Methods and apparatus to minimize command dynamics of a satellite

Patent metadata

Field	Value
Publication number	US-10175700-B2
Application number	US-201715466228-A
Country	US
Kind code	B2
Filing date	Mar 22, 2017
Priority date	Mar 22, 2017
Publication date	Jan 8, 2019
Grant date	Jan 8, 2019

Abstract

Methods, apparatus, and articles of manufacture to minimize command dynamics of a satellite are disclosed. An example apparatus includes a steering law module to calculate a first set of vectors to maneuver a space vehicle, and calculate a second set of vectors based on projecting the first set of vectors onto a fixed plane. The apparatus further includes an attitude controller to generate an attitude command based on the first and the second sets of vectors to prevent an unplanned rotation by the space vehicle.

First claim

What is claimed is:

1. An apparatus comprising:
a steering law module to:
calculate a first set of vectors to maneuver a space vehicle; and
calculate a second set of vectors based on projecting the first set of vectors onto a fixed plane; and

an attitude controller to generate an attitude command based on the first and the second sets of vectors to control an actuator of the space vehicle to maneuver the space vehicle to affect at least one of an orbital path or an orbital height of the space vehicle.

2. The apparatus of claim 1 , wherein the first set of vectors includes a first vector pointing from the space vehicle to a target in an inertial reference frame, and a second vector pointing from the space vehicle to a power source.

3. The apparatus of claim 2 , wherein the inertial reference frame is an Earth-centered inertial coordinate frame and the power source is a light source from a celestial body.

4. The apparatus of claim 2 , wherein the second set of vectors includes a third vector normal to the first and the second vectors, and a fourth vector normal to the first vector.

5. The apparatus of claim 4 , wherein the steering law module is to calculate an angle between the third and the fourth vectors.

6. The apparatus of claim 5 , wherein the attitude command is based on the steering law module calculating a weight factor to determine a contribution from each of the first and the second sets of vectors to the attitude command, the weight factor based on the angle.

7. The apparatus of claim 1 , wherein the attitude controller is to generate the attitude command to prevent an unplanned rotation by the space vehicle.

8. A method comprising:
calculating a first set of vectors to maneuver a space vehicle;
calculating a second set of vectors based on projecting the first set of vectors onto a fixed plane; and
generating an attitude command based on the first and the second sets of vectors to control an actuator of the space vehicle to maneuver the space vehicle to affect at least one of an orbital path or an orbital height of the space vehicle.

9. The method of claim 8 , wherein the first set of vectors includes a first vector pointing from the space vehicle to a target in an inertial reference frame, and a second vector pointing from the space vehicle to a power source.

10. The method of claim 9 , wherein the inertial reference frame is an Earth-centered inertial coordinate frame and the power source is a light source from a celestial body.

11. The method of claim 9 , wherein the second set of vectors includes a third vector normal to the first and the second vectors, and a fourth vector normal to the first vector.

12. The method of claim 11 , further including calculating an angle between the third and the fourth vectors.

13. The method of claim 12 , wherein generating the attitude command includes calculating a weight factor to determine a contribution from each of the first and the second sets of vectors to the attitude command, the weight factor based on the angle.

14. The method of claim 13 , wherein calculating of the weight factor includes using at least one of a linear method, a sinusoidal method, or an exponential method.

15. The method of claim 8 , wherein the attitude command prevents an unplanned rotation by the space vehicle.

16. A tangible computer-readable storage medium comprising instructions that, when executed, cause a machine to at least:
calculate a first set of vectors to maneuver a space vehicle;
calculate a second set of vectors based on projecting the first set of vectors onto a fixed plane; and
generate an attitude command based on the first and the second sets of vectors to control an actuator of the space vehicle to maneuver the space vehicle to affect at least one of an orbital path or an orbital height of the space vehicle.

17. The tangible computer-readable storage medium of claim 16 , wherein the first set of vectors includes a first vector pointing from the space vehicle to a target in an inertial reference frame, and a second vector pointing from the space vehicle to a power source.

18. The tangible computer-readable storage medium of claim 17 , wherein the inertial reference frame is an Earth-centered inertial coordinate frame and the power source is a light source from a celestial body.

19. The tangible computer-readable storage medium of claim 17 , wherein the second set of vectors includes a third vector normal to the first and the second vectors, and a fourth vector normal to the first vector.

20. The tangible computer-readable storage medium of claim 19 , further including instructions that when executed, cause the machine to calculate an angle between the third and the fourth vectors.

21. The tangible computer-readable storage medium of claim 20 , wherein generating the attitude command includes calculating a weight factor to determine a contribution from each of the first and the second sets of vectors to the attitude command, the weight factor based on the angle.

22. The tangible computer-readable storage medium of claim 21 , wherein calculating of the weight factor includes using at least one of a linear method, a sinusoidal method, or an exponential method.

23. The tangible computer-readable storage medium of claim 16 , wherein the attitude command prevents an unplanned rotation by the space vehicle.

Assignees

• Boeing Co

Inventors

• Lui Timothy S
• Lemke Gary E

Classifications

• B64G1/361

  using star sensors · CPC title

• B64G1/283

  using reaction wheels · CPC title

• B64G1/286

  using control momentum gyroscopes (CMGs) · CPC title

• B64G1/244 Primary

  Spacecraft control systems · CPC title

• G01C21/24 Primary

  specially adapted for cosmonautical navigation · CPC title