B - Operations – Transporting – 64 – G
Patent
B - Operations, Transporting
64
G
B64G 1/36 (2006.01) B64G 1/24 (2006.01) B64G 1/28 (2006.01) B64G 1/38 (2006.01) G05D 1/08 (2006.01)
Patent
CA 2117094
ABSTRACT A process is disclosed for controlling the attitude of a three-axis stabilized, spinning spacecraft, in order to maintain the spinning direction in inertial space and to limit the nutation amplitude. For that purpose, the deviation of the spinning direction from the set orientation, as well as the nutation amplitude, are constantly checked for exceeding predetermined set values (? d?, dN) by separate dead zone control elements. However regulating steps for reducing nutation may also be triggered when the spinning direction is within predetermined admissible limits. A corresponding attitude control device has at least one atti- tude sensor for measuring the angular deviation with respect to at least one of both lateral axes, and actuators for generating torques. From the angular deviation signals are derived two signal fractions that represent on the one hand the orbital dis- placement (?0) and on the other hand the nutational displacement (?N) of the spacecraft. The first signal fraction (?0) runs in a first signal path with a first dead zone (204), the second signal fraction (?N) runs in a second signal path to form a signal for the nutation amplitude (AN) and a signal for the nutation angle (.beta.N). A common nutation regulator (205) for de- tennining the moment when controlling torques are triggered is connected after both signal paths. The nutation regulator al- so receives the output signal of a second dead zone control element (209) which receives at its input the signal AN.
Bittner Helmut
Surauer Michael
Deutsche Aerospace Ag
Smart & Biggar
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