Anisogrid structures made of high-modulus carbon fiber reinforced plastics have become widely employed as structural elements of spacecrafts. The unique mechanical behavior of anisogrid cylindrical shells determines the use of these structures in the development of new types of space technology. An example is a space telescope, whose main load-bearing component consists of a thin-walled lattice cylinder with massive equipment attached to its edges. The buckling of a telescope structure under thermal loading is an important issue to be addressed in design. The computational model for this problem is an anisogrid lattice cylindrical shell formed by composite helical and circumferential ribs experiencing a sudden temperature rise. This paper aims to numerically determine the temperature at which the two edges clamped lattice cylinder buckles. To simulate the anisogrid shell as a spatial frame, a beam-type finite element is used. A parametric study is performed to evaluate the influence of the number of helical ribs and their orientation angle on the critical buckling temperature.
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