TY - GEN
T1 - Application of active disturbance rejection control technology in missile with thrust vector control
AU - Wang, Xijiang
AU - Zhou, Daming
AU - Zhang, Ke
N1 - Publisher Copyright:
© 2019 IEEE.
PY - 2019/2
Y1 - 2019/2
N2 - A design method of thrust vector control missile attitude control system is presented in this paper. Firstly, the short period motion model of thrust vector missile is established. Secondly the attitude controllers of pitch, yaw and roll channels are designed based on ADRC (Active disturbance rejection control technology), and the control structures of pitch, yaw and roll channels are given. In pitch (yaw, roll) channel, the pitch (yaw, roll) angular velocity loop is used to track the command of pitch (yaw, roll) angular velocity rapidly, and the angle of attack (sideslip angle, roll angle) loop is used to track the command of angle of attack (sideslip angle, roll angle) rapidly. Finally, the stability of the designed closed-loop system is proved by Lyapunov method. The thrust vector control missile model designed by this method is simulated numerically, and the results show that the designed missile attitude has good response characteristics.
AB - A design method of thrust vector control missile attitude control system is presented in this paper. Firstly, the short period motion model of thrust vector missile is established. Secondly the attitude controllers of pitch, yaw and roll channels are designed based on ADRC (Active disturbance rejection control technology), and the control structures of pitch, yaw and roll channels are given. In pitch (yaw, roll) channel, the pitch (yaw, roll) angular velocity loop is used to track the command of pitch (yaw, roll) angular velocity rapidly, and the angle of attack (sideslip angle, roll angle) loop is used to track the command of angle of attack (sideslip angle, roll angle) rapidly. Finally, the stability of the designed closed-loop system is proved by Lyapunov method. The thrust vector control missile model designed by this method is simulated numerically, and the results show that the designed missile attitude has good response characteristics.
KW - ADRC
KW - Attitude control system
KW - Lyapunov method
KW - Thrust vector
UR - http://www.scopus.com/inward/record.url?scp=85072969084&partnerID=8YFLogxK
U2 - 10.1109/CCOMS.2019.8821773
DO - 10.1109/CCOMS.2019.8821773
M3 - 会议稿件
AN - SCOPUS:85072969084
T3 - 2019 IEEE 4th International Conference on Computer and Communication Systems, ICCCS 2019
SP - 707
EP - 711
BT - 2019 IEEE 4th International Conference on Computer and Communication Systems, ICCCS 2019
PB - Institute of Electrical and Electronics Engineers Inc.
T2 - 4th IEEE International Conference on Computer and Communication Systems, ICCCS 2019
Y2 - 23 February 2019 through 25 February 2019
ER -