When spacecraft works, it will suffer different temperature environments, while temperature difference will always introduce changes of shape and size of composite structures. However, some spacecraft parts need high dimensional stability to keep its right function. Till now, the mechanical properties of the composite have been widely studied, however, the thermal properties of composite and optimization of composite considering both thermal and mechanical properties are far from well studied. Composite tubes were optimized to a given coefficient of thermal expansion (CTE), and the stiffness of those tubes was taken into consideration at the same time. Firstly, multi-scale numerical models were developed to calculate the CTE. In micro-scale mode, the CTE of unidirectional fiber reinforced composite was calculated by the fiber CTE through representative volume elements (RVE). In macro-scale, a composite tube model was generated to predict both axial and transverse CTE of the tube based on the CTE computed by RVE. Composite laminates and tubes with given plies were analyzed and tested. Comparison between the predicted results and the experimental one verified the model, which made the foundation for the optimization mode. Secondly, optimization models for composite truss structure were created. The conjugate gradient method was adopted to optimize the plies of composite parts, and the thermal-mechanical optimizing method was developed. Finally, the satellite support truss structure was analyzed by the thermal-mechanical optimizing method. Analyzed results show that this optimized support structure and the whole antenna have an excellent thermal dimensional stability. The thermal-mechanical optimizing method can be used for thermal stability design and analysis of composite support truss structures. [ABSTRACT FROM AUTHOR]