Abstract
GyroWheel is an integrated mechanism which provides both attitude control torques and measurements of attitude angular rates for tiny spacecrafts. However, aerodynamic interference is inevitable in the process of ground test which hinders the improvement of the system performance. In this paper, the modelling issue of aerodynamic interference with respect to the three-DOF GyroWheel rotor is investigated. Based on the analysis of force distributions associated with each degree of freedom, the dynamical model of the GyroWheel rotor is established with Euler's method. According to the analysis of medium flow field, the mathematical model of the aerodynamic interference is formulated by utilising the boundary layer theory and Navier-Stokes (N-S) equations, which is illustrated by some numerical simulations in the environment of FLUENT.
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