An estimation was made on the in-orbit attitude motion of the small engineering experimental satellite 'ORIZURU'. Attitude data are provided only from the satellite's sun sensors. To estimate the attitude motion, the flight data were compared with numerical simulation results, and parameters with coinciding patterns were sought. The attitude motion is estimated as follows: The spin cycle grew longer at a certain rate as the time elapses (decrease in spin angular speed), the time of 41.5 seconds at the beginning varies at a rate of 0.89 sec/d. Major cause for this phenomenon should be the influence from eddy current. Lateral moment at separation from the rocket generates nutation whose angle is 52.1 degrees. The sun angle varies largely in the simulation. This should be because of actions of disturbance torques such as eddy current torques. The spin cycle change was extrapolated, where the spin cycle immediately after separation from the rocket was estimated 39.7 seconds. From this value, the external force imposed from the spring at the separation was calculated 0.66 Nms for axis circumference and 0.84 Nms for perpendicular axis circumference. 4 refs., 12 figs., 3 tabs.
Kogata jikken eisei ''ORIZURU'' no shisei undo. (Estimation of the attitude motion of the small satellite ''ORIZURU'')
1992
28 pages
Report
Keine Angabe
Englisch
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