Satellite design, development, fabrication, testing and entry into service is a complex process. Each step of this process involves intricate steps to achieve the desired objective. This thesis summarizes a study relating to the area of development and testing of microsatellites to support qualification and eventually preparing a spacecraft for spaceflight. Students in the Space Systems Engineering laboratory (SSE Lab) in the Aerospace Engineering Program are in the process of developing a pair of microsatellites for a technology demonstration in space.
After the initial design of the spacecraft is completed in the design phase a significant amount of time is spent on gaining confidence in the design. Various mathematical models are developed to represent the system and to verify its functionality. In the case of the primary structure of microsatellite a finite element model (FEM) is used to predict the behavior of the satellite structure and to verify strength requirements of design before its fabrication. Finite element model its application and results obtained form the majority of this thesis after which concentration is given to the testing phase of the microsatellite. After gaining confidence in the design and fabrication of the components it is important to validate the structure by subjecting it to structural testing. Structural testing is the only means to gain confidence in the design and certifying it for spaceflight. The results obtained from testing show how closely mathematical model (FEM) represents the physical system and provides an important learning experience for the satellite team and to help better understand and improve the design of the next generation of satellites on campus --Abstract, page iii
