Systems and methods for deploying a deorbiting device

Patent metadata

Field	Value
Publication number	US-11420775-B2
Application number	US-201816151986-A
Country	US
Kind code	B2
Filing date	Oct 4, 2018
Priority date	Oct 4, 2018
Publication date	Aug 23, 2022
Grant date	Aug 23, 2022

Abstract

To reduce space debris and decrease risks for future space flights and currently operating satellites, NASA requires all satellites to have an end of life deorbiting plan to prevent satellites from having long and indefinite orbit lifespan. Accordingly, disclosed herein are systems and methods for deploying a deorbiting drag device to dramatically decrease the orbit lifespan of satellites. One of the methods comprises: providing power, using a photovoltaic panel, to a central processing unit (CPU) of the satellite; determining, using a health sensor, a health status of the satellite by monitoring activities of the CPU; and releasing a deorbiting drag device based on the health status by diverting power from the photovoltaic panel to a release actuator.

First claim

The invention claimed is:

1. A system for deploying a deorbiting drag device on a satellite, the system comprising:
a flight computer;
a drag device;
a health sensor, coupled to the flight computer, the health sensor configured to monitor a health status of the satellite by pinging the flight computer, the health sensor comprising a switch;
a release actuator configured to retain the drag device in an undeployed position; and
a photovoltaic panel coupled to a satellite-power inlet, the health sensor, and to the release actuator, wherein the health sensor is configured to switch, using the switch, power generated by the photovoltaic panel from the satellite-power inlet to the release actuator based on the health status of the satellite, the health status of the satellite determined based on a lack of a response to the pinging of the flight computer, and wherein the release actuator is configured to release the deorbiting drag device upon receiving a current from the photovoltaic panel.

2. The system of claim 1 , wherein the health sensor comprises a pulse sensor configured to receive intermittent signals from a central processing unit of the satellite, wherein the release actuator is configured to release the deorbiting drag device when no intermittent signal is received by the pulse sensor for a predetermined amount of time.

3. The system of claim 1 , wherein the health sensor comprises a current-sensing circuit coupled between a central processing unit of the satellite and the photovoltaic panel, wherein the release actuator is configured to release the deorbiting drag device when a current draw is not detected for a predetermined amount of time.

4. The system of claim 1 , wherein the photovoltaic panel is a main power source of the satellite.

5. The system of claim 1 , further comprises a main internal power source and wherein the photovoltaic panel is a secondary power source of the satellite.

6. The system of claim 5 , wherein the health sensor comprises a current-sensing circuit configured to sense intermittent power draws from the main internal power source of the satellite, wherein the release actuator is configured to release the deorbiting drag device when intermittent power draws is not detected by the current-sensing circuit.

7. The system of claim 5 , wherein the health sensor comprises one or more voltage-sensing circuits configured to sense voltage across the main internal power source of the satellite and the photovoltaic panel, wherein the release actuator is configured to release the deorbiting drag device when a voltage is not detected from the main internal power source and the photovoltaic panel.

8. The system of claim 7 , further comprises a capacitor electrically coupled to the release actuator, wherein the capacitor is configured to discharge when there is a failure of both the main internal power source and the photovoltaic panel.

9. The system of claim 1 , wherein the deorbiting drag device comprises a device selected from a group of consisting of a sail, an electrodynamic tether, a drag chute, and a balloon.

10. The system of claim 1 , wherein the release actuator comprises a shape memory alloy wire configured to cause the deorbiting drag device to release upon receiving a current from the photovoltaic panel.

11. The system of claim 1 , wherein the release actuator comprises a burn wire configured to melt upon receiving a current from the photovoltaic panel.

12. A method for deploying a deorbiting drag device on a satellite, the system comprising:
providing power, using a photovoltaic panel, to a central processing unit (CPU) of the satellite;
determining, using a health sensor, a health status of the satellite by monitoring activities of the CPU based on a lack of a response to a pinging of the CPU; and
releasing a deorbiting device based on the health status by diverting power from the photovoltaic panel to a release actuator.

13. The method of claim 12 , wherein the deorbiting device comprises a passive drag device selected from a group of consisting of a sail, an electrodynamic tether, and a balloon.

14. The method of claim 12 , wherein the deorbiting device comprises an active device selected from a group ef consisting of an electrospray and plasma thruster.

15. The method of claim 12 , wherein determining the health status comprises monitoring, using a pulse sensor, intermittent signals from the CPU, and wherein power is diverted to the release actuator when no intermittent signal is detected for a predetermined amount of time.

16. The method of claim 12 , wherein determining the health status comprises monitoring, using a current-sensing circuit, power usage of the CPU, and wherein power is diverted to the release actuator when no power usage is detected for a predetermined amount of time.

17. The method of claim 12 , further comprises providing an internal power source to the CPU, wherein power from the photovoltaic panel is a secondary power source and the internal power source is a main power source.

18. The method of claim 16 , wherein determining the health status comprises monitoring, using a current-sensing circuit, intermittent power usage of the internal power source, and wherein power is diverted to the release actuator when no power usage is detected for a predetermined amount of time.

19. The method of claim 16 , wherein determining the health status comprises monitoring, using a voltage-sensing circuit, voltages from the internal power source and the photovoltaic panel, and wherein power is diverted to the release actuator when no voltage is detected from both the internal power source and the photovoltaic panel.

20. The method of claim 12 , wherein the release actuator comprises a shape memory alloy wire configured to release the drag device upon receiving a current from the photovoltaic panel.

Assignees

• Aerospace Corp

Inventors

• Fuller Jerome K

Classifications

• B64G1/10 Primary

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

• B64G1/623

  Retarding devices, e.g. retrorockets · CPC title

• B64G1/2229

  characterised by the deployment actuating mechanism (inflating B64G1/2227) · CPC title

• B64G1/2228

  characterised by the hold-down or release mechanisms · CPC title

• B64G1/443

  Photovoltaic cell arrays · CPC title