Flexible dynamic model of attitude maneuvering of RazakSAT® Satellite

In this paper,a dynamic model equation of the razaksat® class satellite three flexible solar panels for three-dimensional dynamic studies is developed based on the coupling deformation field. in the model,each solar panel is flexible and attached to the satellite body via a fixed joint where the assumption of euler-bernoulli beam is applied for the solar panels. lagrange and assumed mode method are used to develop the dynamic model of the razaksat® multi-body system. a comprehensive model of flexible satellite has been provided in ansys environment as a reference when simulating the theoretical response generated by matlab to show that the coupling effect on the characteristics of the flexible sub system while undergoing rigid-body rotational motion. © 2015 penerbit utm press. all rights reserved.