Adaptive tracking control of flapping wing micro‐air vehicles with averaging theory. Issue 1 (5th April 2018)

• Record Type: Journal Article
• Authors: Qian, Chen; Fang, Yongchun
• Is Part Of: CAAI transactions on intelligence technology. Volume 3:Issue 1(2018)
• Page Start: 18
• Page End: 27
• Publication Date: 2018-04-05
• Subjects: aerodynamics -- attitude control -- remotely operated vehicles -- adaptive control -- aerospace components -- robust control -- closed loop systems -- control system synthesis -- nonlinear control systems -- feedback -- microrobots -- autonomous aerial vehicles; adaptive tracking control -- averaging theory -- moving averaging filter -- averaged states -- tracking control problem -- outer loop controller -- constrained thrust -- average estimation -- tracking differentiator -- inner loop -- hybrid attitude tracking controller -- closed‐loop system -- control torques -- flapping wing microair vehicles -- yaw angle -- input constraints; C1180 Optimisation techniques -- C1310 Control system analysis and synthesis methods -- C1320 Stability in control theory -- C1340E Self‐adjusting control systems -- C1340K Nonlinear control systems -- C3120C Spatial variables control -- C3360L Aerospace control -- C3390C Mobile robots -- C3390T Telerobotics; Artificial intelligence -- Periodicals; Computer science -- Periodicals; Artificial intelligence; Computer science; Electronic journals; Periodicals; 006.305
• DOI: 10.1049/trit.2018.0007
• Languages: English
• ISSNs: 2468-6557

Abstract

Abstract : An input constrained adaptive tracking controller is designed for flapping micro aerial vehicles, wherein the moving averaging filter is adopted to estimate the averaged states of the system. Specifically, in the outer loop controller, an observer is constructed to estimate the disturbances within the system. Moreover, the constrained thrust is designed to keep the frequency in a proper region so as to meet the requirement of average estimation. Then, a tracking differentiator is used to provide trackable trajectories for the inner loop. Subsequently, a new quaternion‐based hybrid attitude tracking controller is designed which successfully deals with high‐frequency noises and avoids possible chattering. As supported by mathematical analysis, the proposed control strategy guarantees the uniform ultimate boundedness of the closed‐loop system, and it keeps the control torques within the permitted range to meet the application requirement. At last, numerical simulations are carried out to support the validity of the proposed controller, whose results are satisfactory even when the thrust and torques are saturated.