In this report, parts of the systems engineering of a spacecraft are presented. In 2014 the Royal Institute of Technology KTH initiated a new space technology and research platform, the KTH Space Centre. The first student project at KTH Space Centre was the MIST student satellite with the scope of the system design and construction of a real satellite due for launch in 2017.
As part of the MIST project this bachelor thesis covers the mission analysis and parts of the system design. The system design is confined to the orbit lifetime and attitude perturbation analysis of the spacecraft and a complete analysis of the solar array illumination for the power system.
The orbit lifetime was simulated in two different software, AGI’s Satellite Toolkit (STK), and NASA’s Debris Assessment Software (DAS). An approximate lifetime could be calculated from the two separate programs.
The perturbation analysis was done by deriving parts of the governing equations of disturbance torques in the orbit. The analysis is confined to aerodynamic, magnetic dipole moment and gravity gradient torques. From these calculations the actuatio strength needed by the attitude control system was determined.
The solar array configuration analysis was done by looking at the power generation and illumination of the solar panels in all of the possible flight attitudes.
Following a computation of the power requirements a power budget was created and in conjunction with the complete configuration analysis of the solar array the optimal flight attitude was determined.
The results of the system design analyses are compiled into a baseline design specification. The report is concluded with a discussion of the future work in the project and the lessons learned from the systems design process.
2015. , 20 p.