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Modeling, design and optimization of the business jet aircraft fuslage structure

Marek Jonas

Abstract

This paper is focused on the design of composite fuselage structure of very light, five-seated, turbofan jet. The plane is to be offered to private users, equipped with a pressurized cabin, recovery parachute system and a modern avionics allowing for use in IFR conditions. The main advantage of the aircraft is low take-off weight equal to 1400 kg - the lowest among competitors. Therefore it is necessary to keep low weight of the carrying structure. To meet this challenging task a carbon composite prepregs cured in an autoclave were used. This material provides a very high strength-to-weight ratio, but requires more complex calculations than that of metal. The dissertation presents the manner of designing parts and assemblies including the fuselage loaded structure to meet the requirements of airworthiness CS-23 and additional functional properties, enhancing the attractiveness of the aircraft. The mathematical models have been shown to: appoint of the plane loads, simulate the layered anisotropic shells, predict strength margin and critical forces. There was created a discreet computational model of the fuselage structure and then analyzed by finite element method. The division of decisive load cases was shown on the selected areas of the structure. Particularly, for the tail of the fuselage there was developed a more detailed model, which allowed to choose the material and direction of orientation of the layers. An optimization of the position of the access hole cut out into the heavily loaded tail skin was performed. Numerical results obtained from mathematical modeling were compared to measurements obtained from static tests in a laboratory and a good accuracy was confirmed. It was found that the highest relative error of tail displacement was of order 20%.
Record ID
WUTb6d74381a33a40238efc37a1908b0de6
Diploma type
Doctor of Philosophy
Author
Marek Jonas Marek Jonas,, Faculty of Power and Aeronautical Engineering (FPAE)
Title in Polish
Modelowanie, projektowanie i optymalizacja struktury nośnej kadłuba samolotu klasy Business_Jet
Title in English
Modeling, design and optimization of the business jet aircraft fuslage structure
Language
(pl) Polish
Certifying Unit
Faculty of Power and Aeronautical Engineering (FPAE)
Discipline
automation and robotics / (technology domain) / (technological sciences)
Status
Finished
Start date
18-06-2013
Defense Date
16-12-2014
Title date
19-12-2014
Supervisor
Internal reviewers
External reviewers
Maciej Bossak Maciej Bossak,, External affiliation of publication: Institute of Aviation
Pages
170
Internal identifier
MEL; D-174
Keywords in English
composite structure, aircraft modeling and design
Abstract in English
This paper is focused on the design of composite fuselage structure of very light, five-seated, turbofan jet. The plane is to be offered to private users, equipped with a pressurized cabin, recovery parachute system and a modern avionics allowing for use in IFR conditions. The main advantage of the aircraft is low take-off weight equal to 1400 kg - the lowest among competitors. Therefore it is necessary to keep low weight of the carrying structure. To meet this challenging task a carbon composite prepregs cured in an autoclave were used. This material provides a very high strength-to-weight ratio, but requires more complex calculations than that of metal. The dissertation presents the manner of designing parts and assemblies including the fuselage loaded structure to meet the requirements of airworthiness CS-23 and additional functional properties, enhancing the attractiveness of the aircraft. The mathematical models have been shown to: appoint of the plane loads, simulate the layered anisotropic shells, predict strength margin and critical forces. There was created a discreet computational model of the fuselage structure and then analyzed by finite element method. The division of decisive load cases was shown on the selected areas of the structure. Particularly, for the tail of the fuselage there was developed a more detailed model, which allowed to choose the material and direction of orientation of the layers. An optimization of the position of the access hole cut out into the heavily loaded tail skin was performed. Numerical results obtained from mathematical modeling were compared to measurements obtained from static tests in a laboratory and a good accuracy was confirmed. It was found that the highest relative error of tail displacement was of order 20%.
Thesis file
  • File: 1
    Jonas praca.pdf
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Uniform Resource Identifier
https://repo.pw.edu.pl/info/phd/WUTb6d74381a33a40238efc37a1908b0de6/
URN
urn:pw-repo:WUTb6d74381a33a40238efc37a1908b0de6

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