ANALISIS KEKUATAN STRUKTUR PADA SAYAP MORPHING UAV MENIRU PESAWAT CESSNA 172

Abstract

Nowadays, UAVs are widely used in various sectors including military, agricultural, social and other fields. There are two types of UAV control, the first uses remote control or remote control and the second the aircraft is flown independently or on autopilot. The results of the MBKM research at the Yogyakarta College of Aerospace Technology campus in 2022 resulted in several shortcomings, including having a heavier mass than a UAV wing made from balsa wood with a weight difference of 874 grams and another problem, namely that the wing's straight geometric shape will cause more resistance. so big that it needs to be changed to a morphing wing. Based on the shape of the wing and the problems, the researchers tried to correct these deficiencies by forming a new geometry. The design of this research uses CFD and FEA methods to determine deformation and pressure values. With research results. Pressure distribution on the wing surface using CFD simulation displays contour velocity and contour pressure. For contour pressure, use a velocity of 21 m/s, 22 m/s, 23 m/s, 24 m/s, 25 m/s which flows through the front of the airfoil. At a speed of 21 m/s the maximum value is 26.89 m/s, then if the speed increases then the maximum value will also increase. At a speed of 25 m/s the maximum value is 32.03 m/s. At a speed of 21 m/s the maximum value of deformation is 0.33164 mm, at a speed of 22 m/s the maximum value of deformation is 0.3515 mm, at a speed of 23 m/s the maximum value of deformation is 0.37107 mm, at a speed of 24 m/s the maximum value of deformation is 0.55469 mm, and at a speed of 25 m/s the maximum value of deformation is 0.56883 mm.