Impact Loads and Crash Safety of the Cockpit of a Composite Glider
One major problem associated with gliding is the safety of the crew during landings in the country outside the airfield. The analysis of glider-accident statistics shows that such out-landings may significantly influence the safety. Therefore, of vital importance are the crashworthiness properties o...
| Main Authors: | , , , |
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| Format: | Article |
| Language: | English |
| Published: |
Sciendo
2019-12-01
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| Series: | Fatigue of Aircraft Structures |
| Subjects: | |
| Online Access: | https://doi.org/10.2478/fas-2019-0005 |
| _version_ | 1797969538280587264 |
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| author | Lindstedt Łukasz Rodzewicz Mirosław Rzymkowski Cezary Kędzior Krzysztof |
| author_facet | Lindstedt Łukasz Rodzewicz Mirosław Rzymkowski Cezary Kędzior Krzysztof |
| author_sort | Lindstedt Łukasz |
| collection | DOAJ |
| description | One major problem associated with gliding is the safety of the crew during landings in the country outside the airfield. The analysis of glider-accident statistics shows that such out-landings may significantly influence the safety. Therefore, of vital importance are the crashworthiness properties of the glider fuselage structure. The subject of the study was the PW-5 glider fuselage made of composites and subjected to high loads typical of glider crashes. The aim was to provide experimental data for validation of a numerical model of the cockpit-pilot system during impact. Two experimental tests with the composite glider cockpit were performed using a typical car-crash track. During the first test the cockpit with a dummy inside was crashed onto the ground at the angle of 45 degrees at a speed of 55 km/h. Accelerations and deformations at chosen points in the cockpit as well as signals coming from the dummy sensors and forces in the seat belts were recorded. The second test was an impact into a concrete wall at a speed of about 80 km/h. The full-scale tests were accompanied by a number of quasi-static and dynamic laboratory tests on samples of composite material. The experimental tests provided valuable results for the parametrical identification of a simulation model developed using the MADYMO software. |
| first_indexed | 2024-04-11T03:03:47Z |
| format | Article |
| id | doaj.art-460ad630b9c142bbbf962bbd27828f4a |
| institution | Directory Open Access Journal |
| issn | 2300-7591 |
| language | English |
| last_indexed | 2024-04-11T03:03:47Z |
| publishDate | 2019-12-01 |
| publisher | Sciendo |
| record_format | Article |
| series | Fatigue of Aircraft Structures |
| spelling | doaj.art-460ad630b9c142bbbf962bbd27828f4a2023-01-02T13:34:33ZengSciendoFatigue of Aircraft Structures2300-75912019-12-01201911395510.2478/fas-2019-0005fas-2019-0005Impact Loads and Crash Safety of the Cockpit of a Composite GliderLindstedt Łukasz0Rodzewicz Mirosław1Rzymkowski Cezary2Kędzior Krzysztof3Warsaw University of Technology, Institute of Aeronautics and Applied Mechanics plac Politechniki 1, 00-661Warsaw, PolandWarsaw University of Technology, Institute of Aeronautics and Applied Mechanics plac Politechniki 1, 00-661Warsaw, PolandWarsaw University of Technology, Institute of Aeronautics and Applied Mechanics plac Politechniki 1, 00-661Warsaw, PolandWarsaw University of Technology, Institute of Aeronautics and Applied Mechanics plac Politechniki 1, 00-661Warsaw, PolandOne major problem associated with gliding is the safety of the crew during landings in the country outside the airfield. The analysis of glider-accident statistics shows that such out-landings may significantly influence the safety. Therefore, of vital importance are the crashworthiness properties of the glider fuselage structure. The subject of the study was the PW-5 glider fuselage made of composites and subjected to high loads typical of glider crashes. The aim was to provide experimental data for validation of a numerical model of the cockpit-pilot system during impact. Two experimental tests with the composite glider cockpit were performed using a typical car-crash track. During the first test the cockpit with a dummy inside was crashed onto the ground at the angle of 45 degrees at a speed of 55 km/h. Accelerations and deformations at chosen points in the cockpit as well as signals coming from the dummy sensors and forces in the seat belts were recorded. The second test was an impact into a concrete wall at a speed of about 80 km/h. The full-scale tests were accompanied by a number of quasi-static and dynamic laboratory tests on samples of composite material. The experimental tests provided valuable results for the parametrical identification of a simulation model developed using the MADYMO software.https://doi.org/10.2478/fas-2019-0005crash safetycomposite glidermodel experimental validation |
| spellingShingle | Lindstedt Łukasz Rodzewicz Mirosław Rzymkowski Cezary Kędzior Krzysztof Impact Loads and Crash Safety of the Cockpit of a Composite Glider Fatigue of Aircraft Structures crash safety composite glider model experimental validation |
| title | Impact Loads and Crash Safety of the Cockpit of a Composite Glider |
| title_full | Impact Loads and Crash Safety of the Cockpit of a Composite Glider |
| title_fullStr | Impact Loads and Crash Safety of the Cockpit of a Composite Glider |
| title_full_unstemmed | Impact Loads and Crash Safety of the Cockpit of a Composite Glider |
| title_short | Impact Loads and Crash Safety of the Cockpit of a Composite Glider |
| title_sort | impact loads and crash safety of the cockpit of a composite glider |
| topic | crash safety composite glider model experimental validation |
| url | https://doi.org/10.2478/fas-2019-0005 |
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