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              高超聲速飛行器指定時間時變高增益反饋跟蹤控制

              張康康 周彬 蔡光斌 侯明哲

              張康康, 周彬, 蔡光斌, 侯明哲. 高超聲速飛行器指定時間時變高增益反饋跟蹤控制. 自動化學報, 2024, 50(6): 1001?1009 doi: 10.16383/j.aas.c210895
              引用本文: 張康康, 周彬, 蔡光斌, 侯明哲. 高超聲速飛行器指定時間時變高增益反饋跟蹤控制. 自動化學報, 2024, 50(6): 1001?1009 doi: 10.16383/j.aas.c210895
              Zhang Kang-Kang, Zhou Bin, Cai Guang-Bin, Hou Ming-Zhe. Prescribed-time tracking control of hypersonic vehicles by time-varying high-gain feedback. Acta Automatica Sinica, 2024, 50(6): 1001?1009 doi: 10.16383/j.aas.c210895
              Citation: Zhang Kang-Kang, Zhou Bin, Cai Guang-Bin, Hou Ming-Zhe. Prescribed-time tracking control of hypersonic vehicles by time-varying high-gain feedback. Acta Automatica Sinica, 2024, 50(6): 1001?1009 doi: 10.16383/j.aas.c210895

              高超聲速飛行器指定時間時變高增益反饋跟蹤控制

              doi: 10.16383/j.aas.c210895
              基金項目: 國家杰出青年科學基金(62125303), 國家自然科學基金委基礎科學中心項目(62188101), 國家自然科學基金(61773387, 62073096)資助
              詳細信息
                作者簡介:

                張康康:哈爾濱工業大學控制科學與工程博士研究生.主要研究方向為有限時間控制, 非線性控制和飛行器控制. E-mail: kangkang_kkz@163.com

                周彬:哈爾濱工業大學控制理論與制導技術研究中心教授. 主要研究方向為約束控制, 時滯系統, 時變系統, 非線性控制, 多智能體系統和飛行器控制. 曾獲全國優秀博士學位論文獎和國家杰出青年科學基金資助. 目前擔任Automatica等雜志的編委. 本文通信作者. E-mail: binzhou@hit.edu.cn

                蔡光斌:博士, 火箭軍工程大學導彈工程學院副教授, 陜西省優秀博士學位論文獲得者. 主要研究方向為新型飛行器制導與控制, 快速軌跡優化, 智能控制理論及應用. E-mail: cgb0712@163.com

                侯明哲:中國自動化學會會員, 《美國數學評論》評論員. 2011年獲哈爾濱工業大學控制科學與工程博士學位. 主要研究方向為非線性控制和飛行器控制. 發表期刊論文40余篇和出版專著一部. E-mail: hithyt@hit.edu.cn

              Prescribed-time Tracking Control of Hypersonic Vehicles by Time-varying High-gain Feedback

              Funds: Supported by National Science Fund for Distinguished Young Scholars (62125303), Science Center Program of National Natural Science Foundation of China (62188101), and National Natural Science Foundation of China (61773387, 62073096)
              More Information
                Author Bio:

                ZHANG Kang-Kang Ph.D. candidate at the Department of Control Science and Engineering, Harbin Institute of Technology. His research interest covers finite-time control, nonlinear control, and aircraft control

                ZHOU Bin Professor at the Center for Control Theory and Guidance Technology, Harbin Institute of Technology. His research interest covers constrained control, time-delay systems, time-varying systems, nonlinear control, multi-agent systems, and aircraft control. He received the “National Excellent Doctoral Dissertation Award” in 2012 from the Academic Degrees Committee of the State Council and the Ministry of Education of China and is supported by the National Science Fund for Distinguished Young Scholars. He is currently an Associate Editor of Automatica. Corresponding author of this paper

                CAI Guang-Bin received his Ph.D. degree in control science and engineering in 2012 from Rocket Force University of Engineering, and got the reward-gainer of the excellent doctor degree dissertation in Shaanxi Province. He is an associate professor at the College of Missile Engineering, Rocket Force University of Engineering. His research interest covers guidance and control theory and its applications of aircrafts

                HOU Ming-Zhe Professor at the Center for Control Theory and Guidance Technology, Harbin Institute of Technology. He is a member of Chinese Association of Automation, and a reviewer for American Mathematical Review. He received his Ph.D. degree in control science and engineering from Harbin Institute of Technology in 2011. His research interest covers nonlinear control and aircraft control, and he has published over 40 journal papers and a monograph

              • 摘要: 研究了高超聲速飛行器控制通道存在未知環境干擾時的指定時間跟蹤控制問題. 基于高超聲速飛行器的輸入輸出線性化模型, 借助參量 Lyapunov方程的一些性質, 設計一種光滑、有界的時變高增益控制律. 相比于現有的高超聲速飛行器有限/固定時間控制方法, 該算法不會出現抖振現象, 同時收斂時間不依賴于初始狀態且可以事先設定. 當高超聲速飛行器存在未知的有界環境匹配干擾時, 該控制器能使高度和速度在指定時間跟蹤上參考信號. 仿真結果驗證了方法的有效性.
              • 圖  1  速度、飛行航跡角、高度和攻角變化曲線

                Fig.  1  The curves of changes in velocity, flight path angle, altitude and angle of attack

                圖  2  俯仰角速率、發動機節流閥開度及其導數變化曲線

                Fig.  2  The curves of changes in pitch rate, engine throttle setting and their time-derivative

                圖  3  控制輸入和推力變化曲線(1 Ibf = 4.45 N)

                Fig.  3  The curves of changes in control input and thrust (1 Ibf = 4.45 N)

                圖  4  速度誤差及其導數變化曲線

                Fig.  4  The curves of changes in velocity errors and their time-derivatives

                圖  5  高度誤差及其導數變化曲線

                Fig.  5  The curves of changes in altitude errors and their time-derivatives

                表  1  高超聲速飛行器參數以及飛行環境參數

                Table  1  The parameters of the hypersonic aircraft and the flight environment

                模型參數 符號
                質量 $m$ 9 375 slugs
                地球半徑 $ R_{e}$ 20 903 500 ft
                參考面積 $S$ 3 603 ft2
                平均氣動弦長 $\bar{c}$ 80
                升降副翼弦長 $ c_{e} $ 0.029 2
                繞$ y $軸的轉動慣量 $ I_{yy} $$ 7 \times 10 ^{\rm{6}}$ slugs ft2
                空氣密度 $\rho$ $2.432\,5 \times 10 ^{\rm{-5} }$ slugs/ft3
                重力常數 $\mu $ $1.39 \times 10 ^{\rm{16}} $ ${\rm{ft}}^{\rm{3}}/ \text{s} ^{\rm{2}} $
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                        • 收稿日期:  2021-01-15
                        • 錄用日期:  2022-03-01
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