High angle of attack control system design based on ADRC and fuzzy logic

被引：0

作者：

Ma, Yue-Yue ^{[1
]}

Tang, Sheng-Jing ^{[1
]}

Guo, Jie ^{[1
]}

Shi, Jiao ^{[2
]}

机构：

[1] Key Laboratory of Dynamics and Control of Flight Vehicle, School of Aerospace Engineering, Beijing Institute of Technology

[2] China Academy of Launch Vehicle Technology

来源：

Xi Tong Gong Cheng Yu Dian Zi Ji Shu/Systems Engineering and Electronics | 2013年 / 35卷 / 08期

关键词：

Active disturbance rejection control (ADRC); Air-to-air missile; Blended control; Fuzzy logic; High angle of attack;

D O I：

10.3969/j.issn.1001-506X.2013.08.21

中图分类号：

学科分类号：

摘要：

A missile autopilot design method based on active disturbance rejection control (ADRC) and fuzzy logic is proposed for agile turn of air-to-air missile with reaction-jet/aerodynamic blended control system. The scheme separates the missile pitching channel into angle of attack loop and pitching angular velocity loop. Controllers are designed by the ADRC respectively and combined to the whole control loop in tandem. Then a virtual control value is decided by the angle of attack command and allocated to aerodynamic deflectors and reaction jet control system. Finally, the feedback gains of the ADRC controller are adjusted in real time by fuzzy control. Simulation results indicate that the proposed strategy can track the high angle of attack command accurately, and it is applicable to finish agile turn at high angle of attack.

引用

页码：1711 / 1716

页数：5

共 17 条

[1]

Wise K.A., Broy D.J., Agile missile dynamics and control, Journal of Guidance, Control, and Dynamics, 21, 3, pp. 441-449, (1998)

[2]

Innocenti M., Thukral A., Simultaneous reaction jet and aerodynamic control of missile systems, (1993)

[3]

Thukral A., Innocenti M., A sliding mode missile pitch autopilot synthesis for high angle of attack maneuvering, IEEE Trans. on Control Systems Technology, 6, 3, pp. 359-371, (1998)

[4]

Ratliff R.T., Ramsey J.A., Wise K.A., Advances in agile maneuvering for high performance munitions, Proc. of the American Institute of Aeronautics and Astronautics Guidance, Navigation, and Control Conference, pp. 412-419, (2009)

[5]

Kang S., Kim H.J., Lee J.I., Et al., Roll-pitch-yaw integrated robust autopilot design for a high angle-of-attack missile, Journal of Guidance, Control, and Dynamics, 32, 5, pp. 1622-1628, (2009)

[6]

Kim K.U., Kang S., Kim H.J., Et al., Realtime agile-turn guidance and control for an air-to-air missile, Proc. of the American Institute of Aeronautics and Astronautics Guidance, Navigation, and Control Conference, pp. 2207-2225, (2010)

[7]

Wang Y.H., Yao Y., Bi Y.T., Lateral thrust and aerodynamics blended control system design based on auto disturbance rejection controller, Journal of Astronautics, 30, 4, pp. 1544-1550, (2009)

[8]

Bi Y.T., He F.H., Yao Y., Design of blended lateral thrust and aerodynamic surface control strategy for agile missile, Journal of Jilin University (Engineering and Technology Edition), 41, 2, pp. 590-596, (2011)

[9]

Li Z., Wei M.Y., Zhou D., Et al., Technology of Lateral Thrust and Aerodynamics Blended Control for Anti-Air Missile, pp. 2-3, (2012)

[10]

Tian Y., Chen J., Zhang R., Design of three-dimensional guidance law based on extended state observer for hit-to-kill interceptors, Proc. of the IEEE International Conference on Automation and Logistics, pp. 73-78, (2009)

← 1 2 →