Document Type : Original Article
Authors
1 MS graduated/Sharif university of technology
2 Aerospace department, Sharif university of technology
3 Iranian Space Research Center Academic Staff
Abstract
One of the key issues in the operations of on orbit servicing to unmanned satellites is to provide a safe and reliable docking process. This paper investigates the dynamic behavior of a flexible probe in the central docking mechanism of unmanned satellites.
For simulating the impact phenomenon, a dynamic analysis software (MSC. Adams) has been applied and a three-dimensional model has created based on the assumption of a flexible clamped beam as a shock absorber. The results are in good agreement with similar theoretical and experimental results. additionally, it is possible to consider the parameters such as the type of connection between the beam and the concentrated mass, angular and translational velocity of chaser and target satellites, in order to determine the optimum condition to perform a successful docking operation. The results of this study indicate that the use of a spherical joint for the ball attached to the probe, significantly reduces the maximum value of impact force. Also, the rotation of the sphere leads to less change in the linear and angular velocity of the target satellite and increases the probability of successful mating of the satellites. On the other hand, the movement of the conical area relative to the target satellite reduces the maximum impact force and shock resulting on the satellites structure. As a result, the chance of successful docking increases.
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