Abstract
Understanding the dynamic characteristics of solar arrays is important for satellite structural design and attitude control design. Considerable theoretical researches have been carried out towards this problem, but they have not been supported by actual orbit data from outer space yet. In this paper, the on-orbit vibration characteristic data of solar arrays under the deployment shock are measured by using vibration measurement apparatuses based on structural strain. With these valuable experimental data, more eigenfrequencies of the solar arrays in the microgravity environment are obtained, and the prediction that the vibration of solar arrays will have larger amplitude and longer decay time under vacuum conditions is verified. Moreover, by comparing the eigenfrequency of main vibration under the space condition with that under the ground condition, the accurate value of the system damping ratio is gained, which has an important guideline significant for the structural design of solar arrays.
Highlights
In order to meet the increasing power requirement, modern large satellite platform usually carries large solar array structures
With the developed vibration measurement apparatus, we conduct both the ground deployment testing and on-orbit ying testing for the GF-2 satellite solar array, and strainform vibration signals of the solar array caused by the deployment and locking shock are successfully measured in the two tests
With the designed vibration measurement apparatus based on strain gauges, this paper conducted an on-orbit vibration measurement research on the solar array of the Chinese GF-2 satellite during this deployment process. e main contribution of this paper can be summarized as below: (1) An efficient vibration strain measurement apparatus that suits the space application is developed
Summary
In order to meet the increasing power requirement, modern large satellite platform usually carries large solar array structures. The deployment and locking process of satellite solar arrays, which is always completed in a very short time (usually less than 5 seconds), will lead to a large transient impulsive forces and moments exerting on the satellite system. These disturbing loads will result in a large vibration behavior of solar arrays due to their structural flexibility, and this may affect the flight orbit and attitude of satellite [5–10]. E research presented in this paper will be of great significance for acquiring the actual dynamic characteristics of satellite solar arrays and guiding the structural design of satellite solar arrays.
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