Attitude control system for momentum-biased spacecraft

• US 5,098,041 A
• Filed: 06/07/1990
• Issued: 03/24/1992
• Est. Priority Date: 06/07/1990
• Status: Expired due to Term

• Current Assignee: Hughes Electronics Corporation (AT&T, Inc.)
• Original Assignee: Hughes Aircraft Company (Rtx Corporation)
• Inventors: Uetrecht, David S.
• Primary Examiner(s): Peters, Jr., Joseph F.
• Assistant Examiner(s): MARQUIS, LISSI MOJICA
• Application Number:
  US07/534,216
• Time in Patent Office: 656 Days
• Field of Search: 244/164, 244/165, 244/169, 244/170, 244/171, 244/172, 364/459
• US Class Current: 244/164
• CPC Class Codes: B64G 1/244 Spacecraft control systems
• CPC Class Codes: B64G 1/36 using sensors, e.g. sun-sensors, horizon sensors
• CPC Class Codes: B64G 1/38 damping of oscillations, e.g. nutation dampers

Abstract

An attitude and nutation control system (30) for a momentum-biased vehicle (10) having roll, pitch, and yaw axes which employs a normal mode estimator (32) which predicts steady-state values for roll attitude, roll rate, and yaw rate. The normal mode estimator (32) receives instantaneous roll attitude information from an earth sensor (34) and optionally receives roll and/or yaw rate information from roll gyro (35a) and yaw gyro (35b). A logic circuit (36) coupled to the normal mode estimator (32) generates correction signals when the steady-state values for roll attitude, roll rate, and yaw rate are outside predetermined limits. A plurality of thrusters (14a-d) produce torque for bringing the steady-state values for roll attitude, roll rate, and yaw rate within predetermined limits. A sample/hold-off control circuit (68) samples correction signals between thruster activations while a optimal thruster selection logic (70) employs a linear program to compute torques associated with changes in the correction signals for use by the normal mode estimator (32), as well as activating selected thrusters (14 a-d).

Claims

1. An attitude and nutation control system for a momentum-biased vehicle having roll, pitch, and yaw axes comprising:

(a) sensor means for measuring instantaneous roll attitude;

(b) estimator means coupled to said sensor means for predicting steady-state values for roll attitude, roll rate, and yaw rate;

(c) logic means coupled to said estimator means for generating correction signals when the steady-state values for roll attitude, roll rate, and yaw rate are outside predetermined limits;

(d) a plurality of thrusters for producing torque for bringing the steady-state values for roll attitude, roll rate, and yaw rate within predetermined limits; and

(e) firing means coupled between said logic means and said thrusters for activating said thrusters in response to the correction signals, said firing means also serving to determine torques associated with changes in the correction signals for use by said estimator means.

2. The system as recited in claim 1 wherein said sensor means comprises inertial means for sensing changes in instantaneous roll and yaw attitudes.

3. The system as recited in claim 2 wherein said inertial means comprises:

(a) a roll gyro coupled to said estimator means for producing instantaneous roll rate information; and

(b) a yaw gyro, coupled to said estimator means, for producing instantaneous yaw rate information.

4. The system as recited in claim 1 wherein said sensor means comprises a reference means for measuring instantaneous roll attitude of the vehicle with respect to a celestial body, said vehicle being in orbit around the celestial body.

5. The system as recited in claim 1 wherein said firing means comprises:

(a) a sampling circuit for sampling correction signals between thruster activations;

(b) optimal thruster selection means coupled to said sampling circuit for selectively choosing thrusters for activation, for determining the duration of thruster activation, and for determining torques associated with changes in the correction signals; and

(c) actuators coupled to said optimal thruster selection means for activating said thrusters.

6. The system as recited in claim 1 wherein said estimator means includes a microprocessor programmed with a set of state equations employing negative feedback of steady-state roll attitude values.

7. The system as recited in claim 1 wherein said logic means comprises:

(a) a microprocessor for implementing software logic functions, a first software logic function receiving the steady-state roll attitude and steady-state yaw rate outputs of said estimator means and determining a roll component of the vehicle'"'"'s angular momentum vector, a second set of software logic functions generating correction signals, and a third set of software logic functions determining the proper phase of correction signals and whether the roll component, the steady-state roll rate, and steady-state yaw rate exceed predetermined limits;

(b) comparison means coupled to said microprocessor for generating error signals when the roll component, the steady-state roll rate and yaw rate differ from commanded values, said error signals causing said second set of software logic functions to generate correction signals; and

(c) control circuit means coupled to said microprocessor for controlling transmission of the correction signals to the firing means.

8. The system as recited in claim 7 further comprising gain control means for amplifying correction signals associated with said roll component when the roll component error signals which are outside predetermined limits.

9. An attitude and nutation control system for a momentum-biased vehicle having roll, pitch, and yaw axes comprising:

(a) sensor means for measuring instantaneous roll attitude, roll rate, and yaw rate;

(b) estimator means coupled to said sensor means for predicting steady-state values for roll attitude, roll rate, and yaw rate, said estimator means including a microprocessor programmed with a set of state equations employing negative feedback of steady-state roll attitude, roll rate, and yaw rate values;

(c) logic means coupled to said estimator means for generating correction signals when the steady-state values for roll attitude, roll rate, and yaw rate are outside predetermined limits, said logic means including a microprocessor for implementing software logic functions, a first software logic function receiving the steady-state roll attitude and steady-state yaw rate outputs of said estimator means and determining a roll component of the vehicle'"'"'s angular momentum vector, a second set of software logic functions generating correction signals, and a third set of software logic functions determining the proper phase of correction signals and whether the roll component, steady-state roll rate, and steady-state yaw rate exceed predetermined limits, said logic means also including control circuit means for controlling transmission of the correction signals to the firing means, and comparison means coupled to said microprocessor for generating error signals when the roll component, the steady-state roll rate, and the steady-state yaw rate differ from commanded values, said error signals causing said second set of software logic functions to generate correction signals;

(d) a plurality of thrusters for producing torque for bringing the steady-state values for roll attitude, roll rate, and yaw rate within predetermined limits; and

(e) firing means coupled between said logic means and said thrusters for activating said thrusters, said firing means including a sampling circuit for sampling correction signals between thruster activations, optimal thruster selection means coupled to said sampling circuit for selectively choosing thrusters for activation, for determining the duration of thruster activation, and for determining torques associated with changes in the correction signals, said firing means also including actuators coupled to said optimal thruster selection means for activating said thrusters.

10. The system as recited in claim 9 wherein said sensor means comprises inertial means for sensing changes in instantaneous roll attitude and yaw attitude, said inertial means including a roll gyro coupled to said estimator means for producing instantaneous roll rate information, and a yaw gyro coupled to said estimator means for producing instantaneous yaw rate information.

11. The system as recited in claim 9 wherein said sensor means comprises a reference means for measuring roll attitude of the vehicle with respect to a celestial body, said vehicle being in orbit about said celestial body.

12. A method for controlling a momentum-biased vehicle having roll, pitch, and yaw axes comprising:

(a) measuring instantaneous roll attitude of the vehicle;

(b) predicting steady-state values for roll attitude, roll rate, and yaw rate;

(c) generating correction signals when the steady-state values for roll attitude, roll rate, and yaw rate are outside predetermined limits;

(d) producing torque for bringing the steady-state values for roll attitude, roll rate, and yaw rate within predetermined limits; and

(e) determining torques associated with changes in the correction signals for use in predicting steady-state values for roll attitude, roll rate, and yaw rate.

13. The method as recited in claim 12 further comprising:

(f) measuring instantaneous roll and yaw rates of the vehicle.

14. The method of claim 13 wherein said step of measuring the instantaneous roll attitude comprises:

(a) determining the center of a celestial body, said vehicle being in orbit about said celestial body;

(b) determining a line from the center of said celestial body to the origin of the vehicle axes; and

(c) measuring the angle between said line and the roll axes.

15. The method of claim 12 wherein said step of producing torque comprises activating a plurality of thrusters.