Development and Verification of Attitude Determination and Control Algorithm for "SNUGLITE" Cube Satellite
Minkyu Choi, Sunkyoung Yu, O-Jong Kim, Heekwon No, Hanjoon Shim, and Changdon Kee, Institute of Advanced Aerospace, Seoul National University, Republic of Korea
Location: Grand Ballroom G
Date/Time: Tuesday, Jan. 30, 5:00 p.m.
SNUGLITE(Seoul National University GNSS Laboratory Satellite) is 2U-size Low Earth Orbit (LEO) CubeSat (U-class spacecraft). Attitude Determination and Control System (ADCS) of CubeSat is designed to maintain its attitude at the Earth pointing. For determining satellite's attitude, Extended Kalman Filter (EKF) and Linear Quadratic Gaussian (LQG) algorithm were applied. Specifically, multiple sensors - dual frequency GPS receiver, 3-axis gyroscope, magnetometer and sun sensors - were used with models Jet Propulsion Laboratory sun reference Development Ephemeris (JPL DE405) and International Geomagnetic Reference Field (IGRF12). Moreover, 3-axis magnetorquer was used as a single actuator. Generally, the verification of ADCS algorithm starts from software-in-the-loop simulation (SILS) developed and verified in software tools such as MATLAB. After verification of SILS, Processor-in-the-Loop simulation (PILS) is required to verify the ADCS algorithm implementing in the processor of On Board Computer (OBC) in C-language. Finally, satellite’s ADCS algorithm is needed to be verified experimentally by hardware-in-the-loop simulation (HILS) in the space-like environment under a ground-based setting using a massive simulator. Most of satellite attitude HILS is composed of sensors such as air-bearings, Helmholtz coil, and array sun sensors. In this paper, to verify ADCS algorithm in HILS, the precise attitude estimation, modeling and calibration of sensors (magnetometer, gyroscope and coarse sun sensor) are presented. In addition, a low-cost single-axis HILS verification method is proposed using simple testbed hanging CubeSat with a wire. By using the Earth’s magnetic field on the ground and the light from Halogen lamp, the space environment has been implemented on the ground in order to verify attitude determination and control performance in a single axis. In conclusion, the results of the HILS ensure that the performance of the proposed algorithm meets the estimation and the control requirements of the SNUGLITE.