Temat: actuator faults - Katalog OPAC zbiorów

Skocz do pozycji: 1.

Tytuł:: Pitch and yaw motion control of 2 DoF helicopter subjected to faults using sliding-mode control
Autorzy:: Raghappriya, M.
Kanthalakshmi, S.
Powiązania:: https://bibliotekanauki.pl/articles/2134893.pdf
Data publikacji:: 2022
Wydawca:: Polska Akademia Nauk. Czytelnia Czasopism PAN
Tematy:: fault tolerant control
sliding mode control
reaching law
super-twisting
sensor
actuator faults
component faults
Opis:: This paper presents a fault-tolerant control scheme for a 2 DOF helicopter. The 2 DOF helicopter is a higher-order multi-input multi-output system featuring non-linearity, cross-coupling, and unstable behaviour. The impact of sensor, actuator, and component faults on such highly complex systems is enormous. This work employs sliding mode control, which is based on reaching and super-twisting laws, to handle the problem of fault control. Simulation tests are carried out to show the effectiveness of the algorithms. Various performance metrics are analyzed and the results show SMC based on super-twisting law provides better control with less chattering. The stability of the closed-loop system is mathematically assured, in the presence of faults, which is a key contribution of this research.
Źródło:: Archives of Control Sciences; 2022, 32, 2; 359--381
1230-2384
Pojawia się w:: Archives of Control Sciences
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

Tytuł:: Reconfigurability analysis for reliable fault-tolerant control design
Autorzy:: Khelassi, A.
Theilliol, D.
Weber, P.
Powiązania:: https://bibliotekanauki.pl/articles/907596.pdf
Data publikacji:: 2011
Wydawca:: Uniwersytet Zielonogórski. Oficyna Wydawnicza
Tematy:: sterowanie tolerujące uszkodzenia
rekonfigurowalność
niezawodność
fault tolerant control system
reconfigurability
reliability
actuator faults
Opis:: In this paper the integration of reliability evaluation in reconfigurability analysis of a fault-tolerant control system is considered. The aim of this work is to contribute to reliable fault-tolerant control design. The admissibility of control reconfigurability is analyzed with respect to reliability requirements. This analysis shows the relationship between reliability and control reconfigurability defined generally through Gramian controllability. An admissible solution for reconfigurability is proposed according to reliability evaluation based on energy consumption under degraded functional conditions. The proposed study is illustrated with a flight control application.
Źródło:: International Journal of Applied Mathematics and Computer Science; 2011, 21, 3; 431-439
1641-876X
2083-8492
Pojawia się w:: International Journal of Applied Mathematics and Computer Science
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

Tytuł:: Detection and identification of loss of efficiency faults of flight actuators
Autorzy:: Ossmann, D.
Varga, A.
Powiązania:: https://bibliotekanauki.pl/articles/330772.pdf
Data publikacji:: 2015
Wydawca:: Uniwersytet Zielonogórski. Oficyna Wydawnicza
Tematy:: aerospace engineering
fault detection
fault diagnosis
loss of efficiency type of faults
flight actuator faults
inżynieria lotnicza
detekcja uszkodzeń
diagnostyka uszkodzeń
Opis:: We propose linear parameter-varying (LPV) model-based approaches to the synthesis of robust fault detection and diagnosis (FDD) systems for loss of efficiency (LOE) faults of flight actuators. The proposed methods are applicable to several types of parametric (or multiplicative) LOE faults such as actuator disconnection, surface damage, actuator power loss or stall loads. For the detection of these parametric faults, advanced LPV-model detection techniques are proposed, which implicitly provide fault identification information. Fast detection of intermittent stall loads (seen as nuisances, rather than faults) is important in enhancing the performance of various fault detection schemes dealing with large input signals. For this case, a dedicated fast identification algorithm is devised. The developed FDD systems are tested on a nonlinear actuator model which is implemented in a full nonlinear aircraft simulation model. This enables the validation of the FDD system’s detection and identification characteristics under realistic conditions.
Źródło:: International Journal of Applied Mathematics and Computer Science; 2015, 25, 1; 53-63
1641-876X
2083-8492
Pojawia się w:: International Journal of Applied Mathematics and Computer Science
Dostawca treści:: Biblioteka Nauki

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