Spacecraft yaw pointing for inclined orbits

• US 6,154,692 A
• Filed: 09/17/1998
• Issued: 11/28/2000
• Est. Priority Date: 10/01/1997
• Status: Expired due to Term

• Current Assignee: Space Systems/Loral Incorporated (Loral Space and Communications Incorporated)
• Original Assignee: Space Systems/Loral Incorporated (Loral Space and Communications Incorporated)
• Inventors: Machlis, Matthew, Furumoto, Nobi, Cielaszyk, David
• Primary Examiner(s): Zanelli, Michael J.
• Assistant Examiner(s): Gibson, Eric M.
• Application Number:
  US09/154,899
• Time in Patent Office: 803 Days
• Field of Search: 701/13, 701/3, 701/4, 244/158 R, 244/164, 244/165, 244/171
• US Class Current: 701/13
• CPC Class Codes: B64G 1/244 Spacecraft control systems
• CPC Class Codes: B64G 1/26 using jets
• CPC Class Codes: B64G 1/285 using momentum wheels
• CPC Class Codes: B64G 1/36 using sensors, e.g. sun-sensors, horizon sensors
• CPC Class Codes: B64G 1/365 using horizon or Earth sensors

Abstract

A method for use in a spacecraft for controlling yaw angle deviations from a desired yaw angle profile. The method includes the steps of: (a) operating a profile generator to output roll angle, pitch angle, yaw momentum, and yaw angle profiles, the profiles being calculated to meet spacecraft pointing requirements while operating in an inclined orbit; (b) inputting to an observer raw roll-axis sensor measurements, commanded and measured yaw-axis wheel momentum storage, measured pitch-axis wheel momentum storage, and external roll-axis and yaw-axis torques, the observer generating a yaw angle estimate and a yaw momentum estimate; (c) subtracting the yaw angle profile from the yaw angle estimate to obtain a difference value; and (d) using the difference value and the yaw momentum estimate to control roll-axis thruster firings to limit spacecraft yaw angle deviations from the yaw angle profile.

Claims

1. A method for use in a spacecraft for controlling yaw angle deviations from a desired yaw angle profile, comprising steps of:

operating a profile generator to output desired roll angle, pitch angle, yaw momentum, and yaw angle profiles, the desired profiles being calculated to meet spacecraft pointing requirements while operating in an inclined orbit;

inputting to an observer raw roll-axis sensor measurements, commanded and measured yaw-axis wheel momentum storage, measured pitch-axis wheel momentum storage, and external roll-axis and yaw-axis torques, the observer generating a yaw angle estimate and a yaw momentum estimate;

subtracting the yaw angle profile from the yaw angle estimate to obtain a difference value; and

using the difference value and the yaw momentum estimate to control roll-axis thruster firings to limit spacecraft yaw angle deviations from the yaw angle profile.

2. A method as in claim 1, wherein the yaw angle profile and the yaw angle estimate are both referenced to the orbit plane of the spacecraft.

3. A method as in claim 1, wherein the external roll-axis and yaw-axis torques are obtained from solar torque and thruster firing disturbance models.

4. A method as in claim 1, wherein the desired yaw angle profile is derived from kinematics of pointing the spacecraft at the Earth, while maintaining the spacecraft momentum bias perpendicular to the Earth'"'"'s equatorial plane in the inclined orbit.

5. A spacecraft comprising a control system for controlling yaw angle deviations from a desired yaw angle profile, comprising:

a profile generator that outputs roll angle, pitch angle, yaw momentum, and yaw angle profiles, the profiles being calculated to meet spacecraft pointing requirements while operating in an inclined orbit;

an observer for inputting raw roll-axis sensor measurements, commanded and measured yaw-axis wheel momentum storage, measured pitch-axis wheel momentum storage, and external roll-axis and yaw-axis torques, the observer generating a yaw angle estimate and a yaw momentum estimate;

a node for subtracting the yaw angle profile from the yaw angle estimate to obtain a difference value; and

a controller responsive to the difference value and the yaw momentum estimate for controlling roll-axis thruster firings to limit spacecraft yaw angle deviations from the yaw angle profile.

6. A spacecraft as in claim 5, wherein the yaw angle profile and the yaw angle estimate are both referenced to the orbit plane of the spacecraft.

7. A spacecraft as in claim 5, wherein the external roll-axis and yaw-axis torques are obtained from solar torque and thruster firing disturbance models.

8. A spacecraft as in claim 5, wherein said profile generator derives the desired yaw angle profile from kinematics of pointing the spacecraft at the Earth, while maintaining the spacecraft momentum bias perpendicular to the Earth'"'"'s equatorial plane in the inclined orbit.