Analysis Of The Composite Material Truss Structural Thermal Deformation

The carbon fiber composite material is focus attention fully, for its light quality, high strength, heat-resistant, bearing corrosion and a good characteristic of the thermodynamics performance. Along with satellite technical development, the carbon fiber composite material truss structure is more and more applied to the satellite structure. The form of truss structure is a simple, the load distribution is reasonable, the local strength is high. It is easy to install and dismantle. Particularly, its universalness and assembly are good. It can be combined according to the different configuration. The applying foreground of truss structure is very extensive. Because of the thermal expansion coefficients discrepancy between the metal and the composite material, the changing of the environment temperature of the satellite running is acutely, the thermal deformation will generate for the carbon fiber composite material truss structure. The satellite structure is different with public production. The weight and the thermal deformation of truss structure are restricted strictly. Therefore it is very important to control the thermal deformation of the composite material truss structure by change its design variable.The performance of the truss structure of satellite is studied in the paper. The traditional metal poles are replaced by the advanced composite material poles. The joints of the truss structure are made of the metal composite material. The structural poles are made of the carbon fiber winding composite material. The thermal deformation performance subjected to the temperature load is investigated by using finite element method. The first, the effects of the winding angle of the composite material structural poles, the layer number and the single layer thickness on the truss structure thermal deformation are discussed. The second, the results of the thermal deformation of composite material truss structure are given by changing the winding angle of composite material structural poles, then the winding scheme of composite material structural poles are obtained, in which the truss structure thermal deformation is small. Finally, according to the relevant theory, the existence of the defect or the damage in the structural poles is equal to the rigidity attenuation of the structural poles. The effects of the defect or the damage of the different site composite material structural poles on the truss structure thermal deformation are obtained by studying the influence of the rigidity attenuation of the different site composite material structural poles upon the truss structure thermal deformation. The truss structure thermal deformation's rule with the structural poles rigidity reducing is given. From the results, we have that the influence of the rigidity attenuation of the composite material structural poles upon the composite material truss structure thermal deformation is large. These results are useful for the design and application of the composite materials truss structure.