Active Fault Tolerant Control on Multi-rotor UAVs using ELM-based Neuro-Fuzzy System

Thanaraj, T; Ng, Bing Feng; Low, Kin Huat

doi:10.2514/6.2022-3510

Cited by 3 publications

(2 citation statements)

References 27 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Among recent works on the fault-tolerant control (FTC) of flight vehicles, both fixedwing aircrafts [12][13][14][15][16][17][18] and rotorcrafts [19][20][21][22][23][24][25][26][27][28] have been taken into account. In [12], FTC systems are presented for vectored thrust aircraft with a robust fault detection and identification mechanism.…”

Section: Introductionmentioning

confidence: 99%

“…With respect to rotorcrafts, attention is paid mainly to the configuration of conventional helicopters [19], quadrotors [20][21][22][23][26][27][28], octorotors [25], and rarely to novel configurations such as hybrid helicopters [24]. Using a backstepping baseline controller to improve performance under healthy situations, a robust adaptive compensation FTC system is presented in [19].…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Hybrid Adaptive Control for Tiltrotor Aircraft Flight Control Law Reconfiguration

Wen,

Song,

Wang

et al. 2023

Aerospace

View full text Add to dashboard Cite

Tiltrotor aircrafts have both fixed-wing control surfaces and helicopter rotors for attitude control. The redundancy of control surfaces provides the possibility for the control system to reconfigure the control law when actuator faults occur during flight. Possible actuator faults have been classified into two categories: predictable and unpredictable faults, and a different strategy has been adopted to deal with each kind of fault. Firstly, the predictable faults are handled by a multiple-model switching adaptive scheme. These kinds of faults are modeled, and their corresponding controllers are derived offline. Secondly, since the degree of drop in aerodynamic effectiveness cannot be predicted a priori, unpredictable faults are handled by a simple adaptive control scheme, to force the plant with faults to track the prescribed reference model. The presented methodology has been verified by nonlinear full-envelope flight simulation for both categories of actuator faults. The predictable fault is represented by the elevator floating. Elevator damage causing an aerodynamic effectiveness drop by 80% is chosen as the example of unpredictable fault. Both faults are simulated at the late stage of the tiltrotor conversion mode. Results show that the presented strategy of reconfiguration is able to detect the fault rapidly and stabilize the aircraft when a fault occurs, while the aircraft motion diverges without the reconfiguration scheme. The aircraft also presents a relatively good performance under controller reconfiguration with a well-tracked conversion path.

show abstract