Energy efficient satellite maneuvering

Patent metadata

Field	Value
Publication number	US-10005568-B2
Application number	US-201514940811-A
Country	US
Kind code	B2
Filing date	Nov 13, 2015
Priority date	Nov 13, 2015
Publication date	Jun 26, 2018
Grant date	Jun 26, 2018

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:
maneuvering, via a thruster, a satellite that is in an orbit around a space body by aligning a functional vector to an orbit frame plane and slewing about the functional vector so that a principle sensitive axis of the satellite 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 , wherein a thrust vector of the satellite is oriented to be perpendicular to the principle sensitive axis.

4. The method as defined in claim 1 , further including determining the principle sensitive axis.

5. The method as defined in claim 1 , wherein orienting the satellite occurs during a portion of the orbit.

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

7. An apparatus comprising:
a maneuvering device of a satellite, wherein the maneuvering device includes a thruster; and
an orientation controller to 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 principle sensitive axis of the satellite to the orbit frame plane to reduce gravity gradient torques acting upon the satellite.

8. The apparatus as defined in claim 7 , wherein the orientation controller is to cause the maneuvering device to orient the functional vector of the satellite with the orbit frame plane.

9. The apparatus as defined in claim 8 , wherein the functional vector includes a thrust vector.

10. The apparatus as defined in claim 7 , wherein the orientation controller is to cause the thruster to orient a thrust vector of the satellite to be perpendicular to the principle sensitive axis.

11. The apparatus as defined in claim 7 , wherein the maneuvering device further includes a momentum storage device.

12. A method comprising:
maneuvering, via at least one thruster of a satellite, the satellite that is in an orbit around a space body to orient a principle sensitive axis of the satellite to an orbit frame plane by slewing the satellite about a functional vector of the satellite that is perpendicular to the principle sensitive axis; and
operating the at least one thruster of the satellite to cause a thrust vector to be perpendicular to the principle sensitive axis to alter an orbital distance of the satellite.

13. The method as defined in claim 12 , further including determining the principle sensitive axis.

14. The method as defined in claim 12 , wherein orienting the principle sensitive principle axis includes slewing the satellite about the thrust vector.

15. The method as defined in claim 12 , wherein operating the at least one thruster includes coordinating activation of thrusters of the satellite based on the thrust vector.

16. The method as defined in claim 12 , wherein maneuvering the satellite further includes operating a momentum storage device.

17. The method as defined in claim 12 , wherein the principle axis is oriented to the orbit frame vector or the orbit frame plane within 5 degrees.

18. The method as defined in claim 12 , wherein the thrust vector is perpendicular to the sensitive principle axis within 5 degrees.

19. A method comprising:
maneuvering, via a thruster, a satellite orbiting a space body so that a functional vector of the satellite is within an orbit frame plane perpendicular to an orbital frame vector, the orbital frame vector directed from the satellite towards a center of the space body; and
slewing the satellite about the functional vector so that a sensitive axis of the satellite is oriented to the orbit frame plane.

20. The method as defined in claim 19 , wherein the functional vector includes a thrust vector.

21. The method as defined in claim 20 , wherein the thrust vector is a resultant vector from multiple thrusters of the satellite.

22. The method as defined in claim 19 , wherein the functional vector includes at least one of an attitude sensor boresight, an axis of rotation for solar wings, antenna boresights, an actuator vector, or a payload specific vector.

23. The method as defined in claim 19 , further including calculating a thrust pattern of the satellite based on at least one of an orientation or a position of the satellite.

24. The method as defined in claim 19 , further including maintaining the satellite at a defined orbital range.

25. A tangible machine readable medium having instructions stored thereon, which when executed, cause a machine to:
access or determine inertial characteristics of a satellite orbiting a space body to identify a sensitive axis 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 determine orbit frame plane, and to orient the functional vector to be aligned with the orbit frame plane; and
instruct a thrust controller to utilize one or more thrusters to move the satellite to the attitude.

26. The machine readable medium having instructions stored thereon as defined in claim 25 , wherein the thrust controller maintains an orbital range of the satellite.

27. The machine readable medium having instructions stored thereon as defined in claim 25 , wherein the functional vector includes a thrust vector.

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

• B64G1/36

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

• B64G1/244

  Spacecraft control systems · CPC title

• B64G1/285

  using momentum wheels · CPC title