From theory to flight tests: Airbus Flight Control System TRL5 achievements

Goupil, Philippe; Dayre, RÃ©my; Brot, P.

doi:10.3182/20140824-6-za-1003.02547

Cited by 12 publications

(12 citation statements)

References 7 publications

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“…Therefore, it is hard to use advanced processors capable of executing online optimization or even wavelet or Fourier transforms in real time. In RECONFIGURE, to allow the industrial partners to evaluate the computational load of the designs, they have all been coded following the Airbus state of practice for FCC software coding using the SAO (Airbus software, Computer‐Assisted Specification) library, which contains a set of graphical functional blocks (similar to SIMULINK blocks), allowing only a limited set of mathematical operations. Then, an automatic generation tool calculates the computational load and produces the code to be implemented on the FCC.…”

Section: Design and Evaluation Resultsmentioning

confidence: 99%

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Development and evaluation of an integral sliding mode fault‐tolerant control scheme on the RECONFIGURE benchmark

Chen

Alwi

Edwards

2017

Intl J Robust & Nonlinear

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Summary This paper describes the development, application, and evaluation of a linear parameter‐varying integral sliding mode control allocation scheme to the Reconfiguration of Control in Flight for Integral Global Upset Recovery benchmark model to deal with an actuator failure/fault scenario. The proposed scheme has the capability to maintain close to nominal (fault free) load factor control performance in the face of elevator failures/faults by including a retrofitted integral sliding mode term and then rerouting (via control allocation) the augmented control signal to healthy elevators without reconfiguring the baseline controller. In order to mitigate any chattering appearing in the elevator demands, the retrofitted signal is based on a super‐twisting sliding mode structure. This produces a control signal that is continuous and does not have the discontinuous switching nature of traditional sliding mode schemes. The scheme is evaluated using an industrial Functional Engineering Simulator developed as part of the Reconfiguration of Control in Flight for Integral Global Upset Recovery project. Monte Carlo campaign results are shown to demonstrate the performance of the proposed scheme.

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Section: Design and Evaluation Resultsmentioning

confidence: 99%

“…where the virtual control terms δ a is the original control law defined in Equations 48 and 49, v s is the added sliding mode (super-twist) term, and B f 2 is defined in Equation 59. From Equation 66, it follows:…”

Section: Control Law Designmentioning

confidence: 99%

Development and evaluation of an integral sliding mode fault‐tolerant control scheme on the RECONFIGURE benchmark

Chen

Alwi

Edwards

2017

Intl J Robust & Nonlinear

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“…The aim of our study and its purpose to the aviation community is similar to the goal of the real-time on-board Fault Detection and Diagnosis introduced by Goupil et al [34] but differs in the scope of their study. Their study focuses on numerical aspects of signals and emphasizes on the link between academic and industrial R&D. Our research work aims at bringing new knowledge regarding timed aspects of discrete-event models.…”

Section: Related Workmentioning

confidence: 99%

Timed Discrete-Event Simulation of Aviation Scenarios

Van¹,

Boulanger²,

Wolff³

2020

SNE

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Ensuring systems behave as they are expected is unavoidable in the context of critical environments. In the aviation industry, certification standards provide rules and protocols to ensure correct maneuvers with respect to logical or timed events. These are targeted to computer-intensive systems as well as to human flight crews. In this setting, we are interested in the modeling and simulation of event-driven and time-driven behaviors at a high level. This study focuses on the TESL language [1] that provides a logical framework for timed behaviors with monitoring and testing features. In particular, we model various aviation scenarios and focus our study on fault monitoring. Multi-pilot aircrafts. The Airbus A320 aircraft family is a well-known system made of fault-tolerant components based on redundancy and dissimilarity. Traverse [12, 13] reported that the aircraft primary control surface computers were designed by different design analysts on independent architectures. This case of heterogeneity clearly exhibits how a multi-paradigm environment needs to be unified in order to be validated at a higher-level. Unmanned aircrafts. Furthermore, recent advances in unmanned aircrafts [14, 15] make the topic of verification and validation even more crucial due to the need of safe, reliable and fully automated software-intensive systems [16, 17] where, accordingly, design and test procedures tend to be fully automated.

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“…Despite the advancements in Technology Readiness Levels (TRLs) achieved during the European projects ADDSAFE and RECONFIGURE, only one FDD scheme, based on an extended Kalman filter formulation, was flight tested and certified on the A350-XWB aircraft [18]. Such a validation is usually considered the final 'top level' check in the aviation industria l validation process.…”

Section: Introductionmentioning

confidence: 99%

Flight Evaluation of an LPV Sliding Mode Observer for Sensor FTC

Chen

Alwi

Edwards

et al. 2022

IEEE Trans. Contr. Syst. Technol.

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This paper develops a sliding mode sensor fault tolerant control scheme for a class of LPV systems. It incorporates a sliding mode observer which reconstructs the unknown sensor faults based on only the system inputs and outputs. The reconstructed sensor faults are used to compensate the corrupted sensor measurements before they are used in the feedback controller. Provided accurate fault estimates can be computed, near nominal control performance can be retained without any controller reconfiguration. Furthermore, the closed-loop stability of the FTC scheme, involving both a sliding mode controller and a sliding mode observer, is rigorously analysed. The proposed scheme is validated using the Japan Aerospace Exploration Agency's Multi-Purpose Aviation Laboratory (MuPAL-α) research aircraft. These flight tests represent the first validation tests of a sliding mode sensor FTC scheme on a full scale aircraft. sliding mode control, fault tolerant control, fault detection and diagnosis, flight test.

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From theory to flight tests: Airbus Flight Control System TRL5 achievements

Cited by 12 publications

References 7 publications

Development and evaluation of an integral sliding mode fault‐tolerant control scheme on the RECONFIGURE benchmark

Development and evaluation of an integral sliding mode fault‐tolerant control scheme on the RECONFIGURE benchmark

Timed Discrete-Event Simulation of Aviation Scenarios

Flight Evaluation of an LPV Sliding Mode Observer for Sensor FTC

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