Attitude Vibration Caused by a Stick–Slip Motion for Flexible Solar Array of Advanced Earth Observation Satellite

Abstract: The Advanced Earth Observation Satellite (ADEOS), a remote sensing satellite, was developed by the National Space Development Agency of Japan and launched in 1996. ADEOS had a large flexible solar array, which was made of a membrane-like structure of 23 m in length. During the checkout and subsequent phases of in-orbit operations, it was discovered that the attitude control system was experiencing internal disturbances that had not been anticipated. An intensive investigation based on the down-linked flight data revealed that mechanical vibrations was caused by a stick–slip motion at the tension control mechanism (TCM) of the solar array. The scope of this paper is to present an analytical approach to the stick–slip of the TCM by means of spacecraft attitude responses. The mathematical model utilized assumes that the spacecraft was composed of a main rigid body and flexible appendages, which consist of a number of rigid plates connected by torsional hinges. Key parameters of the hinges are determined by applying the equations of vibration of a uniform cantilever beam with tangible physical parameters. This mathematical model has been evaluated using the ADEOS flight data and ground-based test data. It is concluded that the technical approach and mathematical model utilized have correctly represented actual spacecraft motions