The importance of developing and constructing systems for nano-satellites, including cube-satellites, is increasing as the space industry grows and the system is miniaturized worldwide. These nano-satellites are limited in sub-system configurations because of their smaller size, reduced mass and power compared to conventional commercial satellites. The Attitude Determination and Control System (ADCS), which requires precision to perform the targeted mission, is also one of the constrained sub-system, and the techniques using various sensors are presented to achieve good performance within the constraints. This paper presents attitude determination method using multiple GPS antennas and the simulation results. Most attitude determination systems based on GPS, estimate attitude by resolving the integer ambiguity of differential carrier phase measurements (Hauschild et al. 2019) or eliminating the effects of integer ambiguity using the motion of the platform (Cohen 1992) for high precision. To apply this to the cube-satellites, geometric constraints are added with differential carrier phase measurements to reduce the amount of calculation needed to resolve integer ambiguity and simplify the process required for attitude estimation. The simulation is used to verify the performance of the proposed attitude determination method. And from this results, it can be verified that it is sufficiently possible to perform on the cube-satellites.

Keywords: GPS, multiple antennas, attitude determination, cube-satellite