Multi-objective optimization of spacecraft electrical power subsystem design/sizing

This paper presents application of multi-objective optimization to the design of spacecraft power subsystem. The selection of optimum design can be achieved by having a comparative trade study among different alternatives available. The paper provides a methodology to optimize the SEPS (Spacecraft Electrical Power Subsystem) design process taking into account both the technology trades and initial sizing in a constrained environment. The primary requirements for the design which depend on the mission choice like, average power, mission life, temperature and radiation environment, both for low earth orbit and geosynchronous earth orbit are considered here. The paper briefly describes comparison of different technologies available within the solar cells, solar array and batteries. Then it presents spacecraft power system sizing, which is derived by the mission requirements and design constraints imposed by technology available. Finally genetic algorithms are applied on this design process to get best possible choice for the design.