies;

(d) by means of said robotic arm and hand assemblies inserting said space debris into said modified recovery module;

(e) preparing said modified recovery module for deorbit maneuvering by coupling said space debris vehicle therewith;

(f) by means of said power subsystem, maneuvering said space debris vehicle with said modified recovery module coupled therewith to achieve deorbit maneuvering thereof;

(g) after assurance of deorbiting of said modified recovery module, separating said space debris vehicle from said modified recovery module and maneuvering said space debris vehicle to a designated orbit; and

(h) controlling deorbiting of said modified recovery module to soft landing at a designated landing site on the earth'"'"'s surface.

23. The method of claim 22, wherein said modified recovery module incorporates a parachute system for controlled reentry and controlled descent to soft landing, said method further comprising;

controllably deploying said parachute system for stabilization of said modified recovery module during reentry and for assisting in deceleration of said reentry to soft, parachute controlled landing at said designated landing site.

24. The method of claim 23, wherein said modified recovery module incorporates a landing gear system for achieving soft, controlled landing at a designated landing site on the Earth'"'"'s surface, said method further comprising:

(a) deploying said landing gear system after reentry velocity of said modified recovery module has decreased to a predetermined landing velocity;

(b) deploying said parachute system for parachute slowed landing of said modified recovery module at said designated landing site.

25. The method of claim 22, wherein said space debris capture subsystem incorporates a plurality of elongate tether elements for external physical connection of said space debris with said space debris, said method further comprising

(a) manipulating said elongate tether elements for tether attachment of said space debris to said debris capture subsystem;

(b) by means of said power subsystem, maneuvering said space debris vehicle with said space debris tethered thereto to a designated orbital region being well away from said predetermined orbital zone;

(c) releasing said plurality of elongate tether elements from said space debris; and

(d) with said power subsystem, returning said space debris vehicle to said designated earth orbit.

26. The method of claim 25, including:

(a) attaching said elongate tethering elements to said space debris;

(b) with said power subsystem maneuvering said space debris vehicle and towing said space debris to the immediate vicinity of said modified recovery module;

(c) placing said space debris within said modified recovery module; and

(d) returning said modified recovery module from orbit to a designated landing site.

27. Apparatus for recovery of space debris from a designated earth orbit zone, comprising:

(a) a space debris vehicle having a debris capture subsystem and a power subsystem said debris capture subsystem having a receptacle therein for receiving space debris;

(b) a plurality of elongate tethering elements being provided on said debris capture subsystem and being adapted for external attachment to inactive satellites and other large space debris;

(c) a robotic arm and hand system being provided on said debris capture subsystem for grappling onto space debris and for controllably moving said space debris relative to said space debris vehicle;

(d) a video camera system being provided on said debris capture subsystem for viewing space debris in the near vicinity of said space debris vehicle and enabling ground control personnel to receive video signals therefrom and visually monitor operation of said robotic arm and hand system and said elongate tether elements during handling of space debris by said debris capture subsystem.

28. The apparatus of claim 27, including:

(a) a modified recovery module being placed in said orbital zone and being adapted for receiving said space debris therein and for protecting said space debris during reentry through the earth'"'"'s atmosphere to soft landing on the earth'"'"'s surface, said modified recovery module having a parachute system for stabilizing said modified recovery module during a portion of its reentry and slowing said modified recovery module to a predetermined velocity;

(b) a landing system being provided on said modified recovery module and including deployable landing gear for permitting runway landing of said modified recovery module at a designated landing site on the Earth'"'"'s surface; and

(c) a thermal control system being provided for said modified recovery module for providing thermal protection for said space debris during reentry thereof.

29. The apparatus of claim 28, wherein said modified recovery module is an aeroassist flight experiment type recovery vehicle.

30. The apparatus of claim 28, wherein said modified recovery module is a biconic type recovery vehicle.

31. The apparatus of claim 28, wherein said modified recovery vehicle is a mushroom type recovery vehicle.

32. The apparatus of claim 28, wherein said modified recovery module is a domed type recovery vehicle.