Abstract
Today large space structures are in focus of attention of engineers and designers of rocket and space equipment. In ground-based experiments, it is not always possible to carry out complex tests of large space structure functionality. Therefore, the development of mathematical models describing properly the transformable structure dynamics when they opened from the densely packed transport state to the operating position in the orbit becomes very important. To determine the stress-strain state of the frame elements when it is unfolding the shape of the framework is taken at the moments when relative velocities of the adjacent sections are maximal. Supposed, that at these moments the frame elements are getting on the stops limiting their relative angular displacements, and the structure behaves as an elastic rod with specified characteristics. Numerical analysis of the stress-strain state in the framework is carried out by means of a finite element model. Therefore, the represented mathematical model can be effectively used to predict the functional suitability of such transformable space structures already on the early stages of their development.
Highlights
Today large space structures are in focus of attention of engineers and designers of rocket and space equipment
In ground-based experiments, it is not always possible to carry out complex tests of large space structure functionality
That at these moments the frame elements are getting on the stops limiting their relative angular displacements, and the structure behaves as an elastic rod with specified characteristics
Summary
Among the large space structures a special place is occupied by transformable structures allowing configuration changes [1,2,3,4] Such structures are delivered to a near-earth orbit being folded and placed in a container. When the desired operational orbit is reached, the opening of the structure load-bearing framework (or its transformation) is fulfilled. The design of the load-bearing framework for the transformable space systems contains a large number of elements connected by hinges. At the beginning steps of the development, generation of mathematical models that ensure effective calculation of the structural parameters and analysis of various variants of packing the structure for transportation and subsequent unfolding to the operating position in the orbit is an urgent task
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