A Fault Tolerant Direct Control Allocation Scheme with Integral Sliding Modes

Hamayun, Mirza Tariq; Edwards, Christopher; Alwi, Halim

doi:10.1007/978-3-319-32238-4_4

Cited by 5 publications

(4 citation statements)

References 11 publications

(22 reference statements)

Supporting

Mentioning

Contrasting

Order By: Relevance

“…13,14 Moreover, the various modifications have been made on conventional SMC to address the inherent problem of chattering in the design. They are integral SMC, 15,16 adaptive SMC, 17 nonsingular terminal SMC, 18 and higher-order SMC. 19,20 These controllers ensure zero steady-state error and finite time for reaching to the sliding surface.…”

Section: Introductionmentioning

confidence: 99%

Design of sliding mode flight control system for a flexible aircraft

Mohamed

Gopakumar²

2021

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

The evolution of large transport aircraft is characterized by longer fuselages and larger wingspans, while efforts to decrease the structural weight reduce the structural stiffness. Both effects lead to more flexible aircraft structures with significant aeroelastic coupling between flight mechanics and structural dynamics, especially at high speed, high altitude cruise. The lesser frequency separation between rigid body and flexible modes of flexible aircraft results in a stronger interaction between the flight control system and its structural modes, with higher flexibility effects on aircraft dynamics. Therefore, the design of a flight control law based on the assumption that the aircraft dynamics are rigid is no longer valid for the flexible aircraft. This paper focuses on the design of a flight control system for flexible aircraft described in terms of a rigid body mode and four flexible body modes and whose parameters are assumed to be varying. In this paper, a conditional integral based sliding mode control (SMC) is used for robust tracking control of the pitch angle of the flexible aircraft. The performance of the proposed nonlinear flight control system has been shown through the numerical simulations of the flexible aircraft. Good transient and steady-state performance of a control system are also ensured without suffering from the drawback of control chattering in SMC.

show abstract

Section: Introductionmentioning

confidence: 99%

Design of sliding mode flight control system for a flexible aircraft

Mohamed

Gopakumar²

2021

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

show abstract

“…Works which have considered the use of robust control in conjunction with CA include [19] and [20]. In [19] and [20],

H_{\infty}

control and back‐stepping are used, respectively, whereas SMC is used in [3] and [21] for FTC of aerospace systems. Higher‐order SMCs (HOSMCs) have also been considered for FTC.…”

Section: Introductionmentioning

confidence: 99%

Robust fault tolerant control allocation for a modern over‐actuated commercial aircraft

Vile

Alwi

Edwards

2020

IET Control Theory & Appl

Self Cite

View full text Add to dashboard Cite

This paper presents a novel form of control allocation, designed within a sliding mode framework, for the fault tolerant control of over‐actuated systems. The control allocation is designed in such a way as to allow a subset of the actuators to remain inactive under nominal fault‐free conditions. In the event that the active set of actuators becomes unable to provide the desired performance, an adaption process takes place which allows the inactive actuators to compensate. A computationally light gradient descent algorithm is proposed to govern the adaption which guarantees that, if possible, actuator saturation is avoided and system performance is maintained, even in the event of severe actuator faults/failures. Rigorous conditions are derived, in terms of the faults/failures, uncertainties in fault reconstruction information and the adaptive process, which ensure sliding occurs in a finite time and that the resulting motion is stable. To demonstrate the effectiveness of the control scheme, a high‐fidelity blended wing body aircraft model is also proposed in this paper; this particular configuration of aircraft is nominally unstable, with poor control authority and a large amount of redundancy, making it a suitable candidate for testing reconfigurable fault tolerant control laws in the presence of input constraints.

show abstract

“…Alwi (2008) and Alwi and Edwards (2008) proposed a fault tolerant control strategy of sliding modes with on-line CA, and used small gain theory to ensure the sliding mode dynamics with CA will be stable when faults happened. The theory was improved by Hamayun (2013) and Hamayun et al (2010) using integral sliding mode fault tolerant control. Ijaz et al (2019) proposed an adaptive integral sliding mode FTC with CA scheme to ensure the faster and reliable actuation with the occurrence of faults.…”

Section: Introductionmentioning

confidence: 99%

Fault tolerant control using integral sliding modes with control allocation along the null-space

Liu

Yao

2020

Transactions of the Institute of Measurement and Control

View full text Add to dashboard Cite

In this paper, a new fault tolerant control scheme with control allocation is presented. The pseudo-inverse along the null-space control allocation is applied to the fault tolerant control system to handle the actuator constraints. The stability of the overall closed-loop system is proved via the small gain theory. The null-space vector is viewed as uncertainty, and is disposed by an integral sliding mode controller and a robust controller. The simulation results show that the new method can solve both failure scenarios and actuator saturation problems well.

show abstract

A Fault Tolerant Direct Control Allocation Scheme with Integral Sliding Modes

Cited by 5 publications

References 11 publications

Design of sliding mode flight control system for a flexible aircraft

Design of sliding mode flight control system for a flexible aircraft

Robust fault tolerant control allocation for a modern over‐actuated commercial aircraft

Fault tolerant control using integral sliding modes with control allocation along the null-space

Contact Info

Product

Resources

About