Host: The Japan Society of Mechanical Engineers
Name : Dynamics and Design Conference 2016
Date : August 23, 2016 - August 26, 2016
In this paper, spacecraft with tether and sub-satellite is analyzed to optimize the intermediate masses attached to the tether and the optimization purpose is to minimize the settling time of deployment process from stowed state, where constant force exerted on sub-satellite attached to the end of the tether. The analysis is carried by the use of a method proposed by authors. The method enables low-computational analysis for the system with extremely flexible element by utilizing the complementarity which the system has. The results of the analyses shows that the existence of the optimum value of intermediate mass, and furthermore such a possibility of optimization reveals the validity of the analysis method proposed by authors.
