Abstract
The offset-feed truss reflector is installed with unilateral restraint. In the deployment process, it is expanded and deployed on one side, with fast deployment speed and impact force, which has a certain impact on the structure of the antenna itself and the flexible load accessories on the satellite, especially the solar wing. In order to accurately evaluate the impact of deployment, a 6-DOF force measuring platform is built, the deployment impact force and moment of the antenna are measured, the multi-body dynamic model including the satellite is established on the base, and the impact dynamics analysis of the satellite during the deployment of the antenna is carried out. The analysis results show that the maximum pitch angle of the satellite during the deployment of the antenna is 0.81°, The impact force borne by the south solar wing is greater than the north wing, and the maximum value is less than 40N. The impact moment along the rotation direction of the solar wing will exceed the holding torque by 6Nm, and it will have a certain out of step phenomenon. The analysis results provide technical support for the on orbit safety of the solar wing during antenna deployment.
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