Systematic vectored thrust calibration method for satellite momentum control

• US 5,765,780 A
• Filed: 12/22/1995
• Issued: 06/16/1998
• Est. Priority Date: 12/22/1995
• Status: Expired due to Term

• Current Assignee: Hughes Electronics Corporation (AT&T, Inc.)
• Original Assignee: Hughes Electronics Corporation (AT&T, Inc.)
• Inventors: Barskey, Michael F., Yocum, John F. Jr.
• Primary Examiner(s): Kashnikow, Andres
• Assistant Examiner(s): DINH, TIEN QUANG
• Application Number:
  US08/577,595
• Time in Patent Office: 907 Days
• Field of Search: 244/165, 244/164, 244/169, 244/168, 364/463, 364/567
• US Class Current: 244/165
• CPC Class Codes: B64G 1/244 Spacecraft control systems
• CPC Class Codes: B64G 1/26 using jets
• CPC Class Codes: B64G 1/262 having adjustable angles, e.g. gimbaled thrusters
• CPC Class Codes: B64G 1/28 using inertia or gyro effect
• CPC Class Codes: B64G 1/36 using sensors, e.g. sun-sensors, horizon sensors

Abstract

A method of simultaneously performing a translational maneuver of a spacecraft by a thruster and dumping momentum from the spacecraft during a time period P. The method entails aligning the thruster along a thrust vector which is fixed during the time period P, wherein the thrust vector is aligned with the center of mass of the spacecraft at a time P/2, and firing the thruster throughout the time period P.

Claims

1. A momentum control system for a spacecraft having a propulsion system in which a disturbance is exerted on the spacecraft, said system comprising:

a control processor for receiving an attitude signal representative of the attitude motion of said spacecraft and processing said attitude signal to generate a state variable signal representative of one or more state variables of said spacecraft;

a system identification processor which receives said state variable signal and isolates a signal which has the characteristics of said disturbance exerted on said spacecraft, said system identification processor generating a pseudo input signal for said isolated disturbance which within a multiplicative constant has substantially the same shape, when plotted as a function of time, as the actual disturbance would have if it had been measured,

said system identification processor processing said pseudo input signal to generate a thruster torque signal representative of a thruster torque generated by said propulsion system;

a propulsion processor for receiving said thruster torque signal and generating a control command signal representative of a maneuver to be performed by said propulsion system, said propulsion processor comprising a thruster calibration alignment processor which calculates the mass properties of said spacecraft in response to said thruster torque signals; and

wherein said control command signal is sent to said control processor which aligns said propulsion system in response to said control command signal.

2. The momentum control system of claim 1, wherein said propulsion system comprises:

a gimbaled thruster attached to said spacecraft;

an actuator operationally attached to said gimbaled thruster so as to control the angled position of said gimbaled thruster in two orthogonal directions; and

wherein said control processor sends a control signal to said actuator which moves said gimbaled thruster to an angled position in response to said control signal, wherein said angled position of said gimbaled thruster controls the attitude of said spacecraft.

3. The momentum control system of claim 2, wherein said gimbaled thruster comprises an ion propulsion thruster.

4. The momentum control system of claim 1, further comprising:

a momentum accumulator for storing and dumping momentum accumulated on said spacecraft;

a sensor for generating a momentum state signal corresponding to the momentum being stored on said spacecraft at a given time, wherein said momentum state signal forms said state variable signal at least in part.

5. The momentum control system of claim 1, wherein said calibration alignment processor calculates the motion of the center of mass of said spacecraft at an instant of time.

6. The momentum control system of claim 5, wherein said calibration alignment processor calculates the thrust vector of said propulsion system.

7. A method of dumping momentum of a spacecraft having a propulsion system in which a disturbance is exerted on the spacecraft, said method comprising the steps of:

receiving an attitude signal representative of the attitude motion of said spacecraft;

generating from said attitude signal a state variable signal representative of several state variables of said spacecraft;

isolating from said state variable signal a disturbance signal which has the characteristics of said disturbance exerted on said spacecraft;

generating a pseudo input signal from said isolated disturbance signal which within a multiplicative constant has substantially the same shape, when plotted as a function of time, as the actual disturbance; and

aligning said propulsion system along a thrust vector which is fixed with respect to said spacecraft in response to said pseudo input signal to thereby dump momentum from said spacecraft, such that said thrust vector is momentarily aligned with the center of mass of said spacecraft.

8. The method of claim 7, wherein said moving step comprises moving a gimbaled thruster in response to the value of said pseudo signal.

9. The method of claim 8, wherein the step of generating a pseudo input signal includes the step of:

determining a mass property of said spacecraft.

10. The method of claim 9, wherein said mass property comprises the movement of the center of mass of said spacecraft at an instant of time.

11. A method of simultaneously performing a translational maneuver of a spacecraft by a thruster and dumping momentum from said spacecraft during a time period P, said method comprising the steps of:

aligning said thruster along a thrust vector which is fixed with respect to said spacecraft during said time period P, wherein the thrust vector is momentarily aligned with the center of mass of said spacecraft during said time period P; and

firing said thruster throughout said time period P.

12. The method of claim 11, comprising the steps of:

accumulating momentum on said spacecraft from when the thruster is initially fired to a time P/2, at which time said thrust vector is aligned with the center of mass of said spacecraft; and

dumping momentum accumulated on said spacecraft from P/2 to the end of time period P.

13. The method of claim 12, wherein the amount of accumulated momentum from when the thruster is initially fired to time P/2 is equal to the amount of momentum dumped on said spacecraft from time P/2 to the end of time period P.

14. The method of claim 11, wherein the position of said center of mass of said spacecraft varies with time.