Electrical energy management and attitude control system for a satellite

• US 6,439,510 B1
• Filed: 10/30/2000
• Issued: 08/27/2002
• Est. Priority Date: 10/29/1999
• Status: Active Grant

• Current Assignee: Astrium Sas (Airbus SE)
• Original Assignee: Astrium Sas (Airbus SE)
• Inventors: Barde, Henri
• Primary Examiner(s): Jordan, Charles T.
• Assistant Examiner(s): DINH, TIEN QUANG
• Application Number:
  US09/698,477
• Time in Patent Office: 666 Days
• Field of Search: 244/165, 244/158.R, 244/164, 322/4, 322/16, 322/38, 322/39, 310/76, 310/102.R
• 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 1/426 Flywheels
• CPC Class Codes: B64G 1/428 Power distribution and management

Abstract

A system for managing electrical energy and for controlling attitide of a satellite has an attitude control unit which controls a plurality of reaction wheels oriented about different axes for instance three wheels. An on-board electricity power supply network has a solar array, a payload and a storage unit connected to a power line. The storage unit comprises a buffer supercapacitor and one inertia wheel unit with a respective motor/generator and typically two contra-rotating wheels. Interchanges between the storage units and the power supply line are controlled by a regulator which attenuates power demand transients and thus torque transients on the inertia wheel or wheels.

Claims

1. A system for managing electrical energy and for controlling attitude of a satellite comprising:

an on-board electricity power supply and storage network having a primary power source and a storage capacitor connected to a power line, at least one set of two mutually aligned counter-rotating inertia wheels each with a respective motor/generator, and a regulator for controlling electrical power interchanges between the motor-generators of said inertia wheels, the storage capacitor and the power line for attenuating power demand transients and torque transients applied to the inertia wheels by causing discharge and charge of the capacitor; and

an attitude control assembly having a plurality of reaction wheels oriented about mutually different axes and a control unit controlling said reaction wheels for attitude control about axes other than a direction of alignment of said inertia wheels.

2. System according to claim 1, wherein said regulator comprises a filter for limiting the rate of variation of power called from and applied to the inertia wheel.

3. System according to claim 1, wherein the two mutually aligned counter-rotating inertia wheels are driven at substantially the same rotational speed.

4. System according to claim 1, wherein said regulator has means for distributing any torque call between the two inertia wheels of the set.

5. System according to claim 1, having a regulation circuit controlling a difference between torques each required from one of the two inertia wheels, responsive to an attitude error signal representing an error of position of the satellite about a common axis of the inertia wheels.

6. System for managing electrical energy and controlling attitude of a satellite, having:

an attitude control unit controlling a plurality of wheels oriented about mutually different axes, and

an on-board electricity power supply network having a solar array constituting a power source;

storage means comprising a buffer storage capacitor and a rotary unit having two contra-rotating inertia flywheels mutually aligned along a common axis different from said mutually different axes, each having a motor-generator; and

regulator means for controlling power transfers between power receivers on the satellite, said storage means and said solar array, said regulator being arranged to attenuate power demand transients or power delivery transients, and thus torque transients, from and to the rotary unit responsive to power call from the payload and variations in power delivered by the solar array.

7. System according to claim 6, wherein said regulator means includes means for determining set values of the torque calls required from each of said flywheels for control of attitude of the satellite about said common axis.

8. System according to claim 6, wherein the common axis is a pitch axis of the satellite and said mutually different axes of said reaction wheels are located in a yaw-roll plane.

9. System according to claim 7, wherein said regulator means are arranged for imparting a set time variation of constant slope to the torque transient.