Method of controlling the attitude and stabilization of a satellite in low orbit
AssigneeAstrium GmbH
InventorsAnge Defendini, Kristen Lagadec
Life of this patent
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Abstract
For controlling the attitude of a satellite placed on a low earth orbit, components of a vector Bm of the earth's magnetic field along three measurement axes of a frame of reference bound with the satellite (typically by means of a three-axis magnetometer) are measured. The orientation of the earth's magnetic field in the frame of reference is computed and a derivative {dot over (B)}m of the vector is also computed. Magneto-couplers carried by the satellite are energized to create a torque for spinning the satellite at an angular frequency ωc about a determined spin axis of the satellite, where ωc is greater than an orbital angular frequency 2ω0 of the satellite.
Claims18
A method of controlling and stabilizing the attitude of a satellite placed on a low earth orbit, comprising the steps of:
- measuring components of a vector of the earth's magnetic field along three measurement axes of a frame of reference bound with the satellite,
- deducting an orientation of said earth's magnetic field in the frame of reference and a derivative {dot over (B)}m of the vector from said components, and
- controlling magneto-couplers carried by the satellite based on said orientation and said derivative and exclusive of any additional attitude measurements, so as to create a torque from said orientation and derivative of earth's magnetic field for setting the satellite into rotation at an angular frequency ωc about a selected spin axis of the satellite, without need of any internal momentum where ωc is greater than 2ω0, ω0 being an orbital angular frequency of the satellite.
A method of controlling the attitude of a satellite placed into a low earth orbit with an orbital angular frequency of ωo, said method comprising the steps of:
- measuring components of a vector of the earth's magnetic field along three measurements axes of a frame of reference with respect to the satellite;
- determining from said components (i) an orientation of said earth's magnetic field in the frame of reference and (ii) a derivative {dot over (B)}m of the vector, and
- controlling magneto-couplers carried by the satellite, based on said orientation and said derivative and exclusive of any additional attitude measurements, so as to create a torque setting the satellite into rotation at an angular frequency ωc about a selected spin axis of the satellite, without need of any internal momentum, wherein said selected axis can be other than the axis of greatest inertia and wherein ωc is greater than 2ω0.
Dependencies are inferred from the claim text.