Dynamic Analysis And Damping Parameters Determined Of Large Spacecraft Developable Structure

Modern spacecraft often carry large-scale and deployable structure such as solar panel, antenna and so on, of which the deployment will affect the attitude motion. Especially when solar wing is developed into the proper position, great impact moment will be inevitably loaded on the hinges due to the large speed of solar panel at present and the whole deployable structure will produce violent vibration because of the total energy stored in the hinge being released. In annex damped circumstances, vibration will eventually decay, but impact will be inevitably produced on the spacecraft in the process of attenuation. So on base of full-scale dynamics simulation of deployment and locking of deployable structure, put forward evaluation criterion and damper parameters selection principle of the dampers installed whether or not, and provide guidance of the structure design for large developable structure. Based on the systematical generalizing of present status, the thesis investigates the deployment dynamics of the appendages for a certain satellite that is undergoing development by flexible multi-body system theory. The chief achievement is listed as below.Based on the Newton's law of motion, the law of angular momentum and the variation principle, the dynamic equations of the satellite with a flexible solar panel has been established, the final expression of the dynamic equation is hybrid one of algebra and differential. Based on Euler kinematical equations, the kinematical model of the satellite has been established. Numerical analysis is proceeded to the model established using the tool of MATLAB.Based on the multi-body system dynamics simulation software ADAMS, satellite system model is established in detail containing deployment synch-ronization mechanism, deployment driving mechanism and locking mechanism, which is compared to the math model to verify the rationality. The dynamics simulation research to the satellite solar panels is made in detail. Focus on investigating the difference on the attitude angle of the satellite and the locking impact moment between the hinges during the process of deployment, by which analysis and summary is carried on.In view of the dampers improving the change of satellite angle during the process of deployment and improving the influence on the impact moment during the process of locking, focus on analyzing the influence of different parameter (position, number and size) of damper. Through simulation, analysis and comparison of a variety of conditions, evaluate the reduction effect of the damper, and propose damper parameters selection principle.