<abstract xmlns="http://www.w3.org/1999/xhtml"><p>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.</p></abstract>

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.

Impact Loads and Crash Safety of the Cockpit of a Composite Glider

Institute of Aeronautics and Applied Mechanics plac Politechniki 1

Fatigue of Aircraft Structures

This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 3.0 License.

{"article-title":"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...

Impact Loads and Crash Safety of the Cockpit of a Composite Glider

Publicado en línea: 15 jul 2020

Páginas: 39 - 55

DOI: https://doi.org/10.2478/fas-2019-0005

Palabras clave
crash safety, composite glider, model experimental validation

© 2019 Łukasz Lindstedt et al., published by Sciendo

This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 3.0 License.

Impact Loads and Crash Safety of the Cockpit of a Composite Glider

Publicado en línea: 15 jul 2020

Páginas: 39 - 55

DOI: https://doi.org/10.2478/fas-2019-0005

Palabras clavecrash safety, composite glider, model experimental validation

© 2019 Łukasz Lindstedt et al., published by Sciendo

This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 3.0 License.

Palabras clave
crash safety, composite glider, model experimental validation