ANALISIS KEKUATAN STRUKTUR PADA BATANG SAYAP
FLAPPING WING AF-1823
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Institusion
INSTITUT TEKNOLOGI DIRGANTARA ADISUTJIPTO
Author
Nurmeina Putri Sari Br Tarigan, Dwi
Subject
T Technology (General)
Datestamp
2024-02-15 08:26:53
Abstract :
Sparrows are a type of pest that attacks rice plants. In this case, technology is needed that can be used to assist in the process of repelling pests in agriculture, which is called flapping wing AF-1823 (Small Unmanned Aircraft). In this case the strength of the structure is the most important part of flapping wing AF-1823. Wings are an important part of the aircraft because of its construction. So that the analysis of the strength of the wing structure needs to be taken into account to determine the configuration of the structure and material. Modeling and analysis were carried out using CATIA V5R21 software based on the finite element method. After being analyzed, the results obtained are the static loading value on the flapping wing AF-1823 wing resulting from the value of 3,1498N. The maximum stress value in the flapping wing AF-1823 wing structure is found in the Carbon Fiber material variation 3 with a value of 2590 Mpa and the safety level of the FLAPPING WING AF-1823 wing structure is in the carbon fiber material variation 5-3 mm with a value of 2,70 and the lowest value is in the carbon fiber material variation 4-2 mm with a value of 0,16. Therefore variation 5-3 mm and 4-2 mm is said to be safe because the margin of safety is ? 0.
Sparrows are a type of pest that attacks rice plants. In this case, technology is needed that can be used to assist in the process of repelling pests in agriculture, which is called flapping wing AF-1823 (Small Unmanned Aircraft). In this case the strength of the structure is the most important part of flapping wing AF-1823. Wings are an important part of the aircraft because of its construction. So that the analysis of the strength of the wing structure needs to be taken into account to determine the configuration of the structure and material. Modeling and analysis were carried out using CATIA V5R21 software based on the finite element method. After being analyzed, the results obtained are the static loading value on the flapping wing AF-1823 wing resulting from the value of 3,1498N. The maximum stress value in the flapping wing AF-1823 wing structure is found in the Carbon Fiber material variation 3 with a value of 2590 Mpa and the safety level of the FLAPPING WING AF-1823 wing structure is in the carbon fiber material variation 5-3 mm with a value of 2,70 and the lowest value is in the carbon fiber material variation 4-2 mm with a value of 0,16. Therefore variation 5-3 mm and 4-2 mm is said to be safe because the margin of safety is ? 0.
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