Dynamic model and simulation on attitude menoeuvring of flexible satellite

Abstract

Flexibility has gained much interest in satellite design in recent years due to its capability to accommodate much for functionality with minimum trade-off. A flexible satellite is satellite that consists of many movable components that is much more sceptical towards external and internal interferences. In this paper, the flexible model of the hexagonal bodied satellite with 3 appendages is derived. Natural physical properties of the satellite were used to derive the mathematical model based on the principle axis of the moment of inertia of the satellite. Verification on the mathematical model is done using MATLAB software to simulate the dynamic behaviour of the satellite. This paper only demonstrates the passive control method.