Abstract
VTOL UAV aircraft is aircraft capable of vertical takeoff and landing (VTOL) and have flexible maneuverability. This aircraft is increasingly being used because of its ability to carry out various missions. The aircraft modification process that was previously designed for the VTOL VX-1 was carried out to correct problems encountered during flight tests The stages of research carried out in the static analysis of the structural strength of the UAV VX-2 aircraft were to modify the wing structure, fuselage and tail of the previous aircraft design, carry out modeling with CATIA software and then analyze the structure with Patran-Nastran to ensure the modification was safe. The result of the analysis the modified structure of the UAV VX-2 aircraft design, the wing structure has a maximum stress 185 MPa in the case of torsion loads, while the maximum tension tail structure 257 MPa is located in the horizontal stringer stabilizer at pull up loads. The results of the calculation the Margin of Safety with all positive values, the modified structure is declared safe.
Highlights
Kondisi ini terjadi saat pesawat melakukan transisi dari vertical take off ke cruising
Diasumsikan bebannya merupakan beban saat take off dikalikan load factor 3,8, hasil ini dikalikan panjang batang vertical takeoff and landing (VTOL) 310 mm untuk memperoleh besar momen torsi
Beban take off pada satu engine mounting sama dengan beban total dibagi 4 yang merupakan jumlah motor pada pesawat
Summary
Pada tahap ini menggali sumber referensi yang berhubungan dengan topik penelitian seperti buku, jurnal, serta sumber referensi yang lain. 2. Proses Modifikasi Rancangan Pada tahap ini dilakukan proses modifikasi geometri pesawat UAV VX-1 untuk memperbaiki kendala yang yang terjadi sebelumnya serta memperbaiki konsep assembly saat proses manufaktur. 3. Analisis Statik Kekuatan Struktur Tahap ini melakukan pemodelan geometri hasil proses modifikasi dengan software CATIA V5R21. Tahap berikutnya melakukan analisis struktur dengan software MSC Patran Nastran serta menghitung kekuatan struktur berdasarkan nilai Margin of Safety [11]. Untuk memvalidasi model simulasi dilakukan uji konvergensi pada nilai tegangan yang dihasilkan akibat perubahan jumlah elemen. Untuk mempermudah manufaktur maupun handling, rancangan sayap dibagi menjadi 2 bagian dan disambung dengan batang tube karbon.
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