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Endah Yuniarti, Endah
Universitas Dirgantara Marsekal Suryadarma
Aerospace Engineering Humanities Chemical Engineering, Chemistry & Bioengineering Computer Science & IT Control & Systems Engineering Earth & Planetary Sciences Electrical & Electronics Engineering Energy Engineering Environmental Science Industrial & Manufacturing Engineering Library & Information Science Materials Science & Nanotechnology Mechanical Engineering Nursing Physics Social Sciences Transportation

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Initial Modelling of Bird Strike by Numerical Simulation in Varied L/D Ratio of Bird Geometry H, Simon Shindu; Sitompul, Sahril Afandi; Yuniarti, Endah
SENATIK STT Adisutjipto Vol 4 (2018): Transformasi Teknologi untuk Mendukung Ketahanan Nasional [ ISBN 978-602-52742-0-6 ]
Publisher : Sekolah Tinggi Teknologi Adisutjipto

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (699.363 KB) | DOI: 10.28989/senatik.v4i0.165

Abstract

This research studies influence of bird geometry on impact pressures during bird strike, namely Hugoniot and Stagnation pressure through initial modelling by numerical simulations. Bird geometry is capsule or cylinder with hemisphere end. The geometry is simulated with different L/D ratio, 1.4, 1.6, 1.8 and 2.0. Elastic-plastic hydrodynamic material model is used in simulation. Bird model simulation are using lagrangian method and initial velocities are 200 m/s. The results show variation of L/D ratio provide Hugoniot pressure 10-19 times higher than stagnation pressure in L/D = 1.4, 8-18 times in L/D = 1.6, 9-17 times in L/D = 1.8 and 4-16 times in L/D = 2. Hugoniot pressures show higher in ratio L/D = 1.8 and lower in ratio L/D = 1.6. Stagnation pressure show higher in ratio L/D = 2.0 and lower in ratio L/D 1.4.
ESTIMASI DISTRIBUSI BERAT SAYAP DAN DISTRIBUSI LIFT UNTUK OPTIMASI BENDING MOMENT DENGAN SISTEM FUEL TRANSFER PADA PESAWAT BOEING 737-500 Arifin, Mufti; Yuniarti, Endah; Sari, Rafika Arum; Said, Ahmad Akmal
JTK: JURNAL TEKNOLOGI KEDIRGANTARAAN Vol 4, No 2 (2019): JURNAL TEKNOLOGI KEDIRGANTARAAN
Publisher : JTK: JURNAL TEKNOLOGI KEDIRGANTARAAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (1101.347 KB) | DOI: 10.35894/jtk.v4i2.310

Abstract

Aside from being a manufacturer of lift force, a wing is functioning hold the load that occurs in the structure of the aircraft, such as the shear load, twist and bending. Of all the load the load bending is the greatest burden are received by the wings. Setting the load bending is one of the major factors in reducing the burden experienced by the wing. However, the optimal value indicated opposite between on land and in the air, to take advantage of the situation to use fuel system transfers the load alleviation. Fuel transfer load alleviation is a system that automatically move the fuel more in the tank at the time in part on land and are on the outside of the tank at the time in the air so that the effect of the load bending bending loads can be reduced, which generated as the result of addition between the weight distribution and the distribution of lift that occurs on the wings so as to calculate the bending data needed weight distribution and the distribution of lift on the wing. This research aims to know the weight distribution occurs on the wings of the Boeing 737-500. The value of the weight distribution and distribution of lift yield optimization moment on two States namely, on land and in the air with three variations of the fuel transfer that is, constant with a value of 40134.53 N, linear with a value of 48059.53 N, and the maximum value of 172386.50 N.
ANALISIS NUMERIK PENGARUH GEOMETRI BURUNG TERHADAP TEKANAN IMPAK PADA KASUS BIRD STRIKE DENGAN SMOOTHED PARTICLE HYDRODYNAMICS (SPH) MODEL Yuniarti, Endah; Sitompul, Sahril Afandi; Warsiyanto, Budi Aji
JTK: JURNAL TEKNOLOGI KEDIRGANTARAAN Vol 5, No 1 (2020): Jurnal Teknologi Kedirgantaraan
Publisher : JTK: JURNAL TEKNOLOGI KEDIRGANTARAAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (886.075 KB) | DOI: 10.35894/jtk.v5i1.426

Abstract

Penelitian ini mempelajari pengaruh geometri burung terhadap tekanan impak pada kasus tabrak burung, yaitu tekanan hugoniot dan stagnasi. Geometri burung berbentuk capsule atau silinder dengan kedua ujung setengah bola. Geometri disimulasikan dengan rasio L/D yang berbeda yaitu 1,5; 1,7; dan 1,9. Model material burung elastis, plastis, hidrodinamik digunakan pada simulasi. Simulasi model burung dilakukan dengan metode Smooth Particle Hydrodynamics (SPH) pada variasi kecepatan 100 m/s, 200 m/s, dan 300 m/s. Hasil simulasi menunjukkan dengan variasi rasio L/D diperoleh nilai tekanan Hugoniot jauh lebih tinggi sekitar 14-25 kali lipat tekanan stagnasi pada L/D = 1.5, 12-25 kali pada L/D = 1.7, dan 11-34 kali pada L/D = 1.9. Tekanan Hugoniot menunjukkan nilai yang meningkat dari L/D 1.5 sampai 1.9 pada kecepatan 100 m/s. Namun, untuk tekanan Hugoniot pada kecepatan 200 m/s menunjukkan nilai yang menurun dari L/D 1.5 sampai 1.9. Tekanan stagnasi rasio L/D 1.9 lebih rendah dibandingkan L/D 1.5 dan 1.7 pada kecepatan impak 100 dan 200 m/s.
Rancang Bangun Perangkat Lunak Database Dent and Buckle Chart Pada Pesawat Boeing 737-800 fahmins; muftiarifin; endahyuniarti
Jurnal Teknologi Kedirgantaraan Vol 6 No 1 (2021): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (2064.384 KB) | DOI: 10.35894/jtk.v6i1.28

Abstract

Pemeliharaan pada pesawat terbang harus tercatat rapi dan lengkap menurut CASR Part 145, dimana salah satu pencatatan pemeliharaan yaitu catatan pada setiap komponen yang mengalami kerusakan dan perbaikan. Semua dicatat berdasarkan lokasi komponen, tanggal ditemukan dan dokumen yang berkaitan dengan kerusakan dan perbaikan tersebut. Contoh catatan pemeliharaan adalah dent and buckle chart (DBC). Dent and buckle chart yaitu catatan kerusakan dan perbaikan yang telah dilakukan pada struktur pesawat terbang. Fungsi dari DBC ini yaitu untuk memudahkan dalam pencarian riwayat kerusakan dan perbaikan pada pesawat terbang. Penelitian ini berupa rancang bangun perangkat lunak database DBC, tujuannya memudahkan pencatatan DBC, dan penggunaannya dapat diakses di semua device seperti PC (Personal Computer) dan smartphone. Perangkat lunak ini berupa website yang diberi nama “Sysdnb” dan telah dibuat untuk mencatat kerusakan dan perbaikan yang ada pada pesawat tipe B737-800. Metode yang digunakan dalam penelitian ini adalah pertama mengumpulkan data catatan perbaikan dan kerusakan B737-800, kemudian membuat Sysdnb dan input data catatan ke database. Setelah selesai membuat Sysdnb dan data sudah ter-input adalah trial Sysdnb. Hasil trial menunjukkan pencatatan kerusakan dan perbaikan pada pesawat B737-800. Sysdnb ini berhasil dibuat untuk memudahkan personil lapangan dalam melakukan pencarian riwayat kerusakan dan perbaikan pada pesawat B737-800 dan keterbatasan dari sysdnb ini yaitu tetap harus membuka dokumen SRM secara manual. Abstract - Maintenance on an aircraft must be neatly and completely recorded according to CASR Part 145, where one of the maintenance records is a record of each component that is damaged and repaired. All are recorded based on the location of the component, date found and documents relating to the damage and repair. Examples of maintenance records are the dent and buckle chart (DBC). Dent and buckle chart is a record of damage and repairs that have been made to aircraft structures. The function of this DBC is to facilitate the search for a history of damage and repairs to aircraft. This research is in the form of DBC database software design, its purpose is to make it easier to record DBC, and its use can be accessed on all devices such as PCs (Personal Computers) and smartphones. This software is in the form of a website called "Sysdnb" and has been made to record the damage and repairs that exist on the type B737-800 aircraft. The method used in this study is to first collect the B737-800 repair and damage log data, then create a Sysdnb and input the log data to the database. After completing Sysdnb and the data has been input is a trial Sysdnb. The trial results show the recording of damage and repairs on the B737-800 aircraft. This system was successfully created to facilitate field personnel in searching for a history of damage and repairs on the B737-800 aircraft and the limitation of this system is that it still has to open SRM documents manually.
EFFECT OF FLAT AND HEMISPHERICALLY ENDED CYLINDER BIRD MODEL WITH FINITE ELEMENT MODELLING OF BIRD STRIKE Endah Yuniarti
Jurnal Teknologi Dirgantara Vol. 17 No. 1 Juni 2019
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2019.v17.a3061

Abstract

This research studies influence of bird model on impact pressures during bird strike, namely Hugoniot and Stagnation pressure through initial modelling by numerical simulations using finite element method. Finite element simulation of bird strike have primarily modelled the bird as either a flat or hemispherically ended cylinder. The geometry is simulated with different L/D ratio, 1.4, 1.6, 1.8 and 2.0. Elastic-plastic hydrodynamic material model is used in simulation. Bird model simulation are using lagrangian method and initial velocities are 100, 200 and 300 m/s. Simulation results of hemispherically ended cylinder bird models show variation of L/D ratio provide Hugoniot pressure 10-19 times higher than stagnation pressure in L/D = 1.4, 8-18 times in L/D = 1.6, 9-17 times in L/D = 1.8 and 4-16 times in L/D = 2. The Hugoniot pressure shows a lower value at an L/D ratio of 1.6 compared to other ratios and the Stagnation pressure is higher at L/D ratio 2. As for cylindrical bird model show variation of L/D ratio provide Hugoniot pressure 35-38 times higher than stagnation pressure in L/D = 1.4, 30-47 times in L/D = 1.6, 31-52 times in L/D = 1.8 and 28-48 times in L/D = 2. The Hugoniot pressure shows a lower value at an L/D ratio of 1.4 and 1.6 compared to other ratios and the Stagnation pressure is higher at L/D ratio 2.
Analisis Numerik Penyerapan Energi pada Sabot untuk Pengujian Bird Strike Riskha Agustianingsih; Sahril Afandi Sitompul; Endah Yuniarti; Rizky fitriansyah; Agus Bayu
Jurnal Teknologi Kedirgantaraan Vol 5 No 2 (2020): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (2431.956 KB) | DOI: 10.35894/jtk.v5i2.7

Abstract

abstrak - Pengujian Bird Strike dilakukan menggunakan alat SHPB (Split Hopkinson Pressure Bar) yang menembakkan sabot (wadah burung). Pada ujung alat SHPB, sabot akan dihentikan oleh stopper sehingga burung akan terlepas dan meluncur dengan bebas hingga mengalami tumbukan dengan komponen uji. Sabot harus memaksimalkan kecepatan burung ketika keluar (terlepas dari sabot). Berdasarkan persamaan impuls dan momentum, hal ini dapat diperoleh dengan meminimalkan waktu tumbukan sehingga gaya impulsnya akan meningkat. Tujuan penelitian ini adalah mengetahui waktu tumbukan, pola grafik Energy Absorption (EA), Peak Crushing Force (PCF), dan Mean Crushing Force (MCF). Dari parameter tersebut, maka diperoleh sabot yang diinginkan berdasarkan waktu tumbukan tersingkat, PCF dan MCF tertinggi, serta EA terendah. Simulasi dilakukan menggunakan perangkat lunak elemen hingga (Abaqus CAE) berdasarkan variasi material (AA6061-T6, S355, dan AISI 1340) sabot. Berdasarkan hasil dan pembahasan, diperoleh bahwa waktu tumbukan paling singkat dimiliki variasi material AISI 1340 dengan nilai 0.00071 s. EA terendah untuk variasi material dimiliki oleh AISI 1340, yaitu sebesar 2.51 kJ. PCF tertinggi untuk variasi material dimiliki oleh material AISI 1340, yaitu 466 kN. Ditentukan bahwa berdasarkan nilai waktu (t) paling singkat, PCF, MCF paling tinggi, dan EA paling rendah, maka diperoleh material AISI 1340 sebagai material yang diinginkan karena paling berpengaruh terhadap peningkatan kecepatan burung setelah keluar dari sabot.
Estimasi Gaya Dorong Dari Motor Brushless Dengan Variasi Propeller Untuk Pesawat Model X-UAV Mini Talon Dengan Menggunakan Pengukur Massa Ananda Rafi Rijalul Awwal; Mufti Arifin; Endah Yuniarti
Jurnal Teknologi Kedirgantaraan Vol 5 No 2 (2020): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (370.591 KB) | DOI: 10.35894/jtk.v5i2.16

Abstract

One that affects aircraft performance is the thrust. The thrust is determined according to the requirements of the aircraft itself. This study uses a thrust test stand that uses a mass gauge as a thrust gauge, using two brushless motors and five propellers to determine the optimal thrust for X-UAV Mini Talon aircraft flying missions. The thrust required by the X-UAV Mini Talon aircraft - is known to be 0.6755 N for cruise flights and 4.979 N for take-off aircraft. After testing, the smallest thrust is produced by the configuration of the DYS 2826-13 brushless motor with a 5x3 inch propeller, while the biggest thrust by the RacerStar BR2212 brushless motor with a 10x6 inch propeller. Compared to calculations with propeller static thrust equation, the difference in thrust in testing with propeller static thrust ranges from 15% to 25%. Therefore, the optimal configuration for flying cruising is the DYS 2826-13 brushless motor with a 5x3 inch propeller, which produces a thrust of 0.988 N. Then, for the optimal configuration take-off is the Brushless DYS 2826-13 with a 9x5 inch propeller, which results in a thrust of 6,151. The configuration above was chosen because it is more efficient, with smaller current requirements compared to other configurations with more or less equivalent thrust.
Analisis Numerik Part Spar Pada Sub System Wing To Fuselage Joinner Assembly Pesawat Berkategory Utility Menggunakan Metode Elemen Hingga Muhammad Jayadi; Sahril Afandi; Agus Suprianto; Nurhadi Pramana; Endah Yuniarti
Jurnal Teknologi Kedirgantaraan Vol 6 No 1 (2021): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (2021.225 KB) | DOI: 10.35894/jtk.v6i1.24

Abstract

Pesawat Utility adalah kategori pesawat udara yang memiliki konfigurasi tempat duduk kurang dari 9 yang tidak termasuk tempat duduk pilot, Maximum Takeoff Weight 12.500 pounds serta memiliki kemampuan pesawat dapat bermanouver layaknya akrobatik yang di batasi pada sudut 60 sampai 90 derajat[2]. Berdasarkan CASR subbagian 23.305, struktur harus sanggup menahan beban limit tanpa merugikan dan membuat kerusakan permanen. Selain itu struktur juga harus mampu menahan beban ultimate tanpa kegagalan paling tidak selama 3 detik, kecuali kegagalan lokal atau ketidakstabilan struktur antara beban limit dengan beban ultimate yang dapat diterima jika struktur mampu menopang beban ultimate paling tidak selama 3 detik[2]. Penelitian ini melakukan analisis numerik part spar untuk pesawat berkategori utility dengan load sebesar 6G menggunakan material komposit. Selain itu dilakukan proses reduksi berat spar berdasarkan variasi jumlah lamina/ply dengan metode ply drop-off laminate. Tujuan Penelitian ini untuk mengetahui keamanan struktur berdasarkan kriteria kegagalan dan mendapatkan berat yang optimal pada spar. Proses penyelesaian masalah menggunakan metode elemen hingga dengan bantuan software CAE. Penelitian dilakukan pada kondisi statik dengan asumsi pembenanan gaya angkat yang terjadi pada spar. Perhitungan gaya angkat dilakukan dengan metode Schrenk. Tegangan tertinggi terdapat pada arah transversal atau arah tegak lurus serat setelah dilakukan optimisasi sebesar 301.7 MPa. Optimisasi menghasilkan pengurangan massa sebesar 30.41% dari sebelum optimisasi. Berat spar yang optimal sebesar 47.82 kg. Hasil kriteria kegagalan Tsai-Hill menghasilkan struktur spar tersebut aman untuk digunakan.
Analisis Numerik Part Bulkhead Pada Sub System Wing To Fuselage Joinner Assembly Pesawat Aerobatik Menggunakan Metode Elemen Hingga Enggar Kristian; Agus Suprianto; Nurhadi Pramana; Sahril Afandi; Endah Yuniarti
Jurnal Teknologi Kedirgantaraan Vol 6 No 1 (2021): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (1420.007 KB) | DOI: 10.35894/jtk.v6i1.34

Abstract

Analisis rancangan bulkhead dilakukan untuk memperoleh geometri terbaik untuk mencari berat yang efisien dengan mengubah geometri bentuk pada bulkhead yang merupakan sub system wing to fuselage untuk pesawat berkategori aerobatik dan berat yang optimal yang memenuhi persyaratan regulasi FAR 23 dan mengetahui respon distribusi tegangan, bending yang dihasilkan  dan kriteria kegagalan struktur berdasarkan variasi geometri bentuk bulkhead. Pada penelitian ini untuk analisis statik bulkhead untuk pesawat berkategori aerobatik menggunakan material Aluminium Alloy 7075-T6 dan menggunakan metode pendekatan Schrenk untuk menghitung beban eksternal distrbusi gaya angkat pada sayap. Selain itu dilakukan proses optimisasi berat bulkhead berdasarkan metode pendekatan topologi yaitu perubahan geometri bentuk pada bulkhead untuk mereduksi berat, sudut insiden spar yang berbeda dan menghitung magin of safety. Proses penyelesaian masalah menggunakan perangkat lunak metode elemen hingga (Abaqus CAE). Optimisasi topologi pada part bulkhead sudut insidet 0° dan 4° menghasilkan volume yang berkurang pada benda sehingga mereduksi berat, tetapi nilai dari margin of safety MS = 0. The bulkhead design analysis was carried out to obtain the best geometry to find an efficient weight by changing the shape geometry of the bulkhead which is a sub-system of the wing to the fuselage for an aircraft categorized as aerobatics and an optimal weight that meets the requirements of FAR 23 regulations and sees the stress distribution response, the resulting bending and structural failure criteria based on the geometric variation of bulkhead shapes. In this study, to analyze the bulkhead static for an aerobatic category aircraft using Aluminum Alloy 7075-T6 material and using the Schrenk Approximation method to calculate the external distribution load of lift force on the wing. In addition, the optimization of bulkhead weight based on the topological approach method is to change the shape geometry of the bulkhead to reduce weight, in different spar incidents and calculate margin of safety. The problem solving process uses finite element method software (Abaqus CAE). Topological optimization of the bulkhead part with an incidence angle of 0 ° and 4 ° results in a reduced volume of the object so that it reduces weight, but the value of the margin of safety MS = 0.  
Analisis Pengaruh High Pressure Compressor Rotor Clearance Terhadap Exhaus Gas Temperature Margin pada CFM56-7 Wildan Sofary Darga; Edy K. Alimin; Endah Yuniarti
Jurnal Teknologi Kedirgantaraan Vol 6 No 2 (2021): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (583.907 KB) | DOI: 10.35894/jtk.v6i2.35

Abstract

Abstract - Exhaust Gas Temperatue is an parameter where the hot gases’s temperature leave the gas turbine. Exhaust gas temperature margin is the difference between highest temperature at take off phase with redline on indicator (EGT Margin 0C = EGT Readline – EGT Take). EGTM is one of any factor to determine engine performance. A good perfomance of an engine when it has a big margin (EGTM), during operation of an engine the EGTM could decrease untill 0 (zero). So many factors could affect EGTM deteroration there are: distress hardware such as airfoil erosion, leak of an airseals, and increase of clearance between tip balde and shroud. Increase of clearance happens in high pressure compressor rotor clearance. In CFM56-7 have 9 stage(s) of high pressure compressor and each stage give the EGT Loses. The calculation of EGT Effect/Losses is actual celarance – minimum clearance x 1000 x EGT Effect °C, where actual clearance define by the substraction of outside diameter’s rotor with inside diamete r’s shroud, minimum clearance define in the manual, 1000 is adjustment from mils/microinch to inch, and EGT Effect is temperature that define in the manual. The analysist had done with 6 (six) engine serial number and proceed by corelation that shown linkage between clearance and EGT Effect, the corelation is strong shown the result of corelation (r) is 0.994275999 or nearest 1.
Co-Authors Aditia Kusuma Wibawa Agus Bayu Alimin, Edy K. amat chaeroni Ananda Rafi Rijalul Awwal Ari Suryo O Ayu Martina, Ayu Budi Aji W Budi Aji Warsiyanto Budi Aji Warsiyanto Dwi Juniarsah, Fahri Edy K. Alimin Edy Suwondo, Edy Enggar Kristian fahmins FORTUNE JR OMBUH Freddy, Franciscus Ganda Tri Alam H, Simon Shindu Haidar Hardiansyah Israq Mifan Junaidi Jauharul Akfiya sudjaelan Luh Putu Ratna Sundari muftiarifin Muhammad Rayhan Zhafrando Noval Erlangga Nurhadi Pramana PANGGIH JOGO MUSTIKO Pangihutan Tambunan Riskha Agustianingsih Rizky fitriansyah Said, Ahmad Akmal Sari, Rafika Arum Septian, Diaz Setiyawati, Defi Simon Shindu H Simon Sindhu Hendrajaja Sitompul, Sahril Afandi Somadi, Ridho Misbahudin Syaiful Rifki Warsiyanto, Budi Aji Wildan Sofary Darga