Research and Education in Aircraft Design 2018

Since 1994 every second year the Research and Education in Aircraft Design (READ) conference has been organized as a general forum for exchange of information about progress in aerospace engineering research. The unique character of the seminar is given by its focus also on aircraft engineering education and inclusion of juried student session. Following the success of the READ 2016, Warsaw, the 2018 seminar will be held in Brno, Czech Republic.

Conference proceedings

Published by: Brno University of Technology, Faculty of Mechanical Engineering, Institute of Aerospace Engineering
Editors: Jan Navrátil, Luboš Janhuba
ISBN: 978-80-214-5696-9
DOI: 10.13164/conf.read.2018

Table of contents

Review process

All papers were double blind peer reviewed by members of scientific committee and by external reviewers from European academic and research institutes.

Copyright Ⓒ 2018 Brno University of Technology, Faculty of Mechanical Engineering, Institute of Aerospace Engineering
All articles are distributed under the Creative Commons Attribution License (CC BY 4.0) which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.

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Recent Submissions

Now showing 1 - 5 of 19
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    About conference
    (Vysoké učení technické v Brně, Fakulta strojního inženýrství, 2019) Navrátil, Jan; Janhuba, Luboš
    About conference, conference proceedings and review process, scientific committee, table of contents
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    Modelling of health monitoring signals and detection areas for aerospace structures
    (Vysoké učení technické v Brně, Fakulta strojního inženýrství, 2019) Šplíchal, Jan; Hlinka, Jiří
    This paper is focused on Structural Health Monitoring (SHM) for aerospace use. It analyses the performance of commercially available finite element (FE) software packages for the simulation of propagation of ultrasonic guided waves (UGW) in typical aerospace structures. The purpose of the research is to support activities leading to the introduction of UGW based health monitoring on aerospace structures, as well as to support the design of future structures with integrated health monitoring. Activities are demonstrated on panels with growing complexity (adding different materials, sensors, damage types etc.). FE simulations are used to identify “detection areas” of UGW sensors. This output can be directly applied to the design of future aerospace structures with an integrated SHM system (to ensure the proper planning of the placement of UGW sensors).
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    Diagnostic parameters determination of aircraft hydraulic system
    (Vysoké učení technické v Brně, Fakulta strojního inženýrství, 2019) Třetina, Karel; Cäsar, Tomáš
    The article presents methodology for application of information theory for selection of hydraulic system diagnostic parameters. Changes in technical state of the system are accompanied by a set of symptoms. Method of determining information value of each symptom by information theory is presented. A set of technical conditions and set of symptoms for a simple hydraulic system are determined. Matrix of technical state describing relations between technical conditions and symptoms is constructed. The four symptoms are determined by matrix analysis with use of information theory. These symptoms are chosen as diagnostic parameters and provide the most information about technical state of the hydraulic system.
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    Layout optimisation method for active structural health monitoring
    (Vysoké učení technické v Brně, Fakulta strojního inženýrství, 2019) Červenka, Miroslav; Koštial, Rostislav
    This paper describes optimisation method for designing sensoric layout for Active Structural Health Monitoring (A-SHM) by Ultrasonic Guided Waves (UGW) on metal and non-metal (composite) materials. The SHM sensors need to be placed optimally in order to detect structural damage with high probability before the damage turns critical. Configuration of used optimisation algorithm for such task is not straightforward. Differential Evolution (DE) has two configuration parameters – the mutation factor F and the crossover rate CR – whose settings largely influence the solution quality the optimisation process can yield. For that matter we describe an elaborated a method to guide this selection towards good results using visual heat maps with the intent to select best DE’s variant and particular configuration to receive the most optimal SHM sensorics layout.
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    Simple universal nonlinear longitudinal flight simulation with avoiding of static and dynamic stability derivatives
    (Vysoké učení technické v Brně, Fakulta strojního inženýrství, 2019) Matějů, Jiří
    This paper shows simple method to simulate nonlinear longitudinal flight dynamic of an aircraft in the most direct way. The method is based on physical principles of an analytical-empiric flight dynamics. Non-linearity, as stall or thrust dependent on velocity, can be included. Static and dynamic stability derivatives are not required but can be computed as an output. The model is applicable for various aircraft conceptions. Higher level model, for example, based on flight tests data, can be modified by low-level analytical methods, e.g. for modification of horizontal tail area. No special simulation software is necessary. The model is compared to linear model and flight test experiment. This model, together with valuable analytical-empiric data, might be applied for fast flight dynamic computations. Model is easily accessible and understandable even with basic knowledge of flight dynamic and computer programming. The main application of the method is conceptual design when high precision is not expected, even if VLM, CFD or flight test data can improve the precision.