Smallsat Rational Design

Abstract

This paper is devoted to the study of CubeSat rational designing technique. The CubeSat design process is comprised of choice of its trajectory, determination of components and main parameters of its systems, development of external and internal layouts, determination of the number of satellite-born antennas and their main characteristics. The potential of CubeSat has prompted the scientific community to rethink the existing spacecraft technologies and think about how to make them suitable for CubeSats. In terms of specialization of engineering works during Smallsat development, was formulated concept of the design process and recognized physical relationships to find some optimal design solution about compatibility of basic parameters and characteristics. The purpose of Smallsat rational design is to create a project of a vehicle for which the value of the selected criterion is close to the maximum or minimum value. As a result, the design algorithm version was making. The described method of rational design, of course, does not deny the process of intuitive creative thinking. This process reveals itself in assumptions and development of reference versions, as well as in ballistic design.