Abstract: One of the key goals of satellite design is reduction of system’s mass while maintaining high reliability (probability of faultless operation). Every technological decision made is based on the goal of the project, available production and technological base, material and time resourses and designer’s experience. A large number of iterations of design work at enterprises could be often attributed to the established features (traditions) of the organization of work of designers and technologists. There is a demand for advancement of satellite design methods. Development of every satellite component should be carried out within a set of shared models of structural loading, thermal conditions assembly model, unified functional model and a unified model for the formulation and execution of design requirements. This approach to design is theoretically justified. Also, this approach is published in a more systematic way and is compared with other approaches.