چكيده به لاتين
In this thesis, the effect of impact on the dynamic behavior of micro-sattelites has been investigated and a new buffering mechanism, which is based on probe-cone docking unit equipped with shock absorbers, has been introduced to remarkably decrease the impact phenomenon during capture process. In the theoretical model, it has been used the viscous damper as well as eddy current damper. In general, docking mission requires at least two spacecraft: active and passive ones called chaser and target, respectively. In the probe-cone docking mechanism, the docking probe and docking cone are mounted on the chaser and target satellites, respectively. Compared to the current mating systems in which the docking probe was tightly clamped to the main body of chaser, the proposed buffer can freely experience both translational and rotational motions with respect to chaser. The Lankarani-Nikravesh contact force model is used to study interaction between multibody systems. First, the theoretical model has been formulated by unconstrained multibody dynamics together with constrained multibody model. Second, according to a new alternative validation approach, which is based on constrained multibody problem, the accuracy of presented model can be also evaluated. This proposed verification approach can be applied to indirectly solve the constrained multibody problems by minimum required effort. Third, the entire docking process has been built in Matlab/Simulink’s SimMechanics multibody virtual environment from initial contact to simulation time in order to ascertain the correctness of the theoretical model. Finally, a simple planar ground-based setup has been established to prove the ability of the proposed buffer in capturing target vehicle. Numerical results indicate that the proposed buffering mechanism with proper joint flexibilities is able to considerably reduce impact force, to remarkably increase the total contact duration and to successfully implement the capture mission.
