PERANCANGAN DAN ANALISIS STRUKTUR PLATFORM AGRICULTURAL DRONE SPRAYER UAV HEXACOPTER

TERNAMA SIAHAAN, JUNIOR (2022) PERANCANGAN DAN ANALISIS STRUKTUR PLATFORM AGRICULTURAL DRONE SPRAYER UAV HEXACOPTER. Skripsi thesis, Institut Teknologi Dirgantara Adisutjipto.

	Text (ABSTRAK) 16050125_ABSTRAK.pdf Download (392kB)
	Text (BAB I) 16050125_BAB I.pdf Download (156kB)
	Text (DAFTAR PUSTAKA) 16050125_DAFTAR PUSTAKA.pdf Download (67kB)
	Text (FULL SKRIPSI) 16050125 - converted.pdf Restricted to Repository staff only Download (1MB)

Abstract

This study aimed to design an Agricultural UAV (Unmanned Aerial Vehicle) aircraft that acts as an agricultural tool to spray in rice fields using 6 motors DC as the driving force. The important thing to do in the initial design of this Agricultural Drone was to design and analysis the strength of the design structure to ensure the safety of the structure as well as the durability and strength of the structure when it flies with a load. Design and modelling method were implemented in designing the Agricultural Drone Platform of this Agricultural Drone using CATIA VR21 Software and the calculation of structural strength using ANSYS R19.2 Software. For loading conditions using UAV Australia C.A.S.A. Subpart-C Structure UA25.337 regulation with a load factor value of 3.8 and -1,5. Loading was carried out on the 6 motors when the Drone was in a state of floating in the air with a total load maximum (MTOW) of 24 Kg. The Agricultural Drone Sprayer UAV Hexacopter platform has a total weight of 24000 grams, the configuration of the structure uses X Conviguration with a length of each arm of 650 mm. Components of the Hexacopter UAV Agricultural Drone Sprayer Platform consist of T-motor U10 100KV, Propeller T motor CF29*9.5, Lipo 10S -37V-35C 16000mAh, ESC T-Motor Flame 80A, Brushlass water pump sprayer WA3510 48V, Nozzle dan hose pipe, Flight Controller Mini CC3D, and Radio Control Receiver. From the results of the analysis of the stress value based on the Margin of Safety with a load factor of 3.8 the highest occurred in the Landing Gear 1 part of 20,722 (safe) and the largest load factor of -1.5 on Bolt Part 4 with a Margin of Safety value of 118,554 while for composite materials declared safe based on the Failure Criteria from the Inverse Reverse Factor data with a load factor of 3.8 the largest value occurred in the Carbon Tube 2 layer 1 angle 0° angle of 0,44223 and the load factor -1.5 occurred in the Carbon Tube 2 layer 2 part angle 45 ° is 0,16101.

Actions (login required)

View Item

Downloads