Simplified yaw steering method for satellite antenna beam control

• US 6,283,415 B1
• Filed: 04/29/1999
• Issued: 09/04/2001
• Est. Priority Date: 04/29/1999
• Status: Expired due to Fees

• Current Assignee: Hughes Electronics Corporation (AT&T, Inc.)
• Original Assignee: Hughes Electronics Corporation (AT&T, Inc.)
• Inventors: Rosen, Harold A.
• Primary Examiner(s): Barefoot, Galen L.
• Application Number:
  US09/301,965
• Time in Patent Office: 859 Days
• Field of Search: 244/158.R, 244/164, 244/165, 244/166, 244/168, 244/169, 342/352-359, 701/13
• US Class Current: 244/164
• CPC Class Codes: B64G 1/1007 Communications satellites
• CPC Class Codes: B64G 1/244 Spacecraft control systems
• CPC Class Codes: B64G 1/26 using jets
• CPC Class Codes: B64G 1/283 using reaction wheels
• CPC Class Codes: B64G 1/36 using sensors, e.g. sun-sensors, horizon sensors
• CPC Class Codes: B64G 1/363 using sun sensors
• CPC Class Codes: B64G 1/365 using horizon or Earth sensors
• CPC Class Codes: B64G 1/66 Arrangements or adaptations of apparatus or instruments, not otherwise provided for

Abstract

For an antenna on a satellite in an inclined orbit about the Earth, cross-track motion resulting from the rotation of the Earth can be reduced in antenna coordinates by yawing the antenna (preferably by yawing the entire satellite, for example, by using a reaction wheel system) by an appropriate angle, which varies throughout the orbit.

Claims

1. A method of steering a satellite antenna mounted to a satellite having a pitch axis, a roll axis, and a yaw axis, the satellite traveling in an orbit around a rotating object, the orbit having an inclination and an ascending node, the method comprising the steps of:

determining the inclination of the orbit;

determining the time in the orbit from the ascending node;

determining the period of the orbit;

determining the period of the rotation of the object; and

steering the antenna about the yaw axis by an angle, φ

, wherein φ

is a function of the inclination of the orbit, the time in the orbit from the ascending node, the period of the orbit, and the period of the rotation of the object.

2. The method of claim 1, wherein the steering step includes a step of steering the satellite about the yaw axis by the angle φ

.

3. The method of claim 1, wherein the steering step includes a step of calculating the angle φ

using the formula;

φ

=arctan [[sin(i)cos(2π

t/P)]/[(D/P)-cos(i)]], where i is the inclination of the orbit, t is the time in the orbit from the ascending node, P is the period of the orbit, and D is the period of the rotation of the object.

4. The method of claim 3, wherein the steering step includes a step of steering the satellite about the yaw axis by the angle φ

.

5. A method for steering a satellite antenna mounted to a satellite having a pitch axis, a roll axis, and a yaw axis, the satellite traveling in an orbit around the Earth, the orbit having an inclination and an ascending node, the method comprising the steps of:

determining the inclination of the orbit;

determining the time in the orbit from the ascending node;

determining the period of the orbit; and

steering the antenna about the yaw axis by an angle, φ

, wherein φ

is a function of the inclination of the orbit, the time in the orbit from the ascending node, the period of the orbit, and the period of the rotation of the Earth.

6. The method of claim 5, wherein the steering step includes a step of steering the satellite about the yaw axis by the angle φ

.

7. The method of claim 5, wherein the steering step includes a step of calculating the angle φ

using the formula;

φ

=arctan [[sin(i)cos(2π

t/P)]/[(D/P)-cos(i)]], where i is the inclination of the orbit, t is the time in the orbit from the ascending node, P is the period of the orbit, and D is the period of rotation of the Earth.

8. The method of claim 7, wherein the steering step includes a step of steering the satellite about the yaw by the angle φ

.

9. A method for reducing pointing errors while steering a satellite antenna mounted to a satellite having a pitch axis, a roll axis, and a yaw axis, the satellite traveling in an orbit around a rotating object, the orbit having an inclination and an ascending node and the antenna pointed generally at a target area on the object, the method comprising the steps of:

determining the inclination of the orbit;

determining the time in the orbit from the ascending node;

determining the period of the orbit;

determining the period of the rotation of the object; and

steering the antenna about the yaw axis by an angle, φ

, wherein φ

is a function of the inclination of the orbit, the time in the orbit from the ascending node, the period of the orbit, and the period of the rotation of the object.

10. The method of claim 9, wherein the steering step includes a step of steering the satellite about the yaw axis by the angle φ

.

11. A satellite having a pitch axis, a roll axis, and a yaw axis, the satellite traveling in an orbit around a rotating object, the orbit having an inclination and an ascending node and the antenna pointed generally at a target area on the object, the satellite comprising:

a satellite antenna mounted to the satellite; and

means for reducing pointing errors while steering the satellite antenna by steering the antenna about the yaw axis by an angle, φ

, wherein φ

is a function of the inclination of the orbit, the time in the orbit from the ascending node, the period of the orbit, and the period of the rotation of the object.

12. The satellite of claim 11, wherein the means for reducing pointing errors includes means for calculating the angle φ

using the formula;

φ

=arctan [[sin(i)cos(2π

t/P)]/[(D/P)-cos(i)]], where i is the inclination of the orbit, t is the time in the orbit from the ascending node, P is the period of the orbit, and D is the period of rotation of the object.

13. The satellite of claim 11, wherein the means for reducing pointing errors includes means for steering the satellite about the yaw axis by the angle φ

.