Time-domain output error system identification of iced aircraft aerodynamics

Deiler, Christoph

doi:10.1007/s13272-016-0231-2

Cited by 9 publications

(9 citation statements)

References 15 publications

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“…For example, a ∆-model implementation accounting only for icing effects on the longitudinal motion might be much simpler than a ∆-model covering changes in all six degrees of freedom. Such a formulation for the longitudinal aircraft motion as well as the corresponding parameters resulting from system-identification is given in [22]. More complex ∆-models were developed in [18,23] accounting for icing-induced aerodynamic degradation and corresponding effects on the complete aircraft motion.…”

Section: Model Formulationmentioning

confidence: 99%

Facing the Challenges of Supercooled Large Droplet Icing: Results of a Flight Test Based Joint DLR-Embraer Research Project

Deiler¹,

Ohme²,

Raab³

et al. 2019

SAE Int. J. Adv. & Curr. Prac. in Mobility

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T oday's airplanes are well equipped to cope with most common icing conditions. However, some atmospheric conditions consisting of supercooled large droplets (SLD) have been identified as cause of severe accidents over the last decades as existing countermeasures even on modern aircraft are not necessarily effective against SLD-ice. In 2014, the new Appendix O to the certification regulations (FAR Part 25 / CS-25) had been issued to guarantee the safe operation of future airplane when encountering SLD conditions. But as the SLD topic is quite new for the majority of aircraft manufacturers and research institutes in a same way, DLR (German Aerospace Center) and Embraer established a joint research cooperation in 2012 to obtain a better understanding of the distinct influences of SLD-ice shapes on aircraft characteristics and to evaluate proper ways for future airplane certification under App. O. Furthermore, one additional scientific goal of the cooperation was to develop and test new tools for the in-flight monitoring of aircraft characteristics as well as the on-board identification of simulation models. During the 4 years of the project, a distinct way to better understand icing-induced degradations on a specific aircraft was followed: first, data of the clean aircraft was gathered in flight test to identify a dynamic simulation model as base for the subsequent evaluations. Second, data of test flights with artificial App. C ice configurations were analyzed and used for the development of distinct modifications of the base aircraft simulation model; a first evaluation of the icing-induced changes of aircraft characteristics was conducted. Third, after the generation of SLD-ice shapes, wind tunnel testing and flight clearance, a second flight test campaign with these artificial SLD-ice shapes delivered the data for an additional model modification and identification. The results of the final data and model evaluation provide the observable degradation of SLD-ice in flight, which is well comparable to results obtained from the App. C ice configurations.

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Section: Model Formulationmentioning

confidence: 99%

Facing the Challenges of Supercooled Large Droplet Icing: Results of a Flight Test Based Joint DLR-Embraer Research Project

Deiler¹,

Ohme²,

Raab³

et al. 2019

SAE Int. J. Adv. & Curr. Prac. in Mobility

Self Cite

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“…accumulation as well as a de-icing can be triggered by the user whereas the details about the degradation itself are part of the closed model to allow a fair and realistic test of new developments like detection algorithms or robust flight controllers. The corresponding knowledge about the expectable effects and a realistic amount of degradation is derived from previous icing research at DLR [45,46] where high-quality simulation models were identified from flight data.…”

Section: Wing Ice Casementioning

confidence: 99%

VIRTTAC - A Family of Virtual Test Aircraft for Use in Flight Mechanics and GNC Benchmarks

Deiler

Fezans

2019

AIAA Scitech 2019 Forum

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A new generic aircraft model called VIRTTAC-Castor is introduced. This model was developed by DLR and will be made available for the research community. VIRTTAC-Castor is the first member of a complete model family available in the future. The "VIRtual TesT AirCraft" models will consist of several aircraft designs of different sizes and configurations to be used for manifold applications. Each model of the VIRTTAC family can be utilized for virtual flight test just as engineers would perform with a real aircraft. The VIRTTAC family is designed to provide high-quality validation benchmark models for e.g. system identification, controller design and demonstration of fault-tolerant controllers as well as reduced envelope protection functions.

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“…accumulation as well as a de-icing can be triggered by the user whereas the details about the degradation itself are part of the closed model to allow a fair and realistic test of new developments like detection algorithms or robust flight controllers. The corresponding knowledge about the expectable effects and a realistic amount of degradation is derived from previous icing research at DLR [46,47] where high-quality simulation models were identified from flight data.…”

Section: Test Scenarios and Failure Casesmentioning

confidence: 99%

Inside the Virtual Test Aircraft (VIRTTAC) Benchmark Model: Simulation Architecture

Fezans¹,

Deiler²

2019

SNE

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This paper presents the newly introduced Virtual Test Aircraft (VIRTTAC) model for use in benchmarks for aeronautics research. This model is shared in a black-box form and the core of an open-source benchmark suite. The model needs to remain undisclosed to fulfill its purpose but the principles underlying its internal structure are described in the paper. They permit to ensure that the model equations, parameters, and states are not accessible to the user, that the model can be easily ported to other simulation environments than MATLAB/Simulink, and that it is well maintainable on the long-term.

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Time-domain output error system identification of iced aircraft aerodynamics

Cited by 9 publications

References 15 publications

Facing the Challenges of Supercooled Large Droplet Icing: Results of a Flight Test Based Joint DLR-Embraer Research Project

Facing the Challenges of Supercooled Large Droplet Icing: Results of a Flight Test Based Joint DLR-Embraer Research Project

VIRTTAC - A Family of Virtual Test Aircraft for Use in Flight Mechanics and GNC Benchmarks

Inside the Virtual Test Aircraft (VIRTTAC) Benchmark Model: Simulation Architecture

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