Satellite system with orbital debris avoidance

Patent metadata

Field	Value
Publication number	US-12473102-B2
Application number	US-202218281474-A
Country	US
Kind code	B2
Filing date	Mar 11, 2022
Priority date	Mar 11, 2021
Publication date	Nov 18, 2025
Grant date	Nov 18, 2025

Abstract

The present disclosure provides a satellite system with orbital debris avoidance. In one embodiment, the satellite system includes debris sensor circuitry to scan orbital debris items in an orbital debris field; and sensor controller circuitry to determine a search window within the orbital debris field based on, at least, uncertainties associated with a velocity of the satellite (Vsatellite) and uncertainties associated with a velocity of at least one debris item (Vdebris), the sensor controller circuitry also to control the debris sensor circuitry to detect the at least one debris item within the search window.

First claim

What is claimed is:

1 . A satellite system with orbital debris avoidance, comprising:
debris sensor circuitry to scan orbital debris items in an orbital debris field; and sensor controller circuitry to determine a search window within the orbital debris field based on, at least, uncertainties associated with a velocity of the satellite (Vsatellite) and uncertainties associated with a velocity of at least one debris item (Vdebris), the sensor controller circuitry also to control the debris sensor circuitry to detect the at least one debris item within the search window; wherein:
the search window is defined within a debris position uncertainty zone; and
the search window is a field angle Θ based on the uncertainties associated with the velocity of the satellite (Vsatellite) and the uncertainties associated with the velocity of the at least one debris item (Vdebris).

2 . The satellite system of claim 1 , wherein the sensor controller circuitry further to determine the search window based on uncertainties associated with the debris sensor circuitry.

3 . The satellite system of claim 1 , wherein the sensor controller circuitry further to determine the search window based on a size of the satellite and uncertainties associated with a relative velocity (Vrel) between the satellite and the at least one debris item.

4 . The satellite system of claim 1 , further comprising collision prediction circuitry to generate collision alert data based on space Vdebris and Vsatellite; wherein the collision alert data includes approximate time of collision between the satellite and the at least one debris item.

5 . The satellite system of claim 4 , wherein the sensor controller circuitry further to determine the search window based on the collision alert data.

6 . The satellite system of claim 1 , wherein the sensor controller circuitry further to generate avoidance instructions to avoid a collision between the satellite and at least one debris item based on the detection of the at least one debris item within the search window.

7 . The satellite system of claim 1 , wherein the sensor controller circuitry also to control the debris sensor circuitry to scan within the search window according to a predefined scan pattern.

8 . The satellite system of claim 1 , wherein the debris sensor circuitry comprises laser circuitry to detect the at least one debris item.

9 . A method for a satellite to identify and avoid space debris, comprising:
determining, by sensor controller circuitry, a search window within an orbital debris field based on, at least, uncertainties associated with a velocity of the satellite (Vsatellite) and uncertainties associated with a velocity of at least one debris item (Vdebris) within the debris field; and controlling, by the sensor controller circuitry, debris sensor circuitry to detect the at least one debris item within the search window; wherein:
the search window is defined within a debris position uncertainty zone; and
the search window is a field angle θ based on the uncertainties associated with the velocity of the satellite (Vsatellite) and the uncertainties associated with the velocity of the at least one debris item (Vdebris).

10 . The method of claim 9 , further comprising determining, by the sensor controller circuitry, the search window based on uncertainties associated with the debris sensor circuitry.

11 . The method of claim 9 , further comprising determining, by the sensor controller circuitry, the search window based on a size of the satellite and uncertainties associated with a relative velocity (Vrel) between the satellite and the at least one debris item.

12 . The method of claim 9 , further comprising generating, by collision prediction circuitry, collision alert data based on space Vdebris and Vsatellite; wherein the collision alert data includes approximate time of collision between the satellite and the at least one debris item.

13 . The method of claim 12 , wherein the sensor controller circuitry further to determine the search window based on the collision alert data.

14 . The method of claim 9 , further comprising generating, by collision prediction circuitry, avoidance instructions to avoid a collision between the satellite and at least one debris item based on the detection of the at least one debris item within the search window.

15 . The method of claim 9 , further comprising controlling the debris sensor circuitry, by the sensor controller circuitry, to scan the debris items within the search window according to a predefined scan pattern.

16 . The method of claim 9 , wherein the debris sensor circuitry comprises laser circuitry to detect the at least one debris item.

17 . A non-transitory computer readable device including instructions that, when executed by processor circuitry, cause the processor circuitry to perform operations comprising:
determine a search window within an orbital debris field based on, at least, uncertainties associated with a velocity of the satellite (Vsatellite) and uncertainties associated with a velocity of at least one debris item (Vdebris) within the debris field; and control debris sensor circuitry to detect the at least one debris item within the search window; wherein:
the search window is defined within a debris position uncertainty zone; and
the search window is a field angle θ based on the uncertainties associated with the velocity of the satellite (Vsatellite) and the uncertainties associated with the velocity of the at least one debris item (Vdebris).

18 . The non-transitory computer readable device of claim 17 including instructions that, when executed by the processor circuitry, cause the processor circuitry to perform operations further comprising:
determine the search window based on uncertainties associated with the debris sensor circuitry.

19 . The non-transitory computer readable device of claim 17 including instructions that, when executed by the processor circuitry, cause the processor circuitry to perform operations further comprising:
determine the search window based on a size of the satellite and uncertainties associated with a relative velocity (Vrel) between the satellite and the at least one debris item.

20 . The non-transitory computer readable device of claim 17 including instructions that, when executed by the processor circuitry, cause the processor circuitry to perform operations further comprising:
determine collision alert data based on space Vdebris and Vsatellite; wherein the collision alert data includes approximate time of collision between the satellite and the at least one debris item.

21 . The non-transitory computer readable device of claim 20 including instructions that, when executed by the processor circuitry, cause the processor circuitry to perform operations further comprising:
determine the search window based on the collision alert data.

22 . The non-transitory computer readable device of claim 17 including instructions that, when executed by the processor circuitry, cause the processor circuitry to perform operations further comprising:
generate avoidance instructions to avoid a collision between the satellite and at least one debris item based on the detection of the at least one debris item within the search window.

23 . The non-transitory computer readable device of claim 17 including instructions that, when executed by the processor circuitry, cause the processor circuitry t

Assignees

• Univ Arizona

Inventors

• Vance Leonard
• Moreno Jose Maria Fernandez
• Thangavelautham Jekan

Classifications

• B64G1/2429

  Station keeping · CPC title

• B64G1/68 Primary

  of meteoroid or space debris detectors · CPC title