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Replica Design of L-40 "Meta Sokol " Aircraft - wing
Pluhař, Tomáš ; Jebáček, Ivo (referee) ; Píštěk, Antonín (advisor)
This diploma thesis targets in concept of wing, aileron, flap and main undercarriage of the ultralight replication of the plane L-40 called Meta Sokol. The thesis developed from cooperation with two other members of the team – Alice Lipková (aerodynamics, power) and Miroslav Růžička (fuselage, tail unit and rear gear). The first part of this diploma thesis is concerned with load and concept of structure of the wing. At first the flight envelope is specified, then charakteristics of shearing force, bending moment and torsion moment are determined spanwise. The concept and subsequent strength verification of structure of the wing is also solved. The same process is claimed to concept of the aileron and the flap. The second part of this diploma thesis is dealt with main landing gear, its support, structure, springing and the principle of retraction. The final passage is devoted to load of the undercarriage.
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The design of the landing gear of the small two-seat airplane
Trojánek, Tomáš ; Katrňák, Tomáš (referee) ; Vaněk, František (advisor)
The aim of this master thesis is modification of landing gear for accomplishment CS-23 regula-tion from that purpose, because landing gear in the use can't pass this type of certification. The first part examines the alternatives of landing gear with consideration optimal technical and eco-nomical difficulty. After finding optimal type of landing gear with shock absorber is there part of designing and computing the load. Last part of thesis is about stress analysis of whole con-cept and reconsidering final changes.
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Design of VUT200 TwinCobra landing gear
Novák, Josef ; Horák, Marek (referee) ; Katrňák, Tomáš (advisor)
The goal of following master thesis is to design variety of configuration and retraction options of VUT200 TwinCobra landing gear. For each option are a wheel base and a gauge set up by possibility of main landing gear retraction. Next, CS 23 demands and stress analysis are followed. There is a view of twin engine aircraft landing gear disclosed as well.
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Modification of the WT10 aircraft for the fixed landing gear according to the CS-23 requirements
Kubiena, Jaromír ; Juračka, Jaroslav (referee) ; Vaněk, František (advisor)
In this thesis, we deal with the design of a shock absorber variant for the type of main landing gear design of the aircraft WT10 Advantic. Then we focus on the design of the selected variant of the main landing gear. Next, we follow regulation CS-23 demands to calculate the load cases for the selected main lending gear. Then we design shock absorber based on the load during landing. We compile the equation of motion of the aircraft, which describes motion of the aircraft during landing, then we compute the equation. Finally, we focus on a stress analysis of the main landing gear and the shock absorber.
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Hi-wing aircraft landing gear design
Skutil, Marek ; Vaněk, František (referee) ; Jebáček, Ivo (advisor)
This diploma thesis deals with the design of the main retractable landing gear for a small high-wing aircraft. In the thesis there is made a kinematic solution of the main landing gear retraction, it’s conceptual and structural design and also selection of relevant components. Then there are performed landing gear load calculations according to the relevant regulation as well as representation of the main landing gear leg loads based on the strength analysis created in the Autodesk Inventor program. One part of the thesis is also 3D model of the main landing gear assembly.
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Modification of the landing gear of the Irbis aircraft
Forman, Tomáš ; Vaněk, František (referee) ; Šplíchal, Jan (advisor)
This master thesis deals with the landing gear rebuild from tail gear to nose gear of the M-4 Irbis aircraft. The first chapter presents the aircraft in its current state and includes some technical data, too. The theoretical information about types of landing gears, its characteristics, pros and cons and the typical representatives for each type of landing gear are mentioned in the second chapter. The third chapter is about landing gear loads that occur during landing and about the load calculation according to UL 2 regulation. The following chapter shows the construction of the new landing gear, including some of the suggested, but not realised, designs. In the fifth chapter, there is a landing gear strength calculation of some of the gear components. The calculation is analytical and then uses FEM. The very last chapter then shows the effect of new landing gear on the centre of gravity in its extreme positions. The chapter also compares aircraft masses with both landing gears.
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Hi-wing aircraft landing gear design
Skutil, Marek ; Vaněk, František (referee) ; Jebáček, Ivo (advisor)
This diploma thesis deals with the design of the main retractable landing gear for a small high-wing aircraft. In the thesis there is made a kinematic solution of the main landing gear retraction, it’s conceptual and structural design and also selection of relevant components. Then there are performed landing gear load calculations according to the relevant regulation as well as representation of the main landing gear leg loads based on the strength analysis created in the Autodesk Inventor program. One part of the thesis is also 3D model of the main landing gear assembly.
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Modification of the landing gear of the Irbis aircraft
Forman, Tomáš ; Vaněk, František (referee) ; Šplíchal, Jan (advisor)
This master thesis deals with the landing gear rebuild from tail gear to nose gear of the M-4 Irbis aircraft. The first chapter presents the aircraft in its current state and includes some technical data, too. The theoretical information about types of landing gears, its characteristics, pros and cons and the typical representatives for each type of landing gear are mentioned in the second chapter. The third chapter is about landing gear loads that occur during landing and about the load calculation according to UL 2 regulation. The following chapter shows the construction of the new landing gear, including some of the suggested, but not realised, designs. In the fifth chapter, there is a landing gear strength calculation of some of the gear components. The calculation is analytical and then uses FEM. The very last chapter then shows the effect of new landing gear on the centre of gravity in its extreme positions. The chapter also compares aircraft masses with both landing gears.
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