PENGUJIAN STRUKTUR WING PADA PESAWAT VTOL SKY-BEEJO DENGAN PENDISTRIBUSIAN BEBAN MENGGUNAKAN METODE SCHRENK

RIZQY AVANSYAH, WANA (2024) PENGUJIAN STRUKTUR WING PADA PESAWAT VTOL SKY-BEEJO DENGAN PENDISTRIBUSIAN BEBAN MENGGUNAKAN METODE SCHRENK. Skripsi thesis, Institut Teknologi Dirgantara Adisutjipto.

	Text (ABSTRAK) 18050084_ABSTRAK.pdf Download (11kB)
	Text (BAB I) 18050084_BAB I.pdf Download (94kB)
	Text (DAFTAR PUSTAKA) 18050084_DAFTAR PUSTAKA.pdf Download (13kB)
	Text (FULL SKRIPSI) 18050084.pdf Restricted to Repository staff only Download (2MB)

Abstract

Wing is the main structure of an airplane wing which functions to produce lift. The wings on the Sky-beejo must have a structure that meets the criteria for strength and stiffness and must withstand the loads that occur, one of which is bending loads. The maximum bending load on a wing can be identified by carrying out a bending testing process. The bending test is a material testing process by pressing to obtain results in the form of data about the bending load of the material being tested. This research was carried out with the aim of finding out the maximum bending load that the Sky-beejo wing can withstand. Bending Testing Process. on the wings of UAV aircraft is carried out by determining the load using the Schrenk method. starting from rib 1, namely the root chord, to rib 13, namely the tip chord. Distribution of 11gram sand load on all ribs. The measurement process was carried out for deflection but it is not yet visible. The second load of sand was filled from rib 12 with 220 grams of sand. The deflection was measurable and there was a deflection of 140 mm. The sand load distribution continues to be filled until the addition of 13 with a weight of 2870 grams is filled at the root chord. However, during the distribution of 9 wing structures, the structure was completely broken. For the process, the fulcrum is at the end of the mid wing and the load will be applied to each rib gradually until the wing being tested breaks. From the test results, it was found that there was damage to the upper part, a fracture at rib 1, and a fracture at the joiner. The deflection value of the wing before breaking was 610mm and the maximum bending load of the wing was 164,159 N.

Actions (login required)

View Item

Downloads