Health and usage monitoring system for the small aircraft composite structure

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F68407700%3A21220%2F17%3A00319635" target="_blank" >RIV/68407700:21220/17:00319635 - isvavai.cz</a>

Výsledek na webu

<a href="https://www.scopus.com/record/display.uri?eid=2-s2.0-85025817366&origin=resultslist" target="_blank" >https://www.scopus.com/record/display.uri?eid=2-s2.0-85025817366&origin=resultslist</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.1063/1.4989944" target="_blank" >10.1063/1.4989944</a>

Jazyk výsledku

angličtina

Název v původním jazyce

Health and usage monitoring system for the small aircraft composite structure

Popis výsledku v původním jazyce

This paper is focused on the design of the health and usage monitoring system (HUMS) of the composite ultra-light aircrafts. A multichannel measuring system was developed and installed for recording of the long-term operational measurements of the UL airplane. Many fiber Bragg grating sensors were implemented into the composite aircraft structure, mainly in the glue joints. More than ten other analog functions and signals of the aircraft is monitored and can be correlated together. Changing of the FBG sensors responses in monitored places and their correlations, comparing with the calibration and recalibration procedures during a monitored life may indicate damage (eg. in bonded joints) and complements the HUMS system.

Název v anglickém jazyce

Health and usage monitoring system for the small aircraft composite structure

Popis výsledku anglicky

This paper is focused on the design of the health and usage monitoring system (HUMS) of the composite ultra-light aircrafts. A multichannel measuring system was developed and installed for recording of the long-term operational measurements of the UL airplane. Many fiber Bragg grating sensors were implemented into the composite aircraft structure, mainly in the glue joints. More than ten other analog functions and signals of the aircraft is monitored and can be correlated together. Changing of the FBG sensors responses in monitored places and their correlations, comparing with the calibration and recalibration procedures during a monitored life may indicate damage (eg. in bonded joints) and complements the HUMS system.

Druh

D - Stať ve sborníku

CEP obor

—

OECD FORD obor

20304 - Aerospace engineering

Projekt

<a href="/cs/project/TA04031450" target="_blank" >TA04031450: Systém pro sledování stavu konstrukcí pomocí optických vláknových snímačů</a><br>

Návaznosti

P - Projekt vyzkumu a vyvoje financovany z verejnych zdroju (s odkazem do CEP)

Rok uplatnění

2017

Kód důvěrnosti údajů

S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů

Název statě ve sborníku

AIP Conference Proceedings

ISBN

978-0-7354-1532-4

ISSN

0094-243X

e-ISSN

0094-243X

Počet stran výsledku

6

Strana od-do

—

Název nakladatele

American Institute of Physics Inc.

Místo vydání

—

Místo konání akce

St. Petersburg

Datum konání akce

19. 5. 2017

Typ akce podle státní příslušnosti

WRD - Celosvětová akce

Kód UT WoS článku

000410618900007