Single axis correction for orbit inclination

• US 5,738,309 A
• Filed: 02/28/1996
• Issued: 04/14/1998
• Est. Priority Date: 02/28/1996
• Status: Expired due to Fees

• Current Assignee: Hughes Electronics Corporation (Rtx Corporation)
• Original Assignee: Hughes Electronics Corporation (Rtx Corporation)
• Inventors: Fowell, Richard A.
• Primary Examiner(s): MARQUIS, LISSI MOJICA
• Application Number:
  US08/608,238
• Time in Patent Office: 776 Days
• Field of Search: 244/164, 244/165, 244/171, 342/354, 342/355, 342/357, 342/358, 364/459
• US Class Current: 244/171
• CPC Class Codes: B64G 1/244 Spacecraft control systems
• CPC Class Codes: B64G 1/283 using reaction wheels
• CPC Class Codes: B64G 1/285 using momentum wheels
• CPC Class Codes: B64G 1/36 using sensors, e.g. sun-sensors, horizon sensors

Abstract

A method and system of orienting a payload of an orbiting spacecraft (14) to maintain a desired pointing profile in the presence of orbit inclination. A cone (12) is determined which is traced in inertial space by a pitch axis of the payload to maintain the desired pointing profile throughout an orbit. A bias momentum vector of the spacecraft (14) is oriented at an attitude which lies along the cone (12). The attitude has a nonzero angle with respect to a plane spanned by an orbit normal vector and an equatorial normal vector. The payload is rotated about a single body-fixed axis perpendicular to the pitch axis to align the pitch axis along the cone (12). As a result, the desired pointing profile is maintained throughout the inclined orbit.

Claims

1. A method of orienting a payload of an orbiting spacecraft including a bias momentum storage means to maintain a desired pointing profile other than at Earth center in a presence of orbit inclination, the method comprising the steps of:

determining a cone which is traced in inertial space by a pitch axis of the payload in order to maintain the desired pointing profile throughout an orbit;

orienting a bias momentum vector of the spacecraft at an attitude which lies in the cone and outside of a plane spanned by an orbit normal vector and an equatorial normal vector; and

varying an angle between the payload pitch axis and the bias momentum vector about a single body-fixed axis skewed in a roll-yaw plane by an angle variation means to maintain the payload pitch axis in the desired pointing profile;

wherein the attitude of the bias momentum vector and the single body-fixed axis are chosen to be consistent with maintaining the desired pointing profile.

2. The method of claim 1 wherein the bias momentum storage means includes a momentum wheel, and wherein the angle variation means includes a single axis gimbal.

3. The method of claim 1 wherein the angle variation means includes a single degree of freedom gimbal between the payload and a section of the spacecraft containing the bias momentum storage means.

4. The method of claim 1 wherein the angle variation means includes a first wheel and a second wheel whose axes are distinct and perpendicular to the single body fixed axis.

5. The method of claim 4 wherein each of the first wheel and the second wheel is selected from the group consisting of a momentum wheel and a reaction wheel.

6. The method of claim 1 wherein the bias momentum storage means includes a rotating, external section of the spacecraft.

7. The method of claim 1 wherein the bias momentum storage means includes a wheel selected from the group consisting of a momentum wheel and a reaction wheel.

8. The method of claim 1 further comprising the step of controlling the angle variation using a sensor selected from the group consisting of an infrared earth sensor, a radio-frequency beacon sensor, a ground-located radio-frequency beacon sensor, an optical beacon sensor, a magnetometer, a sun sensor, a star sensor, and a gyroscope.

9. The method of claim 1 wherein the payload is maintained to point fixed on a surface of the Earth.

14. The system of claim 3 wherein each of the first wheel and the second wheel is selected from the group consisting of a momentum wheel and a reaction wheel.

10. A system for orienting a payload of an orbiting spacecraft including a bias momentum storage means to maintain a desired pointing profile other than at Earth center in a presence of orbit inclination, the system comprising:

a set of orbit and attitude sensors to determine an orbit and an attitude of the spacecraft;

a processor which determines a cone which is traced in inertial space by a pitch axis of the payload in order to maintain the desired pointing profile throughout the orbit;

an external torquer responsive to the processor to maintain an orientation of a bias momentum vector of the spacecraft at an attitude which lies along the cone and lies outside a plane spanned by an orbit normal vector and an equatorial normal vector; and

angle variation means responsive to the processor for varying an angle between the pitch axis and the bias momentum vector about a single body-fixed axis skewed in a roll-yaw plane to maintain the pitch axis in the desired pointing profile;

wherein the attitude of the bias momentum vector and the single body-fixed axis are chosen to be consistent with maintaining the desired pointing profile.

11. The system of claim 10 wherein the bias momentum storage means includes a momentum wheel, and wherein the angle variation means includes a single axis gimbal.

12. The system of claim 10 wherein the angle variation means includes a single degree of freedom gimbal between the payload and a section of the spacecraft containing the bias momentum storage means.

13. The system of claim 10 wherein the angle variation means includes a first wheel and a second wheel whose axes are distinct and perpendicular to the single body fixed axis.

15. The system of claim 10 wherein the bias momentum storage means includes a rotating, external section of the spacecraft.

16. The system of claim 10 wherein the bias momentum storage means includes a wheel selected from the group consisting of a momentum wheel and a reaction wheel.

17. The system of claim 10 further comprising the step of controlling the angle variation using a sensor selected from the group consisting of an infrared earth sensor, a radio-frequency beacon sensor, a ground-located radio-frequency beacon sensor, an optical beacon sensor, a magnetometer, a sun sensor, a star sensor, and a gyroscope.

18. The system of claim 10 wherein the payload is maintained to point fixed on a surface of the Earth.