PEMODELAN DAN ANALISIS STRUKTUR WING UNMANNED AERIAL VEHICLE (UAV) SEJENIS BIXLER 2 MENGGUNAKAN SOFTWARE CATIA V5R20

ILLAHY, FIRMAN (2018) PEMODELAN DAN ANALISIS STRUKTUR WING UNMANNED AERIAL VEHICLE (UAV) SEJENIS BIXLER 2 MENGGUNAKAN SOFTWARE CATIA V5R20. Skripsi thesis, Institut Teknologi Dirgantara Adisutjipto.

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Abstract

Unmanned Aerial Vehicle (UAV) is one of a kind aircraft. One of the things that must be considered in the UAV is the strength and endurance of the design of its wing structure in accepting a distributed aircraft load. In addition to structural design and loading, the structural strength criterion is also influenced by its material strength. Based on the importance of wing structure and materials used, the authors modeled and analyzed the strength of the aircraft wing structure in UAV type Bixler 2. The process is to calculate the lift load value which the load is applied on a wing structure that has been modeled and then analyzed using CATIA V5R20 where the process of analysis on the software using finite element method. Finding the strength value of wing structure can be done after obtaining the results of analysis by knowing the margin of safety where the value of MS ≥ 0 for the structure can be said to be safe and the value of MS < 0 for the structure is said to be unsafe when it receives load. The wing structure can still be said to be safe in holding the load well in the cruising condition with load value of 5,88399 N with the load factor n = 1 and the turning performance (banking) 60° condition with load value of 11,76798 N with load factor n = 2. In hard landing condition having load value 22,359162 N with load factor n = 3,8, it is got maximum value of stress at wing section structure equal to 6,94 × 105 N m2⁄ with margin of safety of −0,076 and the maximum stress value on the spar tube structure of 2,49 × 107 N m2⁄ with margin of safety of 32,242. From the three results of the analysis it can be concluded that the overall wing structure can still withstand the load, except the wing section structure on hard landing conditions

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