In order to avoid the high cost and high risk of demonstration mission of rendezvous-docking technology, missions using nanosatellites have recently been increasing. However, there are few successful mission cases due to many limitations of nanosatellites like small size, power limitation, and limited performances of sensor, thruster, and controller. To improve the probability of rendezvous-docking mission success using nanosatellite, a rendezvous-docking phase analysis tool for nanosatellites is developed. The tool serves to analyze the relative position and attitude control of the chaser satellite at the docking phase. In this tool, the Model Predictive Controller (MPC) is implemented as a controller, and Extended Kalman Filter (EKF) is adopted as a filter for noise filtering. To verify the performance and effectiveness of the developed tool for nanosatellites, simulation study was conducted. Consequently, we confirmed that this tool can be used for the analysis of relative position and attitude control for nanosatellites in the rendezvous-docking phase.

1. INTRODUCTION
2. MODELING
    2.1 Equation of Relative Motion
    2.2 Attitude Dynamics and Kinematics
    2.3 Controller
    2.4 Extended Kalman Filter
3. METHODOLOGY
    3.1 Design of the Control Analysis Tool
4. RESULT
5. CONCLUSIONS AND FUTURE WORKS
REFERENCES

• Miri Jeong(Korea University of Science and Technology, Daejeon 34113, Korea)
• Dong-Hyun Cho(Korea Aerospace Research Institute, Daejeon 34133, Korea)
• Hae-Dong Kim(Korea University of Science and Technology/Korea Aerospace Research Institute) Corresponding Author