ANALISIS INTERAKSI FLUIDA DAN STRUKTUR PADA UAV STTA MALE GENERASI 1 DENGAN METODE FLUID STRUCTURE INTERACTION SATU ARAH

Rizal Hayat, Khairul (2023) ANALISIS INTERAKSI FLUIDA DAN STRUKTUR PADA UAV STTA MALE GENERASI 1 DENGAN METODE FLUID STRUCTURE INTERACTION SATU ARAH. Thesis thesis, Institut Teknologi Dirgantara Adisutjipto.

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Abstract

There are several types of UAVs that have been developed, one of which is the STTA MALE GENERATION 1 UAV by the academic community of the Adisutjipto Dirgantara Institute of Technology with its mission of surveillance. In its manufacture, starting with the process of making model drawings with CATIA, the process of analyzing the aircraft Aerodynamics, Structure, Flight Performance, Stability, and Flight Control, then the Manufacturing process includes selecting materials until the manufacturing process. For the FSI phenomenon itself, there are solutions for the solution which can be divided into the monolithic method Fully coupled, Simultaneous and the partition method Stragged, iteraive Paik, K.J., 2010. The monolithic method combines fluid and structural equations and is solved simultaneously. The partition method solves each field separately and the variables from the solution are continued iteratively from one field to another until the results converge. The partition method is divided into two methods, namely One-Way Coupled and Two Way Coupled. For the analysis of the structure itself, it can be iterated with the FSI method. One-Way Coupled is one of the suitable FSI methods where the fluid is solved only for the pressure force, and the pressure force is then applied to the structure to get the stress. Changes in flow rate are assumed to be absent or ignored during deformation of the structure during fluid analysis. Likewise, it is assumed that no displacements/deformations are produced during fluid analysis. From the results of calculations and discussion, the authors obtained several conclusions that can be drawn from the simulations carried out on the 1st Generation STTA MALE UAV wing, namely the highest stress distribution that occurs on the 1st Generation STTA MALE UAV wing of 21.355 MPa when the conditions are given a load factor of 3 based on the requirements structure safety level, carried out at a speed of 41 m/s. Maximum deformation occurred on the wings of the UAV STTA MALE Generation 1 along the wings, which were 3,522 mm after carrying out simulations under 3 times the aircraft load. From the simulation it can be concluded that the structure is still safe with a Margin of safety MS 39.6375 ≥ 0.

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