ANALISIS KELENTURAN STRUKTUR SAYAP PESAWAT UAV TERHADAP GAYA HAMBAT MENGGUNAKAN AUTODESK INVENTOR

Muhammad, Muhammad and Yani, Irsyadi (2018) ANALISIS KELENTURAN STRUKTUR SAYAP PESAWAT UAV TERHADAP GAYA HAMBAT MENGGUNAKAN AUTODESK INVENTOR. Undergraduate thesis, Sriwijaya university.

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Abstract

UAV (Unmanned Aerial Vehicle) is one of a variety of sophisticated robots in the world that are given special abilities. UAV it self is often referred to as a flying machine that can be controlled from a great distance or it can also be said that UAV itself is the pilot in the vehicle. Since it has no crew, UAV it self must be controlled using the remote control from outside the vehicle or it can also be called as RPV (Remotely Piloted Vehicle). The UAV aircraft itself consists of various components and structures which become a unit that has limited structural flexibility. Until now UAVs have generally developed very rapidly and are also used for military purposes. However, the UAV can also be used for human purposes such as aerial and civil surveys that are needed by the govemment and the private sector in Indonesia. Then the purpose of the research that will be used is to analyse the inhibitory force received and the flexibility of the wing structure of the UAV aircraft while in the air. From this goal, you can find out what benefits the UAV itself can produce, while others can find out the maximum flexibility of the aircraft structure so that it can be flown anywhere day or night. Also, the design can be done which aims to produce a structure that is more stable, and durable, and can meet objectives such as ease of implementation of the structure which can also be called stable if durable, not easily broken, tilted or shifted as long as the frame is used. Loading is one of the most important things in planning a wing structure. Error in load planning in the calculation will result in fatal errors in the results of the design of the structure. Therefore, the method used is an experimental method to design or design a fixed-wing UAV structure and calculate the flexibility of a predetermined aircraft frame structure in order to find out whether or not the frame is to be made an unmanned aircraft, then retrieve and collect data then made in the form of a result table testing to get a conclusion. In terms of this analysis will diseuss the flexibility that occurs in the aircraft wing structure in which the structure receives pressure while in the air using Autodesk Inventor Software. The results of this study will use Software where the results will be used as a reference. From the results made using Software, it will be seen which parts'receive the load from the pressure in the air with the strength received 0.100 MPa from a distance of 100 m. It can be seen that the biggest damage received at the base of the wing indicates that the red dot is the worst place to receive the load. In the simulation on this Software can be stated to have an accuracy method that is in accordance with the research procedure. To get accurate results, in this flexibility study must be able to determine how much stress, strain and deformation the wing receives when in the air by distinguishing the material used in order to obtain maximum flexibility. So that it can be seen that the most flexible material is ABS Plastic because the maximum deformation possessed by the material type is greater than that of Aluminium 6061 and stainless Steel which has a smaller maximum limit. : Autodesk Inventor, Analysis ofStasic, Fixed Wing, Pressure, static stress.

Item Type:	Thesis (Undergraduate)
Uncontrolled Keywords:	Autodesk Inventor, Analysis ofStasic, Fixed Wing, Pressure static stress
Subjects:	T Technology > TJ Mechanical engineering and machinery > TJ1425-1475 Lifting and pressing machinery
Divisions:	03-Faculty of Engineering > 21201-Mechanical Engineering (S1)
Depositing User:	Ichlasyah Aisyah
Date Deposited:	11 Aug 2025 07:30
Last Modified:	11 Aug 2025 07:30
URI:	http://repository.unsri.ac.id/id/eprint/182696

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