From the early developments of the A320 program, thanks to Fly-By-Wire systems, Automatic Control techniques have significantly contributed to improve flight performance and safety of civilian aircraft. Today, most of the flight segments can be managed quite efficiently by the autopilot. However, the final approach and landing phases still remain critical in poor visibility and strong wind conditions. Based on a realistic nonlinear model of a civil transport aircraft in full configuration, the objective of the proposed challenge is to design an autopilot system to enable a correct landing despite parametric variations and maximized cross wind conditions.
Based on a realistic and highly adaptable aircraft model (whose characteristics are close to those of an A330) implemented in a fully open SIMULINK file, this challenge is jointly proposed by ONERA (Jean-Marc Biannic) and AIRBUS (Josep Boada-Bauxell).
A complete description of the model and the associated challenge can be found from the paper below:
The associated benchmark model is briefly described below and can be freely downloaded (and used in any non-commercial context) from a link provided at the bottom of this page. However, the authors require to be informed for any usage of the model and correctly referenced in any publication and report (see the References section at the bottom of the page).
The benchmark model is representative of a large, twin-engined, transport aircraft whose total mass may vary between 120t and 180t. A general view of the model is shown below.
Figure 1: A general view of the open-loop landing aircraft simulation diagram.
The objective is to design robust controllers to ensure smooth and precise landings despite many uncertainties and external perturbations (turbulences, windshear, ground effect). The general structure of the control laws is visualized in the following figures. A particular attention will be devoted to Flare and Align phases in this project.
Figure 2: A general view of the closed-loop landing aircraft simulation diagram.
Figure 3: A general view of the autoland control system.
The above Simulink diagrams (respectively named ACS.slx and ALS.slx) as well as a documentation (CACbench.pdf), triming and simulation routines (including Monte-carlo runs) can be extracted from the file CALC.zip file which is available for download from a link at the bottom of the page. Before downloading this file and using the benchmark, please read the disclaimer below. The benchmark comes with a basic version of an autoland control system which has been designed for nominal speeds and low wind conditions only.
The benchmark package including a rough baseline controller may be downloaded here
When using this benchmark to test and illustrate your own design methods in any non-commercial context, please mention the SMAC project and refer to the following paper:
|||J-M. Biannic and C. Roos. "Flare control law design via multi-channel Hinfinity synthesis: Illustration on a freely available nonlinear aircraft benchmark ", in Proceedings of the American Control Conference, Chicago, IL, USA, July 2015.|
|||J-M. Biannic and J. Boada-Bauxell. "A Civilian Aircraft Landing Challenge", On-line available from the aerospace benchmark section of the SMAC Toolbox, http://w3.onera.fr/smac/, Toulouse 2016.|
First version of the Aircraft Benchmark : v1.0 released on June 24th 2015.
Second version of the Aircraft Benchmark : v2.0 released on April 4th 2016.
Third version of the Aircraft Benchmark : v3.0 released on September, 30th 2016.
Fifth version of the Aircraft Benchmark : v5 released on October, 10th 2016.
Sixth version of the Aircraft Benchmark : v6 released on October, 24th 2016.
Current version of the Aircraft Benchmark : v7 released on February, 7th 2017.