Detecting orbital debris

1. A method performed by a network device, the method comprising:

determining an exposure time associated with an image sensor that is coupled to a spacecraft and configured to capture an image of a target object orbiting the Earth;

computing a first relative angular velocity associated with the target object based on the exposure time and a physical dimension of the image sensor;

identifying a first pointing direction of the image sensor for initiating a search for the target object;

accessing known orbital data for the target object;

generating, based on the first pointing direction and the known orbital data, a first set of angular velocity regions (AVRs) that indicate probabilities of the target object having different angular velocities as viewed by the image sensor when the image sensor is pointing in the first pointing direction, wherein each AVR has a central angular velocity and size of an AVR is limited by the first relative angular velocity;

selecting a first AVR from the first set of AVRs for scanning by the image sensor; and

generating a search schedule that includes a first entry to instruct the spacecraft to search for the target object in the first AVR by rotating the image sensor, starting at the first pointing direction, at an angular speed and in a direction corresponding to the central angular velocity of the first AVR,

wherein the network device includes a satellite ground station, and wherein the spacecraft includes a satellite.

2. The method of claim 1 , wherein the physical dimension of the image sensor includes a size of a pixel of the image sensor, and

wherein computing the first relative angular velocity comprises dividing the size of the pixel by the exposure time.

3. The method of claim 1 , further comprising:

determining whether the search schedule is complete;

based on determining that the search schedule is not complete, determining a second pointing direction of the image sensor at completion of scanning the first AVR;

generating, based on the second pointing direction and the orbital data, a second a second set of AVRs that indicate probabilities of the target object having different angular velocities as viewed by the image sensor when the image sensor is pointing in the second pointing direction;

selecting a second AVR from the second set of AVRs for scanning by the image sensor; and

adding a second entry to the search schedule that instructs the spacecraft to search for the target object in the second AVR by rotating the image sensor, starting at the second pointing direction, at an angular speed and in a direction corresponding to the central angular velocity of the second AVR.

4. The method of claim 3 , wherein a number of AVRs in the second set is different from a number of AVRs in the first set.

5. The method of claim 1 , further comprising:

determining whether the search schedule is complete; and

based on determining that the search schedule is complete, transmitting the search schedule to the spacecraft.

6. The method of claim 5 , further comprising:

receiving, at the spacecraft and from the network device, the search schedule;

reading, by the spacecraft, the first entry in the search schedule;

based on reading the first entry, slewing, by the spacecraft, the image sensor starting from the first pointing direction for scanning the first AVR; and

controlling, by the spacecraft, the image sensor for recording sensor readings as the image sensor scans the first AVR.

7. The method of claim 6 , further comprising:

determining, by the spacecraft, whether there are additional entries in the search schedule;

based on determining that there are additional entries in the search schedule, reading, by the spacecraft, a second entry in the search schedule that includes instructions to search for the target object in a second AVR by rotating the image sensor, starting at a second pointing direction, at an angular speed and in a direction corresponding to the central angular velocity of the second AVR;

responsive to reading the second entry, slewing, by the spacecraft, the image sensor starting from the second pointing direction for scanning the second AVR; and

controlling, by the spacecraft, the image sensor for recording sensor readings as the image sensor scans the second AVR.

8. The method of claim 1 , wherein the target object includes orbital debris.

9. The method of claim 1 , wherein the exposure time includes a time used by the image sensor for recording sensor readings, the exposure time based on one or more of a noise floor, a threshold signal-to-noise ratio (threshold SNR) associated with the image sensor, a size of the target object, or a distance of the target object from the spacecraft.

10. The method of claim 1 , wherein the size of an AVR is proportional to a magnitude of the angular velocity at the center of the AVR, the size of an AVR being smaller for a smaller angular velocity at the center of the AVR in comparison to a larger angular velocity at the center of the AVR.

11. The method of claim 1 , wherein selecting the first AVR from the first set of AVRs comprises selecting the first AVR based on one of a random selection strategy or a probability of detection of the target object that is associated with each AVR in the first set of AVRs.

12. A device including a storage medium storing instructions that, when executed by one or more processors, are configured to cause the one or more processors to perform operations comprising:

determining an exposure time associated with an image sensor that is coupled to a spacecraft and configured to capture an image of a target object orbiting the Earth;

computing a first relative angular velocity associated with the target object based on the exposure time and a physical dimension of the image sensor;

identifying a first pointing direction of the image sensor for initiating a search for the target object;

accessing known orbital data for the target object;

generating, based on the first pointing direction and the known orbital data, a first set of angular velocity regions (AVRs) that indicate probabilities of the target object having different angular velocities as viewed by the image sensor when the image sensor is pointing in the first pointing direction, wherein each AVR has a central angular velocity and size of an AVR is limited by the first relative angular velocity;

selecting a first AVR from the first set of AVRs for scanning by the image sensor; and

generating a search schedule that includes a first entry to instruct the spacecraft to search for the target object in the first AVR by rotating the image sensor, starting at the first pointing direction, at an angular speed and in a direction corresponding to the central angular velocity of the first AVR,

wherein the device includes a satellite ground station, and wherein the spacecraft includes a satellite.

13. The device of claim 12 , wherein the physical dimension of the image sensor includes a size of a pixel of the image sensor, and

wherein computing the first relative angular velocity comprises dividing the size of the pixel by the exposure time.

14. The device of claim 12 , wherein the instructions are configured to cause the one or more processors to perform operations comprising further comprising:

determining whether the search schedule is complete;

based on determining that the search schedule is not complete, determining a second pointing direction of the image sensor at completion of scanning the first AVR;

generating, based on the second pointing direction and the orbital data, a second a second set of AVRs that indicate probabilities of the target object having different angular velocities as viewed by the image sensor when the image sensor is pointing in the second pointing direction;

selecting a second AVR from the second set of AVRs for scanning by the image sensor; and

adding a second entry to the search schedule that instructs the spacecraft to search for the target object in the second AVR by rotating the image sensor, starting at the second pointing direction, at an angular speed and in a direction corresponding to the central angular velocity of the second AVR.

15. The device of claim 14 , wherein a number of AVRs in the second set is different from a number of AVRs in the first set.

16. The device of claim 12 , wherein the instructions are configured to cause the one or more processors to perform operations comprising further comprising:

determining whether the search schedule is complete; and

based on determining that the search schedule is complete, transmitting the search schedule to the spacecraft.

17. The device of claim 16 , wherein the instructions are configured to cause the one or more processors to perform operations comprising further comprising:

receiving, at the spacecraft and from the device, the search schedule;

reading, by the spacecraft, the first entry in the search schedule;

based on reading the first entry, slewing, by the spacecraft, the image sensor starting from the first pointing direction for scanning the first AVR; and

controlling, by the spacecraft, the image sensor for recording sensor readings as the image sensor scans the first AVR.

18. The device of claim 17 , wherein the instructions are configured to cause the one or more processors to perform operations comprising further comprising:

determining, by the spacecraft, whether there are additional entries in the search schedule;

based on determining that there are additional entries in the search schedule, reading, by the spacecraft, a second entry in the search schedule that includes instructions to search for the target object in a second AVR by rotating the image sensor, starting at a second pointing direction, at an angular speed and in a direction corresponding to the central angular velocity of the second AVR;

responsive to reading the second entry, slewing, by the spacecraft, the image sensor starting from the second pointing direction for scanning the second AVR; and

controlling, by the spacecraft, the image sensor for recording sensor readings as the image sensor scans the second AVR.

19. The device of claim 12 , wherein the target object includes orbital debris.

20. The device of claim 12 , wherein the exposure time includes a time used by the image sensor for recording sensor readings, the exposure time based on one or more of a noise floor, a threshold signal-to-noise ratio (threshold SNR) associated with the image sensor, a size of the target object, or a distance of the target object from the spacecraft.

21. The device of claim 12 , wherein the size of an AVR is proportional to a magnitude of the angular velocity at the center of the AVR, the size of an AVR being smaller for a smaller angular velocity at the center of the AVR in comparison to a larger angular velocity at the center of the AVR.

22. The device of claim 12 , wherein selecting the first AVR from the first set of AVRs comprises selecting the first AVR based on one of a random selection strategy or a probability of detection of the target object that is associated with each AVR in the first set of AVRs.