ESTIMATION OF SATELLITE MASS CHARACTERISTICS

摘要

PURPOSE:To perform the high-precision navigation guidance control by vibrating a satellite on the orbit in three axes, statistically processing detected signals of the resulting rotating speed and acceleration in each axis of the satellite, and estimating the mass characteristics of the satellite. CONSTITUTION:In an artificial satellite, reference orthogonal three axes (x, y, z) are set, reaction wheels 1x, 1y, 1z as a vibration means are provided in each axis. A three-axis rate gyroscope 2 and an acceleration meter 3 are also provided. In this case, the satellite is vibrated in orthogonal three axes by the reaction wheels 1x, 1y, 1z, the input torque of the vibrating means and output signals of the three-axis rate gyroscope 2 and the acceleration meter 3 are statistically processed, thereby the mass characteristics of the satellite such as the inertial efficiency, inertial product, position of center of gravity or the like are estimated. During the navigation guidance control of the satellite on an orbit, satellite mass characteristic parameters are changed to the above estimated values to attain the high-precision navigation guidance control.