Wheel speed management control system for spacecraft

• US 5,058,835 A
• Filed: 06/11/1990
• Issued: 10/22/1991
• Est. Priority Date: 06/11/1990
• Status: Expired due to Term

• Current Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Original Assignee: General Electric Company
• Inventors: Linder, David M., Goodzeit, Neil E.
• Primary Examiner(s): Peters, Jr., Joseph F.
• Assistant Examiner(s): Mattix, Carla
• Application Number:
  US07/535,675
• Time in Patent Office: 498 Days
• Field of Search: 244/164, 244/165, 244/171, 244/176, 364/432, 364/434, 364/459
• US Class Current: 244/165
• 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 spacecraft attitude control system uses at least four reaction wheels. In order to minimize reaction wheel speed and therefore power, a wheel speed management system is provided. The management system monitors the wheel speeds and generates a wheel speed error vector. The error vector is integrated, and the error vector and its integral are combined to form a correction vector. The correction vector is summed with the attitude control torque command signals for driving the reaction wheels.

Claims

1. A spacecraft, comprising:

attitude control sensing means for generating attitude signals representative of spacecraft 3-axis attitude;

at least four mutually skew reaction wheels adapted to receive torque drive signals for torquing said spacecraft under the control of said torque drive signals;

attitude control means coupled to said attitude control sensing means for processing at least said attitude signals for generating torque command signals;

coupling means coupled to said attitude control means and to said reaction wheels for translating signals from said attitude control means to said reaction wheels, whereby the speed of any one of said wheels may tend to exceed the power optimal value required to control said attitude, said coupling means comprising summing means including a first input data port coupled to said attitude control means for receiving said torque command signals, and also including a sum output port coupled to said wheels and further including a second input data port, said coupling means further comprising wheel speed control means coupled to said second input data port and also coupled to said means comprising (a) wheel speed error signal generator means coupled to said wheels and responsive to said wheel speeds for generating error signals representative of a wheel speed error vector, which error vector represents the difference between actual and power optimal speeds of said wheels, (b) integrating means coupled to said wheel speed error signal generator means for integrating said error signals to produce an integrated signal, and (c) processing means coupled to said wheel speed error signal generator means, to said second input data port of said summing means, and to said integrating means for processing said error signals and said integrated signals for producing wheel speed management signals in response to said wheel speeds, and for applying said wheel speed management signals to said second input data port, whereby said wheel speed management signals are summed with said torque command signals to produce said torque drive signals for control of said wheels to redistribute the momenta of said reaction wheels so that the total power is minimum.

2. A spacecraft according to claim 1, wherein said processing means comprises linear combining means for linearly combining said error signals and said integrated signals to generate said wheel speed management signals.

3. A method for controlling spacecraft attitude, comprising the steps of:

sensing the attitude of said spacecraft to produce attitude signals;

processing said attitude signals to produce torque control signals representative of the torques required to maintain said spacecraft 3-axis stabilized;

spinning at least four mutually skewed reaction wheels mounted on said spacecraft in response to said torque control signals;

sensing the speed of said wheels to produce wheel speed signals;

processing said wheel speed signals to generate wheel speed management control signals representative of the deviation of said wheel speeds from power optimal values, wherein said wheel speed signals processing step comprises the further steps of (a) generating wheel speed error vector signals from said wheel speed signals and information relating to the dimension and orientation of said wheels, (b) integrating said wheel speed error vector signals to produce integrated signals and (c) processing said wheel speed error vector signals and said integrated signals together to generate said wheel speed management signals; and

summing said wheel speed management signals with said torque control signals whereby said wheel speeds are maintained near said power optimal values.

4. A method according to claim 3 wherein said step of processing said wheel speed error vector signals and said integrated signals together comprises the step of combining said wheel speed error vector signals and said integrated signals.

5. A method according to claim 4, wherein in said step of combining, said wheel speed error vector signals and said integrated signals are combined with proportioned combining gains, and the proportional combining gains for the i^th wheel are set to:

##EQU2## where I_wi is inertia of the i^th wheel;

ω

_c is the attitude control system crossover frequency; and

Γ

_i is the i^th diagonal element of the n×

n wheel speed error matrix.

6. A method according to claim 4, wherein, in said step of combining, integral combining gain for the i^th wheel, is set to ##EQU3## where Δ

t is the control system sample period.