Analysis of temperature stress and deformation in caisson composite constructions
Mathematics. Physics. Mechanics
Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia
This paper presents a method of thermal residual stress calculation arising in composite caisson constructions after the manufacturing process. It is necessary to examine the influence of temperature on bulk integral constructions.
There are various fabrication techniques employed by the composites industry. The resin transfer molding (RTM), infusion, prepreg technology are several methods of integral construction producing. In this research prepreg technology is used.
Two main criteria influence the selection of prepregs for a particular application: performance and cost. The advantages of using prepregs are lower fabrication cost, reduced number of parts, control of fiber content, reduced energy consumption, good mechanical performance (tensile, stiffness, corrosion, good ageing, repair)
It is possible, for example, to apply the theoretical research work to manufacturing, that allows to improve the quality of finished product. Applying theory helps to reduce cost and minimize post processes such as finishing and handling.
The present study provides a starting-point for further research in the manufacturing sector.
This is the first research paper examines the influence of temperature on bulk integral constructions that leads to the structural warpage.
Theoretical value is development of the design and calculation methodology for integral constructions. This research has a practical use. Practically, this technique can be used in the design of real constructions such as airplane wings, horizontal and vertical tail assembly.
Keywords:composite material, thermal deformation, deflection, caisson, integral construction
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