Energy efficient satellite maneuvering

Patent metadata

Field	Value
Publication number	US-10407185-B2
Application number	US-201816192411-A
Country	US
Kind code	B2
Filing date	Nov 15, 2018
Priority date	Nov 13, 2015
Publication date	Sep 10, 2019
Grant date	Sep 10, 2019

Abstract

Energy efficient satellite maneuvering is described herein. One disclosed example method includes maneuvering a satellite that is in an orbit around a space body so that a principle sensitive axis of the satellite is oriented to an orbit frame plane to reduce gravity gradient torques acting upon the satellite. The orbit frame plane is based on an orbit frame vector.

First claim

What is claimed is:

1. A method comprising:
calculating, via instructions executed by a processor, a sensitive axis of a satellite that is in an orbit around a space body; and
controlling, via a guidance system, at least one of a thruster or a reaction wheel to maneuver the satellite by aligning a functional vector of the satellite to an orbit frame plane and slewing the satellite about the functional vector so that the sensitive axis is oriented to the orbit frame plane to reduce gravity gradient torques acting upon the satellite.

2. The method as defined in claim 1 , wherein maneuvering the satellite includes rotating the satellite about a thrust vector of the satellite.

3. The method as defined in claim 1 , further including orienting a thrust vector of the satellite to be perpendicular to the sensitive axis.

4. The method as defined in claim 1 , wherein calculating the sensitive axis is based on at least one of fuel burned or a deployed condition of the satellite.

5. The method as defined in claim 4 , wherein the deployed condition includes a degree to which solar panels of the satellite are un-folded from the satellite.

6. The method as defined in claim 4 , further including detecting, via a sensor, at least one of the fuel burned or the deployed condition.

7. The method as defined in claim 1 , wherein maneuvering the satellite further includes accessing a database for inertia data of the satellite, and wherein the sensitive axis is calculated based on the inertia data.

8. The method as defined in claim 1 , wherein the functional vector includes a thrust vector.

9. An apparatus comprising:
a maneuvering device of a satellite, wherein the maneuvering device includes at least one of a reaction wheel or a thruster; and
an orientation controller to:
calculate a sensitive axis of the satellite, and
cause the maneuvering device to orient a functional vector to be aligned with an orbit frame plane and slew the satellite about the functional vector to orient the sensitive axis of the satellite to the orbit frame plane to reduce gravity gradient torques acting upon the satellite.

10. The apparatus as defined in claim 9 , wherein the orientation controller causes the maneuvering device to orient the functional vector of the satellite with the orbit frame plane.

11. The apparatus as defined in claim 10 , wherein the functional vector includes a thrust vector.

12. The apparatus as defined in claim 9 , wherein the orientation controller calculates the sensitive axis is based on at least one of fuel burned or a deployed condition of solar panels of the satellite.

13. The apparatus as defined in claim 12 , further including a sensor to determine the at least one of the fuel burned or the deployed condition.

14. The apparatus as defined in claim 9 , wherein the orientation controller causes the thruster to orient a thrust vector of the satellite to be perpendicular to the sensitive axis.

15. A non-transitory machine readable medium having instructions stored thereon, which when executed, cause a processor to:
calculate a sensitive axis of a satellite orbiting a space body based on sensor readings of the satellite, the satellite having an associated functional vector;
determine an orbit frame plane using an orbit frame transformation matrix, wherein the orbit frame plane is perpendicular to an orbit frame vector;
determine an attitude of the satellite to orient the sensitive axis to the determined orbit frame plane, and to orient the functional vector to be aligned with the orbit frame plane; and
instruct a guidance system to direct at least one of a reaction wheel or thruster to move the satellite to the attitude.

16. The machine readable medium having instructions stored thereon as defined in claim 15 , further cause the processor to maintain an orbital range of the satellite.

17. The machine readable medium having instructions stored thereon as defined in claim 15 , wherein the functional vector includes a thrust vector.

18. The machine readable medium having instructions stored thereon as defined in claim 15 , wherein the sensitive axis is calculated based on at least one of fuel burned or a deployed condition of the satellite.

19. The machine readable medium having instructions stored thereon as defined in claim 18 , wherein the deployed condition includes a degree to which solar panels are un-folded from the satellite.

20. The machine readable medium having instructions stored thereon as defined in claim 15 , wherein the sensitive axis is calculated based on inertia data of the satellite from a database.

Assignees

• Boeing Co

Inventors

• Lui Timothy S
• Lee Kangsik

Classifications

• B64G1/283 Primary

  using reaction wheels · CPC title

• B64G1/34 Primary

  using gravity gradient · CPC title

• B64G1/285

  using momentum wheels · CPC title

• B64G1/244

  Spacecraft control systems · CPC title

• B64G1/66

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