RECONFIGURE FP7 project preliminary results and contributions

Kerr, Murray; Goupil, Philippe; Boada-Bauxell, Josep; Rosa, Paulo; Recupero, Cristina

doi:10.1109/systol.2016.7739842

Cited by 5 publications

(8 citation statements)

References 12 publications

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“…The computational burden and complexity of the schemes also had to be compliant with stringent computational constraints to be possibly implemented on embedded computers. Robustness issues were tackled by using tools like a Functional Engineering Simulator, implemented during the project to achieve a traditional Monte Carlo analysis as a preliminary step of the industrial V&V process . It is also noteworthy that avenues do exist for improving the V&V of more complex controllers like the proposed adaptive scheme; for instance, a practical approach for the worst‐case analysis of a similar adaptive controller was already investigated by Airbus in the work of Oudin et al…”

Section: The A/c Problemmentioning

confidence: 99%

“…Robustness issues were tackled by using tools like a Functional Engineering Simulator, implemented during the project to achieve a traditional Monte Carlo analysis as a preliminary step of the industrial V&V process. 39 It is also noteworthy that avenues do exist for improving the V&V of more complex controllers like the proposed adaptive scheme; for instance, a practical approach for the worst-case analysis of a similar adaptive controller was already investigated by Airbus in the work of Oudin et al 14 The highly realistic nonlinear simulator of the RECONFIGURE project, which is very close to a real civil A/C, includes a nonlinear aerodynamic model with 5 longitudinal states: the angle of attack α, the pitch rate q, the pitch angle θ, the true airspeed V, and the altitude z. The acceleration N z is also to be accounted for as an additional output.…”

Section: T H E A/c Problemmentioning

confidence: 99%

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Adaptive LFT control of a civil aircraft with online frequency‐domain parameter estimation

Ferreres

Hardier²

2017

Intl J Robust & Nonlinear

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Summary This paper describes the application of an indirect linear fractional transformation (LFT)–based state‐space adaptive control scheme to a transport aircraft, within the context of the European project REconfiguration of CONtrol in Flight for Integral Global Upset REcovery. The principle of the scheme is to design and validate off‐line a gain‐scheduled controller, depending on the plant parameters to be estimated, and to combine it online with a model estimator, so as to minimize the onboard computational time and complexity. A modal approach, very classical for the design of a flight control law, is used to directly synthesize the static output feedback LFT controller, depending on the control and stability derivatives, ie, the parameters of the linearized aerodynamic state‐space model to be estimated. Since the gain‐scheduled LFT controller online depends on the parameter estimates instead of the true values, its robustness to transient and asymptotic estimation errors needs to be assessed using μ and integral quadratic constraint analysis techniques. A primary concern being an online implementation, a fully recursive frequency‐domain estimation technique is proposed, with a low online computational burden and the capability to track time‐varying parameters. Full nonlinear simulations along a trajectory validate the good performance properties of the combined estimator and gain‐scheduled flight controller. To some extent, minimal guaranteed stability and performance properties of the adaptive scheme can be ensured by switching to a robust controller when the parameter estimates are not reliable enough, thus bypassing the Certainty Equivalence Principle.

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Section: The A/c Problemmentioning

confidence: 99%

Section: T H E A/c Problemmentioning

confidence: 99%

Adaptive LFT control of a civil aircraft with online frequency‐domain parameter estimation

Ferreres

Hardier²

2017

Intl J Robust & Nonlinear

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“…For the V&V of the alternate protections it is assumed that all 3 AoA sensors become faulty but at least one VCAS sensor remains healthy. A Monte Carlo parameter study is performed . The Monte Carlo parameters are the aircraft's altitude, speed, weight and center of gravity, and different configurations.…”

Section: Industrial Verification and Validationmentioning

confidence: 99%

“…A Monte Carlo parameter study is performed. 2 The Monte Carlo parameters are the aircraft's altitude,…”

Section: Alternate Protectionsmentioning

confidence: 99%

“…The tackled problem is part of the EU‐FP7 Reconfiguration of Control in Flight for Integral Global Upset Recovery (RECONFIGURE) project on fault detection and diagnosis (FDD) and FTC techniques for modern civil aircraft. () Valuable contributions dealing with the same or parts of the defined control problem can be found in the literature. In the work of Chen et al, a linear parameter varying (LPV) approach together with sliding mode techniques is proposed.…”

Section: Introductionmentioning

confidence: 99%

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Multiobjective optimization–based fault‐tolerant flight control system design

Ossmann

Joos

2017

Intl J Robust & Nonlinear

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Summary The loss of measurements used for controller scheduling or envelope protection in modern flight control systems due to sensor failures leads to a challenging fault‐tolerant control law design problem. In this article, an approach to design such a robust fault‐tolerant control system, including full envelope protections using multiobjective optimization techniques, is proposed. The generic controller design and controller verification problems are derived and solved using novel multiobjective hybrid genetic optimization algorithms. These algorithms combine the multiobjective genetic search strategy with local, single‐objective optimization to improve convergence speed. The proposed strategies are applied to the design of a fault‐tolerant flight control system for a modern civil aircraft. The results of an industrial controller verification and validation campaign using an industrial benchmark simulator are reported.

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