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ACTA AERONAUTICAET ASTRONAUTICA SINICA >

2025 , Vol. 46 >Issue 24: 331840 - 331840

DOI: https://doi.org/10.7527/S1000-6893.2025.31840

Electronics and Electrical Engineering and Control

Prescribed performance anti-swing control for wing rotation process of UAV towed aerial recovery

  • Guocheng YAN ,
  • Honglun WANG ,
  • Yanxiang WANG ,
  • Yuebin LUN ,
  • Junfan ZHU
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  • 1.School of Automation Science and Electrical Engineering，Beihang University，Beijing 100191，China
    2.Science and Technology on Aircraft Control Laboratory，Beihang University，Beijing 100191，China
    3.Shenyuan Honors College，Beihang University，Beijing 100191，China
    4.Beijing Institute of Astronautical Systems Engineering，Beijing 100076，China
E-mail： wang_hl_12@126.com

Received date: 2025-01-23

  Revised date: 2025-05-07

  Accepted date: 2025-07-25

  Online published: 2025-08-11

Supported by

National Natural Science Foundation of China(62173022)

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Abstract

To address the swing suppression control problem for wing rotation process of UAV towed aerial recovery assembly， an anti-swing control method based on appointed-time preset performance control is proposed. Firstly， the characteristics of the aerial recovery assembly are analyzed. A six degree of freedom nonlinear model of the aerial recovery assembly is established using the Newton-Euler method， the additional forces and moments caused by the wing rotation are analyzed， and additional force and additional moment models containing the wing rotation angle are established. Secondly， in response to the strong nonlinear characteristics of aerodynamic force and aerodynamic torque changes during wing rotation， this paper adopts unsteady computational fluid dynamics methods to calculate the aerodynamic force and moments during this process， and establishes aerodynamic force and aerodynamic moments models containing the wing rotation angle. On this basis， the six degrees of freedom nonlinear models are transformed to affine nonlinear form， and a composite anti-swing control method integrating a non-constraining force vector sum direction feedforward compensation controller with an appointed-time prescribed performance control feedback controller is proposed. A simulation is carried out and the results show that， the maximum longitudinal displacement of the proposed method is 0.16 m， and the maximum lateral displacement is 0.18 m， demonstrating significant advantages of the proposed method.

Key words： Unmanned aerial vehicle (UAV); aerial recovery; rotary wing; dynamics modeling; prescribed performance

Cite this article

Guocheng YAN , Honglun WANG , Yanxiang WANG , Yuebin LUN , Junfan ZHU . Prescribed performance anti-swing control for wing rotation process of UAV towed aerial recovery[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2025 , 46(24) : 331840 -331840 . DOI: 10.7527/S1000-6893.2025.31840

References

[1] 王宏伦， 王延祥， 刘一恒. 基于轨迹映射的无人机拖曳式空中回收轨迹优化［J］. 航空学报， 2023， 44（20）： 628775.
  WANG H L， WANG Y X， LIU Y H. Recovery trajectory optimization for UAV towed aerial recovery based on trajectory mapping［J］. Acta Aeronautica et Astronautica Sinica， 2023， 44（20）： 628775 （in Chinese）.
[2] 苏子康， 陈海通， 李春涛， 等. 非匹配包线下无人机空基回收拖曳系统协调运动规划［J］. 航空学报， 2023， 44（10）： 327377.
  SU Z K， CHEN H T， LI C T， et al. Coordinating motion planning for towed cable system in UAV aerial recovery with unmatched envelope［J］. Acta Aeronautica et Astronautica Sinica， 2023， 44（10）： 327377 （in Chinese）.
[3] WANG Y X， WANG H L， LIU B L， et al. A visual navigation framework for the aerial recovery of UAVs［J］. IEEE Transactions on Instrumentation and Measurement， 2021， 70： 5019713.
[4] CHU L L， LI Q， GU F， et al. Design， modeling， and control of morphing aircraft： A review［J］. Chinese Journal of Aeronautics， 2022， 35（5）： 220-246.
[5] 杨贯通， 唐胜景， 赵林东， 等. 变后掠变展长飞行器动力学建模与动态响应分析［J］. 兵工学报， 2014， 35（1）： 102-107.
  YANG G T， TANG S J， ZHAO L D， et al. Dynamic modeling and response of a morphing UAV with variable sweep and variable span［J］. Acta Armamentarii， 2014， 35（1）： 102-107 （in Chinese）.
[6] 马航， 宋笔锋， 裴扬， 等. 非对称变后掠柔性后缘飞机滚转控制分配研究［J］. 系统工程与电子技术， 2019， 41（5）： 1094-1102.
  MA H， SONG B F， PEI Y， et al. Research on roll control allocation of asymmetric sweep aircraft with flexible trailing edge［J］. Systems Engineering and Electronics， 2019， 41（5）： 1094-1102 （in Chinese）.
[7] 李勇， 马绍贤， 贺旭照， 等. 斜置机翼变构飞行器纵向操稳特性分析［J］. 飞行力学， 2024， 42（1）： 55-61.
  LI Y， MA S X， HE X Z， et al. Analysis of longitudinal controllability and stability of oblique wing morphing aircraft［J］. Flight Dynamics， 2024， 42（1）： 55-61 （in Chinese）.
[8] 秋路， 高正红， 刘艳. 斜置翼布局飞机的飞行动力学模型研究［J］. 飞行力学， 2015， 33（2）： 106-110.
  QIU L， GAO Z H， LIU Y. Research on oblique wing aircraft’s flight dynamics model［J］. Flight Dynamics， 2015， 33（2）： 106-110 （in Chinese）.
[9] LIU Y H， WANG H L， FAN J X， et al. Trajectory stabilization control for aerial recovery of cable-drogue-UAV assembly［J］. Nonlinear Dynamics， 2021， 105（4）： 3191-3210.
[10] PARANCHEERIVILAKKATHIL M S， PILAKKADAN J S， AJAJ R M， et al. A review of control strategies used for morphing aircraft applications［J］. Chinese Journal of Aeronautics， 2024， 37（4）： 436-463.
[11] DE PONTI T M L， SMEUR E J J， REMES B W D. Incremental nonlinear dynamic inversion controller for a variable skew quad plane［C］∥2023 International Conference on Unmanned Aircraft Systems （ICUAS）. Piscataway： IEEE Press， 2023： 241-248.
[12] 宋慧心， 金磊. 折叠翼飞行器的动力学建模与稳定控制［J］. 力学学报， 2020， 52（6）： 1548-1559.
  SONG H X， JIN L. Dynamic modeling and stability control of folding wing aircraft［J］. Chinese Journal of Theoretical and Applied Mechanics， 2020， 52（6）： 1548-1559 （in Chinese）.
[13] GONG L G， WANG Q， DONG C Y. Disturbance rejection control of morphing aircraft based on switched nonlinear systems［J］. Nonlinear Dynamics， 2019， 96（2）： 975-995.
[14] TONG L， JI H. Multi-body dynamic modelling and flight control for an asymmetric variable sweep morphing UAV［J］. The Aeronautical Journal， 2014， 118（1204）： 683-706.
[15] 徐悦， 韩忠华， 尤延铖， 等. 新一代绿色超声速民机的发展现状与挑战［J］. 科学通报， 2020， 65（S 1）： 127-133.
  XU Y， HAN Z H， YOU Y C， et al. Development status and challenges of a new generation of green supersonic civil aircraft［J］. Chinese Science Bulletin， 2020， 65（S 1）： 127-133.
[16] 甘文彪， 左振杰， 向锦武， 等. 飞行器旋转翼折展过程动稳定性研究进展［J］. 北京航空航天大学学报， 2024， 50（4）： 1053-1064.
  GAN W B， ZUO Z J， XIANG J W， et al. Research progress on dynamic stability of rotating variant wing opening and closing process for aircraft［J］. Journal of Beijing University of Aeronautics and Astronautics， 2024， 50（4）： 1053-1064 （in Chinese）.
[17] 曹承钰， 李繁飙， 廖宇新， 等. 高超声速变外形飞行器建模与固定时间预设性能控制［J］. 自动化学报， 2024， 50（3）： 486-504.
  CAO C Y， LI F B， LIAO Y X， et al. Modeling and fixed-time prescribed performance control for hypersonic morphing vehicle［J］. Acta Automatica Sinica， 2024， 50（3）： 486-504 （in Chinese）.
[18] WANG Y X， WANG H L， LIU Y H， et al. Performance-guaranteed neuroadaptive docking control for UAV aerial recovery under carrier maneuvering flight［J］. IEEE Transactions on Aerospace and Electronic Systems， 2023， 59（6）： 8355-8368.
[19] 苏子康， 陈嘉， 李雪兵， 等. 四倾转旋翼无人机过渡飞行位姿协调控制［J/OL］. 北京航空航天大学学报， （2024-01-18）［2025-01-23］. .
  SU Z K， CHEN J， LI X B， et al. Coordinated control of transition flight position and attitude for quad tilt-rotor UAV［J/OL］. Journal of Beijing University of Aeronautics and Astronautics， （2024-01-18）［2025-01-23］. （in Chinese）.
[20] HAN J Q. From PID to active disturbance rejection control［J］. IEEE Transactions on Industrial Electronics， 2009， 56（3）： 900-906.
[21] CARTER R， KEETER T M， CALHOUN P. Airborne recovery of the X-61A gremlin unmanned aircraft： AIAA-2024-0570［R］. Reston： AIAA， 2024.
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Total visits: 6658907 Today visits: 1341