Modeling of a fault-tolerant electromechanical actuation system for helicopters using Modelica

2012 ◽  
Author(s):  
S. Seemann ◽  
M. Rottach ◽  
S. Bozhko ◽  
C. Schlegel
Keyword(s):  
Fault Tolerant ◽  
Actuation System ◽  
Electromechanical Actuation

Fault Tolerant Scheme of Switched Reluctance Machines for the Electro-Mechanical Actuation Systems

2013 ◽  
Vol 372 ◽  
pp. 608-611
Author(s):  
Xiao Yuan Chen
Keyword(s):  
Fault Tolerant ◽  
Element Model ◽  
Switched Reluctance ◽  
Advantages And Disadvantages ◽  
Dual Channel ◽  
Actuation System ◽  
Switched Reluctance Machines ◽  
Actuation Systems ◽  
Electromechanical Actuation ◽  
Mechanical Actuation

As switched reluctance machines (SRM) generally offer a simple and robust design, they are very suitable for electromechanical actuation systems which need to be actuated by fault tolerant drives. This paper investigates dual-channel, dual-redundancy, lacking phase schemes of SRM guaranteeing fault tolerance and the corresponding control systems in detail are compared to point out the advantages and disadvantages of them., a new lacking phase scheme for 12/8 SRM is proposed and the finite element model based on field-circuit coupling is established, results indicate that this scheme have superior fault tolerant performance and suit tasks in electro-mechanical actuation system of aerospace environments.

scholarly journals Analysis and Design of a Leading Edge with Morphing Capabilities for the Wing of a Regional Aircraft—Gapless Chord- and Camber-Increase for High-Lift Performance

2021 ◽  
Vol 11 (6) ◽  
pp. 2752
Author(s):  
Conchin Contell Asins ◽  
Volker Landersheim ◽  
Dominik Laveuve ◽  
Seiji Adachi ◽  
Michael May ◽  
...  
Keyword(s):  
Leading Edge ◽  
Bird Strike ◽  
High Lift ◽  
Analysis And Design ◽  
Actuation System ◽  
Aerodynamic Properties ◽  
Reinforced Plastic ◽  
Stall Angle ◽  
Carbon Fibre Reinforced Plastic ◽  
Electromechanical Actuation

In order to contribute to achieving noise and emission reduction goals, Fraunhofer and Airbus deal with the development of a morphing leading edge (MLE) as a high lift device for aircraft. Within the European research program “Clean Sky 2”, a morphing leading edge with gapless chord- and camber-increase for high-lift performance was developed. The MLE is able to morph into two different aerofoils—one for cruise and one for take-off/landing, the latter increasing lift and stall angle over the former. The shape flexibility is realised by a carbon fibre reinforced plastic (CFRP) skin optimised for bending and a sliding contact at the bottom. The material is selected in terms of type, thickness, and lay-up including ply-wise fibre orientation based on numerical simulation and material tests. The MLE is driven by an internal electromechanical actuation system. Load introduction into the skin is realised by span-wise stringers, which require specific stiffness and thermal expansion properties for this task. To avoid the penetration of a bird into the front spar of the wing in case of bird strike, a bird strike protection structure is proposed and analysed. In this paper, the designed MLE including aerodynamic properties, composite skin structure, actuation system, and bird strike behaviour is described and analysed.

Active fault-tolerant control for vertical tail damaged aircraft with dissimilar redundant actuation system using integral sliding mode control

2018 ◽  
Vol 233 (7) ◽  
pp. 2361-2378 ◽  
Author(s):  
Salman Ijaz ◽  
Mirza T Hamayun ◽  
Lin Yan ◽  
Cun Shi
Keyword(s):  
Actuator Saturation ◽  
Fault Tolerant ◽  
Sliding Mode ◽  
Fault Tolerant Control ◽  
Fault Estimation ◽  
Redundant Actuation ◽  
Severe Damage ◽  
Integral Sliding Mode ◽  
Actuation System ◽  
Electrohydraulic Actuator

The research about the dissimilar redundant actuation system has indicated the potential fault-tolerant capability in modern aircraft. This paper proposed a new design methodology to achieve fault-tolerant control of an aircraft equipped with dissimilar actuators and is suffered from vertical tail damage. The proposed design is based on the concept of online control allocation to redistribute the control signals among healthy actuators and integral sliding mode controller is designed to achieve the closed-loop stability in the presence of both component and actuator faults. To cope with severe damage condition, the aircraft is equipped with dissimilar actuators (hydraulic and electrohydraulic actuators). In this paper, the performance degradation due to slower dynamics of electrohydraulic actuator is taken in account. Therefore, the feed-forward compensator is designed for electrohydraulic actuator based on fractional-order control strategy. In case of failure of hydraulic actuator subject to severe damage of vertical tail, an active switching mechanism is developed based on the information of fault estimation unit. Additionally, a severe type of actuator failure so-called actuator saturation or actuator lock in place is also taken into account in this work. The proposed strategy is compared with the existing control strategies in the literature. Simulation results indicate the dominant performance of the proposed scheme. Moreover, the proposed controller is found robust with a certain level of mismatch between the actuator effectiveness level and its estimate.

Adaptive fault tolerant control of dissimilar redundant actuation system of civil aircraft based on integral sliding mode control strategy

2019 ◽  
Vol 41 (13) ◽  
pp. 3756-3768 ◽  
Author(s):  
Salman Ijaz ◽  
Mirza Tariq Hamayun ◽  
Lin Yan ◽  
Hamdoon Ijaz ◽  
Cun Shi
Keyword(s):  
Sliding Mode Control ◽  
Control Strategy ◽  
Fault Tolerant ◽  
Sliding Mode ◽  
Fault Tolerant Control ◽  
Redundant Actuation ◽  
Integral Sliding Mode Control ◽  
Integral Sliding Mode ◽  
Actuation System ◽  
Civil Aircraft

In modern aircraft, the dissimilar redundant actuation system is used to resolve the actuator failure issues due to the common cause, thus increasing the system reliability. This paper proposes an adaptive integral sliding mode fault tolerant control strategy to deal with actuator fault/failure in the dissimilar redundant actuation system of civil aircraft. To cope with the unknown actuator faults, the adaptive integral sliding mode controller is designed where the modulation gain is made adaptive to the fault. To deal with the complete failure of certain actuator, the integral sliding mode control is integrated with control allocation scheme and distribute the control input signals to the redundant actuators. The performance of the proposed scheme is tested on the nonlinear model of dissimilar redundant actuation system, where the effect of external airload is accounted during simulations. The effectiveness of the proposed scheme is validated by comparing the simulations with the existing literature.

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