Reaction wheel merupakan aktuator aktif yang digunakan pada subsistem Attitude Determination and Control System (ADCS) Satelit, pada penelitian ini pengendalian reaction wheel disimulasikan dengan menggunakan kendali PID dan penalaan menggunakan Algoritma Genetika dengan populasi awal sebanyak 100 populan, laju crossover 0.8, konstanta mutasi 0.01, kriteria penghenti adalah 50 generasi dengan fitness function berdasarkan indeks performansi PID yaitu ITAE. Pengendalian Reaction Wheel pada lingkar tertutupnya dengan kendali PID yang teroptimasi Algoritma Genetika memiliki karakteristik respon transien yaitu rise time 11 detik, setlling time 91 detik, overshoot 33.2% dengan indeks performansi ITAE sebesar 481.9479. Dengan menggunakan simulator Smart Nanosatellite Attitude Propagator (SNAP) berbasis MATLAB, dilakukan simulasi dinamis menggunakan model 3-axis reaction wheel sebagai aktuatornya. Satelit LAPAN –TUBSAT A1 digunakan sebagai objek pengendalian, dilakukan simulasi dengan menskenariokan bahwa satelit dalam keadaan tumble memiliki inisial kecepatan sudut [0.5 0.5 0.5] °/detik kemudian dilakukan detumbling yaitu membuat kecepatan sudut satelit menjadi [0 0 0]°/detik. Sumbu roll dan yaw memiliki error yang cukup besar yaitu direntang 1 rad/s dan -1 rad/s sedangkan sumbu pitch memiliki error kecil direntang 1.5x10−3 rad/s dan −1.5x10−3 rad/s.
Satellite Attitude Determination and Control System (ADCS) uses an active actuator with a Reaction wheel. This study uses PID and genetic algorithms to control the Reaction wheel. The initial population was 200, and the crossover rate was 0.8, the mutation constant was 0.01 with a stop generation criteria of 50 generations. Reaction Wheel Control in a closed ring with optimized PID control The Genetic Algorithm has transient response characteristics that are 1 seconds rise time, 9 seconds set time, 33.2% overshoot with an ITAE performance index of 481,9479. Use the Matlab program to conduct a Smart Nanosatellite Attitude Propagator (SNAP) simulator to create a 3-axis reaction wheel model as its actuator. The satellite is the object of control, simulating the satellite conditions in a tumbling state having the initial angular velocity [0.5 0.5 0.5] ° / second then stumbling which makes the satellite angular velocity to [0 0 0] ° / second. Roll and yaw axes have a significant enough error that is1 rad / s and -1 rad / s while the pitch axis has a small error that is 1.5 10−3 / and −1.5 10−3 /s.
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