Deformation Analysis Of Solar Arrays When Sattelite Undergoes Space Flight In Orbit

With the development of aeronautics, modern satellite's scale is increasing which enlarges the demand for energy. Thus solar arrays tend to become larger in order to meet the growing energy needs. In addition, solar arrays have to adopt ultra-light and ultra-thin material to make, because satellite's quality should be as light as possible due to the launch conditions and cost. These two aspects contradict each other, making them become a typical large flexible space structures, and posing a great threat to satellite's security. As the air damp is almost non-existent in space, any interference, such as meteor shower, solar wind, orbit maneuver and attitude adjustment, will arouse a persistent vibration with wide range. Therefore, it is necessary to impose effective control measures. However, we must firstly make clear the deformation of solar arrays in order to implement vibration control successfully. So researchs on deformation analysis of solar arrays is significant. The studies includes in this thesis are as follows:(1) In view of box-style satellite with two flexible solar arrays, by defining reasonable reference coordinate systems, a detailed analysis of loads on the center body and solar arrays is carried out respectively based on space environment and satellite's configuration characteristics.(2) A low-orbit satellite's kinematics equations and solar arrays'static equations are set up. A suitable simulation model is established by selecting appropriate orbit, attitude and structural parameters. Satellite's orbit, attitude curve and solar arrays'static deformation curve in an orbit cycle are obtained via MATLAB numerical simulation. The result shows the static deformation is small on the state of normal flight, while large on orbit and attitude manever.(3) Two different simplified models are used to analyse solar arrays'dynamics. By utilizing finite element method, the dynamic equations are founded. One is free straight beam model with lumped mass in middle; the other is free curved beam. On account of static deformation is occurred, the elastic vibration of solar arrays is dynamic deformation based on the static equilibrium position, which changes to a situation of curved beam's vibration. MATLAB programs are written to get the vibration frequencies of two models.In this thesis, a method of flexible structure's elastic deformation description based on the change of static equilibrium position is proposed, and vibration analysis of a special curved beam structure is made. Consequently, the foundation of vibration control system design of flexible appendages when satellite undergoes large overall motion is settled.