Dynamic Modeling and Analysis of Spacecraft with Multiple Large Flexible Structures

Dynamic Modeling and Analysis of Spacecraft with Multiple Large Flexible Structures

Blog Article

An analytical dynamic model is presented for a spacecraft with multiple large flexible structures.Based on the partial differential read more equations (PDEs) of the motion of the solar panel and deployable arm, the governing equations of the main-body and deployable antenna and the boundary conditions at each end point are used to obtain the frequency and mode shapes of the system.Then, the ordinary differential equations (ODEs) of the system can be obtained from the orthogonality relations and mode shape.

The influence of the deployable antenna on the frequencies and mode shapes of the spacecraft is investigated.The frequency veering and mode interchanged phenomenon are observed with the variation of the diameter of the deployable antenna.Using the ODEs, the dynamic responses of the spacecraft are calculated to study the influence of the control torque on the attitude and position of the voyage et cie discount code antenna in the attitude maneuver.