Optimasi Ukuran Spar Pada Pesawat Single Engine Six Seater Cessna 206

Taufiqurrochman, Fayyadh (2020) Optimasi Ukuran Spar Pada Pesawat Single Engine Six Seater Cessna 206. Undergraduate thesis, Institut Teknologi Sepuluh Nopember.

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Abstract

Terdapat beberapa jenis pesawat terbang dapat memenuhi fungsi sebagai pesawat angkut dan pesawat sipil (penumpang). Cessna 206 banyak digunakan untuk mengangkut barang untuk daerah terpencil. Karena fungsi lain dari Cessna 206 sebagai pesawat terbang pengankut barang, maka jika berat dari struktur pesawat dapat dikurangi, nilai dari beban angkut dapat bertambah. Salah satu cara mengurangi berat dari struktur pesawat adalah optimasi pada struktur sayap. Pada tahap awal simulasi yang digunakan adalah Fluid CFX dimana pada simulasi ini akan didapatkan distribusi tekanan yang kemudian akan menjadi gaya angkat pada sayap pesawat pada simulasi static structural. Hasil dari simulasi tersebut didapatkan bahwa nilai stress pada front dan rear spar mengalami penurunan dengan posisi yang semakin menjauh dari fuselage. Berdasarkan hasil simulasi ini, didapatkan kesimpulan bahwa dapat dilkuakan optimasi ukuran dari kedua spar. Simulasi dilakukan pada 5 tinggi retain tip end web untuk masing-masing front dan rear spar dengan total 25 buah kombinasi simulasi. Hasil dari optimasi didapatkan bahwa tinggi tip end web optimum untuk front spar sebesar 103,5551 mm dan rear spar sebesar 19,2 mm. Dengan melakukan permodelan ulang susai optimasi didapatkan masa dari semi span sayap Cessna 206 berkurang sebesar 21,84 Kg. Defleksi maksimum pada model hasil optimasi didapatkan sebesar 0,0143 m dengan ratio defleksi-bentang sayap sebesar 0,00259. Nilai dari aeroelasticity pada model hasil optimasi didapatkan sebesar 0,1930. Tegangan maksimum pada struktur model hasil optimasi naik menjadi 118 Mpa sedangkan nilai life berkurang menjadi 17.369.000 cycle.==================================================================================================================
Airplane is one kind of transportation which can be use to
travel either close or far distance in short time. Based on the purpose of the use, airplane is divided in to some categories which is passenger plane, military plane, experimental plane, and cargo plane. There are some airplane that can be use as either passenger plane or cargo plane at the same time. One of the manufacturer of the said airplane is Cessna. Cessna itself has been manufactured a lot of small size passenger airplane. One of the airplane that is manufactured by Cessna is Cessna 206 in which this airplane is categorized as a single engine, general aviation aircraft with fixed landing gear. Cessna 206 is often used as a cargo airplane for a remote place. The example of using Cessna 206 as a cargo airplane to remote place can be seen in mining industry. Because of this secondary function of Cessna 206 the more weight it can carries is the better, therefore if we can reduce the weight of the structure then we can increase the cargo weight. One of many ways to reduce the structure weight is by optimizing the wing structure.
The first step on the simulation is using Fluid CFX to find the pressure distribution on the semi span which later will be use as the load on the semi span in static structural simulation. The result of the simulation shows that the value of the stress either on front or rear spar is decrease within the further distance from the fuselage. Based on the result of the siumulation, it is conclude that size optimization can be done on the spar. The simulation is run on 5 different retain tip end web for each spar, front and rear spar with a total combination of 25 simulation.
The optimization result is that the optimum tip end web for front spar is 103,5551 mm and rear spar is 19,2 mm. By running the simulation with the model based on optimization result, the weight experience 21,84 Kg decrease. Maximum deflection on the optimized model is 0,0143 m with span deflection ration of 0,00259. The aeroelasticity value for the optimized model is 0,1930 and the maximum stress occur in the model increase to 118 MPa while the life value decrease to 17.369.000 cycle.

Item Type:	Thesis (Undergraduate)
Uncontrolled Keywords:	Cessna 206, tegangan, Aeroelasticity, spar, web, defleksi Cessna 206, stress, Aeroelasticity, Spar, Web, Deflection
Subjects:	T Technology > TL Motor vehicles. Aeronautics. Astronautics > TL671.9 Airplanes--Maintenance and Repair
Divisions:	Faculty of Industrial Technology and Systems Engineering (INDSYS) > Mechanical Engineering > 21201-(S1) Undergraduate Thesis
Depositing User:	Fayyadh Taufiqurrochman
Date Deposited:	04 Aug 2020 04:36
Last Modified:	04 Aug 2020 04:36
URI:	http://repository.its.ac.id/id/eprint/76897

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