Momentum wheel platform steering system and method

• US 5,261,631 A
• Filed: 06/24/1991
• Issued: 11/16/1993
• Est. Priority Date: 06/24/1991
• Status: Expired due to Term

• Current Assignee: Hughes Electronics Corporation (Rtx Corporation)
• Original Assignee: Hughes Aircraft Company (Rtx Corporation)
• Inventors: Brehove, James D., Bender, Douglas J.
• Primary Examiner(s): BAREFOOT, GALEN L
• Application Number:
  US07/720,103
• Time in Patent Office: 876 Days
• Field of Search: 244/164, 244/165
• US Class Current: 244/165
• CPC Class Codes: B64G 1/285 using momentum wheels

Abstract

Method and apparatus for controlling the two-axis rate and position as well as the linear elevation of a momentum wheel platform supported by three jackscrews driven by stepper motors. By tilting the momentum wheel, a control torque is produced in the plane orthogonal to the nominal wheel spin axis. When all three actuators are operational, the control transformations are made unique by constraining the sum of the actuator extensions to be zero. When one actuator has failed, the above constraint is eliminated and the failed actuator is constrained to its measured value. Momentum wheel platform rotational rate commands generated by the roll/yaw control system are first integrated to give desired gimbal angles, and then transformed into jackscrew extensions. Jackscrew step commands are computed as the difference between these desired extensions and the current positions of the jackscrews. The position of each jackscrew is maintained by accumulating the step commands. The desired extensions are also back-transformed to compute gimbal angles that are fed back to the roll-yaw state control system. In ground commanded stepping, the momentum wheel platform steering method operates exactly as described above, except that relative jackscrew step commands from a ground station are utilized instead of the step commands computed in the rate following configuration.

Claims

1. Apparatus for controlling a spacecraft momentum wheel platform in an on-board computer-controlled rate following mode, said apparatus comprising:

a roll-yaw state estimator and controller for generating desired momentum wheel platform rates;

a rate integrator coupled to said roll-yaw state estimator and controller for integrating said desired momentum wheel platform rates to produce desired momentum wheel platform angles;

a forward transform computer coupled to said rate integrator and responsive to said desired momentum wheel platform angles for computing desired actuator extensions;

a step computer coupled to said forward transform computer and responsive to desired actuator extensions for producing actuator step command signals; and

a momentum wheel platform having linear actuators coupled to said step computer for actuation of said linear actuators to tilt said momentum wheel platform a predetermined amount;

the output of said rate integrator being fed back to said roll-yaw state estimator and controller as a momentum wheel platform angle feedback signal.

2. The apparatus of claim 1 which further comprises:

a step counter and accumulator coupled to the output of said step computer for accumulating said actuator step command signals; and

a backward transform computer coupled between said step counter and accumulator and said roll-yaw state estimator and controller for developing momentum wheel platform angle feedback and applying it to said roll-yaw state estimator and controller.

3. Apparatus for controlling a spacecraft momentum wheel platform in an on-board computer-controlled rate-following mode, said apparatus comprising:

a roll-yaw state estimator and controller for generating desired momentum wheel platform rates;

an on-board computer coupled to said roll-yaw state estimator and controller and responsive to said desired momentum wheel platform rates for computing desired actuator extensions;

an actuator step computer coupled to said on-board computer and responsive to said desired actuator extensions for producing actuator step command signals by computing the difference between the desired actuator position and the existing actuator position, where the existing actuator position is determined by taking the sum of the previous actuator step command signals; and

a momentum wheel platform having linear actuators coupled to said actuator step computer and responsive to said actuator step command signals for actuation of said linear actuators to tilt said momentum wheel platform a predetermined amount, thereby producing said desired momentum wheel platform rate.

4. The apparatus of claim 3 which further comprises:

a spacecraft;

a tiltable platform disposed on said spacecraft;

three pivots for supporting said platform disposed equidistantly therearound;

three linear actuators each comprising a jackscrew driven by a stepper motor, each of said linear actuators being individually coupled to a different one of said pivots and being adapted to raise or lower its respective pivot;

a momentum wheel mounted to said platform and being adapted to spin at high speed about a spin axis to produce a momentum vector, the spin axis of said wheel being initially aligned in a predetermined direction with respect to said spacecraft, said platform and said wheel being adapted to be tilted through small angles to produce a component of the wheel momentum vector in a plane transverse to the spin axis of said wheel;

three linear potentiometers each individually coupled to a different one of said pivots for providing an indication of the extension of the respective ones of said linear actuators;

wherein the actuator step computer produces actuator step command signals by computing the difference between the desired actuator position and the existing actuator position, where the existing actuator position is based on the indication provided by said three linear potentiometers;

said three linear actuators being coupled to said actuator step computer and responsive to said actuator step command signals for actuation of said linear actuators to tilt said tiltable platform and said momentum wheel a predetermined amount, thereby producing said desired momentum wheel platform rate.

5. An attitude control system for a spacecraft comprising:

a spacecraft;

a tiltable platform disposed on said spacecraft;

three pivots for supporting said platform disposed equidistantly therearound;

three linear actuators each comprising a jackscrew driven by a stepper motor, each of said linear actuator being individually coupled to a different one of said pivots and being adapted to raise or lower its respective pivot;

a momentum wheel mounted to said platform and being adapted to spin at high speed about a spin axis to produce a momentum vector, the spin axis of said wheel being initially aligned in a predetermined direction with respect to said spacecraft, said platform and said wheel being adapted to be tilted through small angles to produce a component of the wheel momentum vector in a plane transverse to the spin axis of said wheel;

an on-board computer disposed on said spacecraft for computing desired roll-yaw momentum wheel platform rates for said spacecraft;

a platform steering computer coupled to said on-board computer for converting said roll-yaw momentum wheel platform rates to jackscrew position commands;

a step logic computer coupled to said platform steering computer for converting said jackscrew position commands to jackscrew step commands; and

a plurality of stepper motor control drivers coupled from said step logic computer to said linear actuators for applying said jackscrew step commands to said stepper motors.

6. The apparatus of claim 5 which further comprises:

three linear potentiometers each individually coupled to a different one of said pivots for providing an indication of the extension of the respective ones of said linear actuators;

a telemetry encoder unit coupled to said potentiometers for telemetering said indication to a control location; and

a command decoder unit for receiving commands intended to control the tilt of said momentum wheel;

wherein the on-board computer comprises a roll-yaw state estimator and controller coupled to said command decoder for converting said commands to desired roll-yaw momentum wheel platform rates; and

wherein the platform steering computer is coupled to said roll-yaw state estimator and controller for converting said roll-yaw momentum wheel platform rate commands to jackscrew position commands.

7. The apparatus of claim 5 wherein the on-board computer further comprises:

command means for generating jackscrew commands and applying them to said three linear actuators for tilting said momentum wheel;

accumulating means coupled to said command means for accumulating jackscrew commands;

back-transformation means coupled to said accumulating means for back-transforming accumulated jackscrew commands to compute momentum wheel platform angles; and

feedback means for applying computed momentum wheel platform angles to said platform steering computer.

8. The apparatus of claim 5 which further comprises:

means for providing desired platform rates to said spacecraft on-board computer;

means for integrating said platform rates;

means for transforming said integrated platform rates to required linear actuator extensions via a forward transformation;

means for constraining a failed actuator to its measured actuator extension;

means for applying position commands for operable actuators to a step logic computer that converts them into step commands; and

means for applying the step commands to the stepper motors of the operable linear actuators to produce the desired platform rates.

9. The apparatus of claim 8 which further comprises:

means for transforming said integrated platform rates to required linear actuator extensions via a forward transformation;

means for providing measurements of existing linear actuator extensions to said spacecraft on-board computer; and

means for transforming measured actuator extensions to platform rotations via a backward transformation.

10. The apparatus of claim 5 which further comprises:

means for computing desired jackscrew extensions from desired platform angles;

means for measuring existing jackscrew extensions;

means for generating jackscrew step commands as the difference between desired jackscrew extensions and measured jackscrew extensions;

means for counting jackscrew step commands to update the jackscrew position register; and

means for back-transforming the desired jackscrew extensions to compute platform angles.

11. A method for controlling a spacecraft momentum wheel platform in an on-board computer-controlled rate following mode, said method comprising the following steps:

generating desired momentum wheel platform rate commands in a roll-yaw state estimator and controller;

integrating said desired momentum wheel platform rate commands to produce desired momentum wheel platform angle commands;

forward transforming said desired momentum wheel platform angle commands to produce desired actuator extension commands;

computing actuator step command signals from said desired actuator extension commands;

applying said actuator step command signals to the spacecraft momentum wheel platform to produce tilt thereof.

12. The method of claim 11 which further comprises the step of:

applying the integrated momentum wheel platform rate commands to the roll-yaw state estimator and controller as a momentum wheel platform angle feedback signal.

13. The method of claim 11 which further comprises the steps of:

accumulating said actuator step command signals;

back transforming said actuator step command signals to produce momentum wheel platform angle feedback signals; and

applying said momentum wheel platform angle feedback signals to said roll-yaw state estimator and controller.

14. The method of claim 11 wherein the step of computing actuator step command signals comprises the step of:

computing actuator step command signals as the difference between the desired actuator position and the existing actuator position, where the existing actuator position is determined by taking the sum of the previous actuator step command signals.

15. The method of claim 11 wherein the step of computing actuator step command signals comprises the step of:

computing actuator step command signals as the difference between the desired actuator position and the existing actuator position, where the existing actuator position is determined by taking the output of linear potentiometers connected to the momentum wheel platform.

17. The method of claim 15 that is further adapted to control a momentum wheel platform having a failed actuator, said method further comprising the steps of:

computing actuator step command signals for operable actuators by constraining the failed actuator to its existing extension; and

applying the step command signals to the stepper motors of the operable linear actuators to produce the desired platform rates.

16. A method for controlling platform rates of a momentum wheel platform comprising the following steps:

providing desired platform rates to a spacecraft on-board computer;

integrating said platform rates;

transforming said integrated platform rates to required linear actuator extensions via a forward transformation;

providing measurements of existing linear actuator extensions to said spacecraft on-board computer;

transforming measured actuator extensions to platform rotations via a backward transformation;

constraining the sum of the actuator extensions to be zero;

applying actuator position commands to a step logic computer that converts them into step commands; and

applying the step commands to the stepper motors of the linear actuator to produce the desired platform rates.

18. A method of controlling a momentum wheel platform in an on-board computer controlled rate following mode, said method comprising the following steps:

generating platform rate commands in an on-board computer;

integrating platform rate commands to provide desired platform angles;

computing desired jackscrew extensions from desired platform angles;

measuring existing jackscrew extensions;

generating jackscrew step commands as the difference between desired jackscrew extensions and measured jackscrew extensions; and

applying the jackscrew step commands to the jackscrews to tilt the momentum wheel platform.

19. A method of controlling a momentum wheel platform by ground command, said method comprising the following steps:

transmitting desired jackscrew position commands from a ground control to a spacecraft;

measuring existing jackscrew extensions;

generating a number of jackscrew step commands equal to the desired jackscrew position command from ground; and

applying the jackscrew step commands to the jackscrews to tilt the momentum wheel platform.

20. The method of claim 19 which further comprises initializing a system for controlling the tilt of the momentum wheel platform on board the spacecraft by command from the ground station, and wherein said method comprises the following steps:

telemetering existing jackscrew extensions as measured by potentiometers on the spacecraft to the ground station;

transforming measured jackscrew extensions to existing platform angles at the ground station;

transmitting existing platform angles from the ground station to the spacecraft;

initializing the platform rate command integrator with the transmitted platform angles;

transforming the platform angles into jackscrew extensions;

initializing the jackscrew position registers; and

initializing the computed platform angles using the back transform.