Drag-based propellant-less small satellite attitude orbit and de-orbit control system

Patent metadata

Field	Value
Publication number	US-11267589-B2
Application number	US-201716324396-A
Country	US
Kind code	B2
Filing date	Nov 14, 2017
Priority date	Nov 16, 2016
Publication date	Mar 8, 2022
Grant date	Mar 8, 2022

Abstract

In an example embodiment, an attitude, orbit, and de-orbit control system (AODCS) for a satellite is provided. In an example embodiment, the AODCS system comprises one or more selectively retractable booms. The one or more selectively retractable booms are collectively configured to provide a selectively adjustable drag during de-orbiting of a satellite over a predefined de-orbiting time.

First claim

That which is claimed:

1. An attitude, orbit, and de-orbit control system (AODCS) for a satellite, the system comprising:
one or more selectively retractable booms, said one or more selectively retractable booms being collectively configured to provide a selectively adjustable drag during de-orbiting of a satellite over a predefined de-orbiting time; and
a system controller configured to generate one or more instructions for causing retracting or extending of at least one of the one or more selectively retractable booms to control the drag on the satellite.

2. The AODCS of claim 1 , wherein the one or more selectively retractable booms comprise four selectively retractable booms.

3. The AODCS of claim 2 , wherein:
a first deployer secures a first boom of the one or more selectively retractable booms to the satellite,
a second deployer secures a second boom of the one or more selectively retractable booms to the satellite,
a third deployer secures a third boom of the one or more selectively retractable booms to the satellite,
a fourth deployer secures a fourth boom of the one or more selectively retractable booms to the satellite, and
the second deployer being rotated 90 degrees with respect to the first deployer, the third deployer being rotated 180 degrees with respect to the first deployer, and the fourth deployer being rotated 270 degrees with respect to the first deployer.

4. The AODCS of claim 1 , wherein each of the one or more selectively retractable booms (a) is secured to a back surface of the satellite and (b) is inclined at an angle of 20° with respect to the back surface of the satellite.

5. The AODCS of claim 1 , wherein the one or more selectively retractable booms comprise at least two booms and at least one of:
each of the at least two selectively retractable booms is independently extendable and retractable; and
an angle between each of the at least two booms and a direction of travel of the satellite is independently adjustable.

6. The AODCS of claim 1 , wherein each selectively retractable boom is V-shaped in cross section.

7. The AODCS of claim 6 , wherein each selectively retractable boom has a V-shaped cross section with a rounded base.

8. The AODCS of claim 6 wherein each selectively retractable boom is shaped by three-point bending.

9. The AODCS of claim 1 , wherein each selectively retractable boom is secured to a drum.

10. The AODCS of claim 9 , wherein the drum is secured to a motor, the system controller is configured to generate one or more instructions for operation of the motor, and the motor is operational to retract or extend one of the booms.

11. The AODCS of claim 1 , wherein the one or more booms are configured to provide sufficient drag to de-orbit a 15 kg satellite from a low Earth orbit in 25 years.

12. The AODCS of claim 1 , further comprising one or more magnetorquers.

13. The AODCS of claim 12 , wherein the one or more magnetorquers comprise five magnetorquers, four of the magnetorquers are disposed between adjacent deployers, and at least one of the magnetorquers is disposed in a plane that is generally parallel to back surface of the satellite body.

14. The AODCS of claim 12 , wherein the one or more magnetorquers are configured to adjust the angular momentum of the satellite so that the satellite may efficiently exit a tumbling state and the one or more booms are not extended until the satellite exits the tumbling state.

15. The AODCS of claim 1 , wherein a selectively retractable boom of the one or more selectively retractable booms has a flat width substantially equal to 4 cm.

16. A satellite comprising an attitude, orbit, and de-orbit control system (AODCS), the AODCS comprising:
one or more selectively retractable booms, said one or more selectively retractable booms being collectively configured to provide a selectively adjustable drag during de-orbiting of a satellite over a predefined de-orbiting time; and
a system controller configured to generate one or more instructions for causing retracting or extending of at least one of the one or more selectively retractable booms to control the drag on the satellite.

17. The satellite of claim 16 , wherein the AODCS further comprises one or more magnetorquers.

18. The satellite of claim 17 , wherein the one or more selectively retractable booms comprises four selectively retractable booms and the one or more magnetorquers comprises five magnetorquers.

19. An attitude, orbit, and de-orbit control system (AODCS) for a satellite, the system comprising: one or more selectively retractable booms, said one or more selectively retractable booms being collectively configured to provide a selectively adjustable drag during de-orbiting of a satellite over a predefined de-orbiting time; and
one or more magnetorquers, wherein the one or more magnetorquers comprise five magnetorquers, four of the magnetorquers are disposed between adjacent deployers, and at least one of the magnetorquers is disposed in a plane that is generally parallel to back surface of the satellite body.

20. The AODCS of claim 19 , further comprising at least one magnetometer.

Assignees

• Univ Florida
• Us Gov Administrator Of Nasa
• Nasa

Inventors

• Bevilacqua Riccardo
• Guglielmo David C
• Omar Sanny
• Fineberg Laurence
• Treptow Justin
• Clark Scott
• Johnson Yusef
• Poffenberger Bradley

Classifications

• B64G1/244 Primary

  Spacecraft control systems · CPC title

• B64G1/623

  Retarding devices, e.g. retrorockets · CPC title

• B64G1/2225

  Rolling or unfurling (B64G1/2227 takes precedence) · CPC title

• B64G1/66

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

• B64G1/36

  using sensors, e.g. sun-sensors, horizon sensors · CPC title