MODIFIKASI MATERIAL, ANALISIS KEKUATAN
STRUKTUR DAN MANUFAKTUR SAYAP PESAWAT
TRAINER-5774
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Institusion
INSTITUT TEKNOLOGI DIRGANTARA ADISUTJIPTO
Author
DEWI WIDYA TRIANI, SUCIARI
Subject
T Technology (General)
Datestamp
2024-07-16 02:02:34
Abstract :
Unmanned Aerial Vechicle (UAV) is one of the types an aircraft. Trainer is part of an airplane where the aircraft is controlled by a remote control for its flight. Its used by Aeromodellers. One of the things that must be considred in design an airplane is strength and and resistance of the wing structure in accepting distributed aircraft loads. In addition to the structural design and load, the material to be used can have an effect. The process is starting from modelin or modification of the aircraft wing using CATIA V5R20 which is then carried out analysis of the wing structure by being given the aircraft load using ANSYS 19. The strength value of the wing structure can be done after analyzing the result of the structural analysis to determain the Failure criteria where the value ?1 for a composite structure is safe and > is unsafe. Margin of safety is used to is also used to calculate balsa wood were margin of safety value ?1 is safe. The wing structure is safe with loads of 4,22 N in level flight conditions as well as n=2 load factor manuvers with load 8,44N. The analysys value of the wing structure is 58,505 MPa, the upper and lower Spars are 58,043 and 55,476 and then the Joiner section is 0,69 with load 4,22N. the results with the manuver load are 119,27 MPa aircraft wing, 118,21 and 114,2 at upper and lower the Spar structure, then 0,136 at Joiner. The largest structural value is in the Joiner section of 7,967 with manuvering load and smallest value is 0,026 on the Spar section. Margin of safety smallest value in the spar when its manuver. After analysis it is continued with the manufacturing process according to the design that has been made.
Unmanned Aerial Vechicle (UAV) is one of the types an aircraft. Trainer is part of an airplane where the aircraft is controlled by a remote control for its flight. Its used by Aeromodellers. One of the things that must be considred in design an airplane is strength and and resistance of the wing structure in accepting distributed aircraft loads. In addition to the structural design and load, the material to be used can have an effect. The process is starting from modelin or modification of the aircraft wing using CATIA V5R20 which is then carried out analysis of the wing structure by being given the aircraft load using ANSYS 19. The strength value of the wing structure can be done after analyzing the result of the structural analysis to determain the Failure criteria where the value ?1 for a composite structure is safe and > is unsafe. Margin of safety is used to is also used to calculate balsa wood were margin of safety value ?1 is safe. The wing structure is safe with loads of 4,22 N in level flight conditions as well as n=2 load factor manuvers with load 8,44N. The analysys value of the wing structure is 58,505 MPa, the upper and lower Spars are 58,043 and 55,476 and then the Joiner section is 0,69 with load 4,22N. the results with the manuver load are 119,27 MPa aircraft wing, 118,21 and 114,2 at upper and lower the Spar structure, then 0,136 at Joiner. The largest structural value is in the Joiner section of 7,967 with manuvering load and smallest value is 0,026 on the Spar section. Margin of safety smallest value in the spar when its manuver. After analysis it is continued with the manufacturing process according to the design that has been made.
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