System and method for debris capture

Patent metadata

Field	Value
Publication number	US-12017803-B2
Application number	US-202217875543-A
Country	US
Kind code	B2
Filing date	Jul 28, 2022
Priority date	Jul 28, 2021
Publication date	Jun 25, 2024
Grant date	Jun 25, 2024

Abstract

A method for capturing and deorbiting space debris includes: deploying a space debris capturing device in planetary orbit; receiving an initial target set including a first database of space debris targets that are within range of the space debris capturing device; performing a first algorithm to convert the initial target set to an accessible target set including a second database of space debris targets that are within range of the space debris capturing device; performing a second algorithm to convert the accessible target set to a final target set including a third database of space debris targets to be captured by the space debris capturing device capturing the first space debris target via a capture mechanism of the space debris capturing device; jettisoning the capture mechanism and the first captured space debris target into a decaying orbit; one of the remaining space debris targets of the third database; and positioning the space debris capturing device and the final captured space debris target into a decaying orbit.

First claim

What is claimed is:

1. A method for capturing and deorbiting space debris, the method comprising:
providing a space debris capturing device;
deploying the space debris capturing device in planetary orbit;
determining, via an onboard global positioning system unit, the position and orbit velocity of the space debris capturing device;
receiving an initial target set comprising a first database of space debris targets that are within range of the space debris capturing device;
performing a first algorithm to convert the initial target set to an accessible target set comprising a second database of space debris targets that are within range of the space debris capturing device, the second database is smaller than the first database;
performing a second algorithm to convert the accessible target set to a final target set comprising a third database of space debris targets to be captured by the space debris capturing device, the third database is smaller than the second database;
transferring the space debris capturing device to a position within a capture range of a first space debris target of the third database;
capturing the first space debris target via a capture mechanism of the space debris capturing device;
jettisoning the capture mechanism and the first captured space debris target into a decaying orbit;
repeating the transferring, capturing, and jettisoning steps for all but a final one of the remaining space debris targets of the third database; and
positioning the space debris capturing device and the final captured space debris target into a decaying orbit.

2. The method for capturing and deorbiting space debris of claim 1 , wherein the first algorithm comprises a filter-sorter algorithm.

3. The method for capturing and deorbiting space debris of claim 1 , wherein the data of the initial target set is in a two-line element format and wherein performing the first algorithm comprises:
extracting, for each space debris target of the first database, classical orbit elements from indices of the two-line element formatted data;
calculating, for each space debris target of the first database, the delta-V required to transfer the space capturing device to the position within the capture range of the respective space debris target;
deleting the data of any space debris target of the first database for which the respective calculated transfer delta-V exceeds a predetermined value; and
outputting the accessible target set.

4. The method for capturing and deorbiting space debris of claim 3 , wherein calculating the transfer delta-V comprises calculating the delta-V required for a two-burn non-Hohmann transfer between two inclined elliptical orbits having arbitrarily oriented apse lines.

5. The method for capturing and deorbiting space debris of claim 3 , wherein the first database comprises at least ten thousand space debris targets and the second database comprises less than one hundred space debris targets.

6. The method for capturing and deorbiting space debris of claim 1 , wherein the second algorithm comprises a genetic algorithm.

7. The method for capturing and deorbiting space debris of claim 6 , wherein performing the second algorithm comprises:
receiving space debris capture parameters comprising a total propellant budget, a total number of space debris targets for capture, and a maximum weight that can be supported by the capture mechanism;
receiving the accessible target set and loading the data for each space debris target of the second database into a parameter matrix;
scoring each space debris target of the second database via a fitness function of the genetic algorithm;
defining lower and upper bound constraints for a non-linear constraint function of the genetic algorithm;
performing the genetic algorithm for each space debris target of the second database using the scored fitness function and the non-linear constraint function;
ranking each space debris target of the second database based on the space debris capture parameters;
deleting the data of any space debris target of the second database for which the respective ranking exceeds the total number of space debris targets for capture; and
outputting the final target set.

8. The method for capturing and deorbiting space debris of claim 7 , wherein the third database comprises no more than four space debris targets.

9. The method for capturing and deorbiting space debris of claim 1 , wherein the space debris capture device comprises:
a debris capture module housing the capture mechanism;
a control module; and
a propulsion module configured to adjust the position of the space debris capture device in space.

10. The method for capturing and deorbiting space debris of claim 9 , wherein the space debris capture device further comprises at least one solar array configured to provide electrical power to the space debris capture device.

11. The method for capturing and deorbiting space debris of claim 9 , wherein the capture mechanism comprises:
at least one capture barrel;
at least one capture net configured to fit within a first chamber of the capture barrel;
an electromagnetic tether attached to a first end of the capture net;
a power source configured to fit within a second chamber of the capture barrel and configured to provide electrical power to the electromagnetic tether;
a set of carry-weights attached to the capture net; and
a set of springs associated with the set of carry-weights, the set of springs is configured to exert a force on the carry-weights sufficient to launch the capture net from the capture barrel.

12. The method for capturing and deorbiting space debris of claim 11 , wherein capturing the first space debris target comprises:
releasing the set of springs to launch the capture net from the capture barrel;
carrying, via the momentum of the carry-weights, the capture net toward the first space debris target and pulling, via the momentum of the carry-weights, the capture net into an open configuration;
entangling the capture net around the first space debris target; and
securing the capture net around the first space debris target via hook-and-loop fasteners attached to the carry-weights that engage associated hook-and-loop fasteners of the entangled capture net.

13. The method for capturing and deorbiting space debris of claim 1 , wherein the capture range is about two meters.

14. The method for capturing and deorbiting space debris of claim 1 , wherein the space debris targets are in low Earth orbit.

Assignees

• Lyons Jackson Michael
• Anderson Kurt
• Rensselaer Polytech Inst

Inventors

• Lyons Jackson Michael
• Anderson Kurt

Classifications

• B64G1/66 Primary

  Arrangements or adaptations of apparatus or instruments, not otherwise provided for · CPC title

• B64G1/6462

  characterised by the means for engaging other vehicles · CPC title

• B64G1/1081

  for debris removal · CPC title

• B64G1/244

  Spacecraft control systems · CPC title

• B64G1/10 Primary

  Artificial satellites; Systems of such satellites; Interplanetary vehicles (space shuttles B64G1/14) · CPC title