“Modeling and research of critical regimes of the sailplane LAK-17B structure”

Author, institution: Marius Andrikaitis, Kaunas University of Technology

Science area, field: Technological Sciences, Transport Engineering

Scientific supervisor: Prof. Dr. Habil. Algimantas FEDARAVIČIUS, (Kaunas University of Technology, Technological Sciences, Transport Engineering – 03T).

Dissertation Defense Board:

Prof. Dr. Habil. Vytautas OSTAŠEVIČIUS (Kaunas University of Technology, Technological Sciences, Transport Engineering – 03T) – chairman,

Prof. Dr. Žilvinas BAZARAS (Kaunas University of Technology, Technological Sciences, Transport Engineering – 03T),

Prof. Dr. Habil. Marijonas BOGDEVIČIUS (Vilnius Gediminas Technical University, Technological Sciences, Transport Engineering – 03T),

Prof. Dr. Artūras KERŠYS (Kaunas University of Technology, Technological Sciences, Transport Engineering – 03T),

Prof. Dr. Romualdas KLIUKAS (Vilnius Gediminas Technical University, Technological Sciences, Mechanical Engineering – 09T).

Official Opponents:

Dr. Rolanas DAUKŠEVIČIUS (Kaunas University of Technology, Technological Sciences, Mechanical Engineering – 09T),

Prof. Dr. Habil. Jonas STANKŪNAS (Vilnius Gediminas Technical University, Technological Sciences, Transport Engineering – 03T).

Annotation:

In order to get type certificate for a newly designed aircraft, the compliance with corresponding certification requirements must be shown.
During the certification process, the compliance with the requirements is demonstrated by performing flight and ground tests. With the development of computer hardware and computational methods, the number of cases, when requirements are met based on the use of numerical methods, is increasing.
This work can be divided into two main parts: (a) development of numerical models and (b) analysis of the sailplane critical regimes using these models. The goal of the analysis is to determine whether the structure complies with certification requirements.
The term “critical regimes” herein are used to define the limit static and dynamic load cases of the sailplane. Considered regimes: (a) main landing gear ground load conditions, (b) fuselage and tail surfaces flight load conditions, (c) empennage flutter.
The object being modeled and analyzed is Lithuanian aviation construction – 15/18-meter class sailplane LAK-17B.