Rémy Dayre

A Model-based Solution to Robust and Early Detection of Control Surface Runaways

This paper discusses the design of a model-based fault detection scheme for robust and early detection of runaways in aircraft control surfaces servo-loop. The proposed scheme can be embedded within the structure of in-service monitoring systems as a part of the Flight Control Computer (FCC) software. The final goal is to contribute to improve the performance detection of unanticipated runaway faulty profiles having very different dynamic behaviors, while retaining a perfect robustness. The paper discusses also the tradeoffs between adequacy of the technique and its implementation level, industrial validation process with Engineering support tools, as well as the tuning aspects. The proposed methodology is based on a combined data-driven and system-based approach using a dedicated Kalman filtering. The technique provides an effective method ensuring robustness and good performance (well-defined real-time characteristics and well-defined error rates). Simulation results, using In-flight recorded data sets provided by Airbus, are presented to demonstrate the potential of the developed technique.

Parametric Approach to Fault Detection in Aircraft Control Surfaces

THE required technological advances identified by the aeronautics sector to achieve the long-term goals of greener aviation are multiple and challenging. New technological options will be needed to produce incrementally more efficient and environmentally friendlier aircraft. The early and robust detection of faults that have an influence on structural loads contribute to the overall optimization of aircraft design, and therefore to weight savings for better overall performance in terms of fuel burn, noise, range, and environmental footprint.

A Method for Actuator Lock-in-place Failure Detection in Aircraft Control Surface Servo-loops

This paper deals with a signal-based method for robust and early detection of lock-in-place failures (a.k.a. jamming) in aircraft control surface servo-loops. Earlier and robust detection of such failures is an important issue since they may cause additional structural load and affect the sustainability of civil transport airplane. The proposed signal-based scheme uses a sliding-mode differentiator to provide derivatives of measurable signals in noisy environment. Jamming events are next detected by using a dedicated decision making-rule that is able to detect actuator outage (the stuck value can be near zero). The proposed monitoring scheme has been tested on Airbus test facilities located at Toulouse, France. The results confirm good level of robustness and performance, even in extreme situations. The proposed technique can be applied, with slight modifications, to any type of actuator, e.g. Hydraulic, Electro-Hydrostatic (EHA) or Electro-Backup-Hydrostatic (EBHA) actuators.

Practical design considerations for successful industrial application of model-based fault detection techniques to aircraft systems

This paper discusses some key factors which may arise for successful application of model-based Fault Detection(FD) techniques to aircraft systems.The paper reports on the results and the lessons learned during flight V&V(Validation &Verification) activities, implementation in the A380 Flight Control Computer(FCC) and A380 flight tests at Airbus(Toulouse, France).The paper does not focus on new theoretical materials, but rather on a number of practical design considerations to provide viable technological solutions and mechanization schemes. The selected case studies are taken from past and on-going research actions between Airbus and the University of Bordeaux (France). One of the presented solutions has received final certification on new generation Airbus A350 aircraft and is flying (first commercial flight: January 15,2015)