This thesis is a theoretical investigation into the thermal and structural response of large reflector support trusses subject to the space environment. A review of the elements necessary in a successful spacecraft design is included. The determination of the temperature distributions within large orbiting tetrahedral trusses is described. The thermal environment is shown to be an important factor'' in determining the performance of spacecraft. High quality microwave performance of the communication system depends upon the magnitude of distortions within the reflector support truss, and the thermal expansion or contraction of members makes a significant contribution to this distortion. The possibility of flexural vibration of individual members of the truss arising during entry into, or exit from, the earth's shadow is considered. Individual slender members and the radio frequency reflecting mesh cast shadows within the truss. A method for calculating the duration and position of such shadowing events is discussed. The effect that shadows have upon shadowee temperatures is determined using computer programs written by the author. Situations in which temperature gradients between the truss faces exist are highlighted. Such gradients produce bending deflections of the truss. Classical theories are developed to predict the magnitude of thermally induced stresses in the adhesive layer of tubular lap joints having dissimilar adherends. Tubular joints which contain a transition layer are also examined. An appropriately chosen transition layer will reduce the adhesive shear stresses by a substantial amount. Finally, the development of thermally induced stresses and damage mechanisms in laminated composite tubes is discussed. The designer must be aware of the amount of damage that spacecraft materials will experience during the long life missions envisaged for the near future.