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Budi Aji Warsiyanto
Universitas Dirgantara Marsekal Suryadarma
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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.
The Effect of Cross-section and Elliptical Hole Ratio on Crashworthiness Parameters of Crash-Box Structure Budi Aji Warsiyanto
Jurnal Teknologi Dirgantara Vol 19, No 1 (2021)
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2021.v19.a3408

Abstract

The thin-walled column structure or crash-box with metal material and consisting of multi-cell were found to be much more efficient in energy absorption than single-cell under axial impact loads. In this study, a numerical analysis was performed using the Abaqus finite element method for the cross-section differences in thin-walled column structures. The cross-section differences are compared to get a configuration that complies with the indicator parameters using the complex proportional assessment (COPRAS) method. The chosen cross-section configuration is further enhanced by creating elliptical holes with different diameter ratios. The results show that the thin-walled column structure with nine-cell cross-section accompanied by an elliptical hole ratio of 0.3 indicates the potential corresponding to the indicator parameters for the crashworthiness application.
Dynamic response of the wing during UAV collision Budi Aji Warsiyanto
Jurnal Teknologi Dirgantara Vol 19, No 1 (2021)
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2021.v19.a3514

Abstract

An airborne collision between civil Unmanned Aerial Vehicles (UAVs) and manned aircraft is a potential threat to aircraft operation safety. In this paper, the UAV collision test was performed on a commuter aircraft wing section to investigate the dynamic response of this primary operation component. The projectile was a 735 g drone named ‘Mavic’. Explicit dynamic code ABAQUS was employed to simulate the collision process based on the difference of collision scenarios to assess the hazard. The results showed that 735 g drone impact at the aircraft maximum approach flap and cruising speed could cause some damage on the wing front spar and the situation is more serious than 910 g bird strike in which the hardness of drone components rather than kinetic energy is a decisive factor. The lithium-ion battery penetrated the airframe which may be a potential source of ignition.
The effect of Impact Angle on Dynamic Response of 19 Passenger Commuter Aircraft Windshield against Bird Strike Budi Aji Warsiyanto
Jurnal Teknologi Dirgantara Vol 19, No 2 (2021)
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2021.v19.a3560

Abstract

This paper's objective was to determine the dynamic response of a 19 passenger commuter aircraft windshield to impact angle variations. The phenomenon was performed using the finite element method, and the smoothed particle hydrodynamics (SPH) was chosen as a method for modeling bird material. The elastic-plastic polymethyl methacrylate (PMMA) material with the maximum principal strain failure criterion was used to model the windshield's dynamic response. The variation of the impact angle consists of 15°, 0°, -8°, and -15°, which are measured of the longitudinal axis of the aircraft. The simulation result showed that the impact angle that causes the windshield's dynamic response in the elastic, plastic deformation, and the greatest failure is the angle -15°. The upper end of the windshield (fixed) is the weakest part due to the stress concentration.
Analisis tabrak burung pada windshield pesawat komuter 19 penumpang dengan variasi perbedaan massa burung B A Warsiyanto; A Nurrohmad*; R Fitriansyah; S A Sitompul; A B Utama
Prosiding Seminar Nasional Ilmu Teknik Dan Aplikasi Industri Fakultas Teknik Universitas Lampung Vol. 3 (2020)
Publisher : Fakultas Teknik Universitas Lampung

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (756.092 KB) | DOI: 10.23960/prosidingsinta.v3i.11

Abstract

Dalam pengembangan pesawat terbang supaya laik untuk dioperasikan perlu dilakukan proses sertifikasi. Rangkaian kegiatan sertifikasi ini dimaksudkan untuk menjamin bahwa pesawat aman dan memiliki resiko kecelakaan sekecil mungkin. Salah satu tahapan yang harus dilakukan pada proses sertifikasi pesawat 19 penumpang sesuai standar Civil Aviation Safety Regulation (CASR) 23 adalah uji tabrak burung, khususnya pada komponen windshield. Penelitian ini bertujuan untuk mengetahui respon dinamik windshield terhadap variasi massa burung. Pemodelan numerik Metode Elemen Hingga eksplisit-dinamik digunakan untuk mensimulasikan fenomena tabrakan burung. Material polimetil metakrilat plastis-elastis (PMMA) dengan kriteria kegagalan maximum principle strain digunakan untuk memodelkan respons dinamis windshield. Pemodelan numerik divalidasi dengan analisis eksperimental pada kasus serupa yang kemudian digunakan untuk mengetahui pengaruh variasi massa burung terhadap respons dinamis windshield.  Hasil penelitian diperoleh bahwa massa burung yang menyebabkan respon dinamik windshield dalam keadaan elastis, deformasi plastis, dan kegagalan terbesar adalah massa burung sebesar 1,81 kg. Windshield area paling atas  merupakan bagian terlemah akibat tingginya konsentrasi tegangan.
Pembelajaran Dasar Teknologi Penerbangan Melalui Praktikum Fisika Sekolah Menengah Atas Mufti Arifin; Freddy Franciscus; Budi Aji Warsiyanto; Amat Chaeroni; Syarifah Fairuza; Ayu Martina; Muhammad Hadi Widanto; Rafika Arum Sari
Bubungan Tinggi: Jurnal Pengabdian Masyarakat Vol 6, No 1 (2024)
Publisher : Universitas Lambung Mangkurat

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.20527/btjpm.v6i1.9534

Abstract

Mata pelajaran fisika di Sekolah Menengah Atas (SMA) membutuhkan praktikum untuk meningkatkan pemahaman siswa tentang konsep teori fisika dan aplikasinya, akan tetapi terdapat beberapa hambatan diantaranya butuh contoh konkret, keterbatasan laboratorium, keterbatasan alat dan bahan praktikum, alokasi waktu yang terbatas, dan pelaksanaan praktikum yang jarang. Pengabdian kepada Masyarakat (PkM) oleh Fakultas Teknologi Kedirgantaraan Universitas Dirgantara Marsekal Suryadarma dilaksanakan dari tanggal 29 November 2022 sampai dengan 19 Januari 2023 dalam bentuk praktikum fisika ke Madrasah Aliyah (MA) Sahid Bogor, SMA Bintara Depok, SMAK Ign. Slamet Riyadi Jakarta, dan SMAN 109 Jakarta. PkM ini bertujuan untuk mengenalkan teknologi penerbangan dan menawarkan solusi beberapa hambatan tersebut. Kegiatan dilaksanakan dalam 8 (delapan) sesi praktikum dengan tiap sesi terdiri dari 10 (sepuluh) modul dan tiap kelompok siswa bergiliran melaksanakan praktikum yang dipandu oleh dosen dan mahasiswa. Hasil PkM ini menunjukkan bahwa tim pelaksana melalui kegiatan PkM berhasil memberi pengalaman praktikum kepada 259 peserta sebanyak 5-8 modul dalam waktu 90-120 menit dan mendorong ketertarikan 63% peserta pada praktikum fisika. Modul dengan alat praktikum sederhana dan cara penyampaian yang menarik terbukti mudah dipahami oleh siswa meskipun masih perlu pengembangan dengan penambahan waktu dan jenis modul serta pengaturan pergantian antar kelompok yang lebih baik.Physics subject in senior high school requires practicum to increase students' understanding of the theoretical concepts of physics and their applications, but there are several obstacles including the need for concrete examples, limited laboratories, lack of practicum tools and materials, limited time allocation, and a rare practicum implementation. Community service by the Faculty of Aerospace Technology Marshal Suryadarma University was carried out from 29 November 2022 to 19 January 2023 in the form of physics practicum at Madrasah Aliyah (MA) Sahid Bogor, SMA Bintara Depok, SMAK Ign. Slamet Riyadi Jakarta, and SMAN 109 Jakarta aim to introduce aviation technology and offer solutions to some of these obstacles. The activity was carried out in 8 practicum sessions with each session consisting of 10 modules and each group of students took turns carrying out practicums guided by lecturers and students. The results of this PkM show that the implementing team, through PkM activities, succeeded in providing practical experience to 259 participants with 5-8 modules in 90-120 minutes and encouraging 63% of participants' interest in physics practicum. Modules with simple practicum tools and interesting delivery methods are proven to be easy for students to understand, although they still need development by addition of time and types of modules as well as better arrangements for switching between groups.
Analisis Respon Dinamik Windshield Pesawat Komuter 19 Penumpang Terhadap Fenomena Bird Strike Menggunakan Metode Coupled Eulerian-Lagrangian (CEL) Tambunan, Pangihutan; Warsiyanto, Budi Aji; Yuniarti, Endah; Fitriansyah, Rizky
Jurnal Mahasiswa Dirgantara Vol. 2 No. 2 (2023): Jurnal Mahasiswa Dirgantara
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jmd.v2i2.26

Abstract

Fenomena tabrak burung sering terjadi pada saat operasi pesawat terbang yang menyebabkan kerusakan fatal pada struktur pesawat dan mengancam keselamatan operasi penerbangan. Kerusakan struktur pesawat dapat menyebabkan kecelakaan dan korban jiwa. Untuk menunjang keselamatan penumpang pesawat terbang, setiap komponen pada pesawat harus lulus uji. Windshield merupakan komponen yang harus diuji untuk memenuhi persyaratan sertifikasi pada kasus bird strike berdasarkan regulasi keselamatan penerbangan sipil atau Civil Aviation Safety Regulation (CASR) subbagian 23.775. Tujuan tugas akhir ini adalah untuk mengetahui respon dinamik windshield terhadap variasi parameter tumbukan dan kegagalan material windshield. Pada simulasi ini, bentuk material dari burung menggunakan jenis EOS Tabular dan material windshield menggunakan polimetil metakrilat. Untuk pemodelan windshield dan burung menggunakan metode Coupled Eulerian-Lagrangian (CEL). Pada variasi kecepatan, parameter tumbukan yang menyebabkan respon dinamik windshield berupa deformasi elastis, plastis, kegagalan paling besar terjadi pada kecepatan 80 m/s dan pada variasi sudut, kegagalan paling besar terjadi pada sudut tumbukan -150. Area lubang baut bagian atas lebih rentan terjadi kegagalan material dikarenakan adanya konsentrasi tegangan.
Pelatihan Proses Manufaktur Material Komposit dalam Meningkatkan Keterampilan Siswa SMKN 4 Depok untuk Penyelarasan Pendidikan dengan Tren Industri Muhammad Hadi Widanto; Muhamad Jayadi; Riskha Agustianingsih; Rafika Arum Sari; Budi Aji Warsiyanto
Jurnal Bakti Dirgantara Vol. 1 No. 2 (2024): Jurnal Bakti Dirgantara
Publisher : Universitas Dirgantara Marsekal Suryadarma

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35968/36512c82

Abstract

Pelatihan vokasi bagi siswa Sekolah Menengah Kejuruan (SMK) memegang peran sentral dalam mempersiapkan generasi muda untuk menghadapi kebutuhan pasar kerja yang semakin kompleks. Disamping itu, Material komposit adalah jenis material yang menawarkan kekuatan, ringan, dan ketahanan yang luar biasa. Industri otomotif, penerbangan, energi terbarukan, dan konstruksi semuanya memanfaatkan material komposit untuk mencapai performa yang optimal.Kegiatan pengabdian Masyarakat dengan memberikan pelatihan tentang material komposit merupakan salah satu upaya untuk menyelaraskan luaran kompetensi pendidikan dengan kebutuhan tenaga kerja. Metode pelatihan dilakukan dengan pemaparan dan dilanjutkan dengan praktikum untuk memberikan pemahaman yang mendalam terkait material komposit. Dari hasil pelatihan menunjukkan peningkatan pengetahuan siswa oleh siswa. Hasil kepuasan mitra yaitu 90% siswa setuju bahwa materi mudah dipaham. Adapun hal yang disenangi pada pelatihan dimana 54% karena materi mudah dipahami, 31% karena ada praktikum, dan 15% karena menambah pengetahuan. Vocational High School (SMK) students plays a central role in preparing the younger generation to face the increasingly complex needs of the job market. In addition, composite materials are a type of material that offers exceptional strength, lightweight, and durability. The automotive, aviation, renewable energy, and construction industries all utilize composite materials to achieve optimal performance. Community service activities by providing training on composite materials are an effort to align educational competency outcomes with workforce needs. The training method is carried out by exposure and continued with practicum to provide a deep understanding of composite materials. The results of the training showed an increase in student knowledge by students. The results of partner satisfaction are 90% of students agree that the material is easy to understand. The things that are liked in the training where 54% because the material is easy to understand, 31% because there is a practicum, and 15% because it adds knowledge.
ANALISIS LIFE CYCLCE STRUKTUR MAIN LANDING GEAR UAV DENGAN MATERIAL ALUMINIUM BERDASARKAN VARIASI KECEPATAN LANDING Ajie Erlangga Antariksa; Budi Aji Warsiyanto; Syarifah Fairuza
Jurnal Teknologi Kedirgantaraan Vol 9 No 2 (2024): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v9i2.111

Abstract

Main landing gear is a component in UAVs that have support abilities to take offand landing. Repeated loads occur during UAV landings, impact of these cyclic loads can leadto fatigue failure in the main landing gear. The life cycle analysis aims to determine the lifespanof the main landing gear based on the influence of material variations and landing speedvariations. The materials considered are Al 6061 T6, Al 2024 T3, and Al 7075 T6, with landingspeed variations of 4 m/s, 6 m/s, 8 m/s, and 10 m/s. In this research, dynamic loading analysisand cyclic load analysis were performed on the UAV's main landing gear, modeled in the formof a leaf spring. Numerical analysis was conducted using finite element-based software. In thedynamic loading analysis results for landing speed variations, a speed of 4 m/s yielded amaximum stress value of 236,1 MPa and a maximum displacement of 2,949 mm, while aspeed of 10 m/s resulted in a maximum stress value of 308,8 MPa and a maximumdisplacement of 6,482 mm. In the dynamic loading analysis with material variations, thematerial Al 2024 T3 exhibited a maximum stress value of 362,6 MPa and a maximumdisplacement of 4,938 mm. In the cyclic load analysis, Al 6061 T6 had a minimum fatigue lifeof 659.060 cycles at a speed of 4 m/s and 6.786,6 cycles at a speed of 10 m/s. Al 2024 T3showed a minimum fatigue life of 3.308.100 cycles at a speed of 4 m/s and 16.739 cycles ata speed of 10 m/s. Al 7075 T6 had a minimum fatigue life of 982.900 cycles at a speed of 4m/s and 8.795,9 cycles at a speed of 10 m/s.
Analisis Kekuatan Struktur Sayap Pesawat Udara Nir Awak Pasopati Dengan Variasi Material Dan Ketebalan Menggunakan Metode Elemen Hingga Sultan Nugraha A; Budi Aji Warsiyanto; Muhammad Hadi Widanto; Aswan Tajuddin
Jurnal Teknologi Kedirgantaraan Vol 9 No 2 (2024): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v9i2.183

Abstract

PUNA Pasopati, the wing is an important part to generate lift. However, the magnitude of the lift force must be able to be resisted by the wing structure. Therefore, the purpose of this study is to determine the most optimal material and thickness of the spar structure, ribs, and front reinformence leading edge on the PUNA Pasopati wing. This research conducted static tests on the wing structure with skin construction, front reinforcement leading edge, ribs, and spars using the finite element method. static tests were conducted with material and thickness variations on the spar, ribs, and front reinforcement leading edge structures. In material variations, carbon fiber reinforced plastic is stronger than plywood. Displacement on the wing with carbon fiber reinforced plastic material is 61.03% smaller than plywood, but the wing with plywood material weighs 68.43% lighter than carbon fiber reinforced plastic. However, the plywood material gets a safety factor value of 1.15 which means below the limit of the safety factor value of 1.5. Thus, the wing with carbon fiber reinforced plastic material for PUNA Pasopati is more optimal than plywood. The higher the thickness of the ribs, spar, front reinforcement leading edge structure, the smaller the displacement and stress on the wing. Although the 1 mm thickness has the highest displacement and stress values, it still has a safety factor value above the limit. Thus, a thickness of 1 mm is the most optimal.
Co-Authors A B Utama A Nurrohmad* Ajie Erlangga Antariksa Algazali, Febri amat chaeroni Aswan Tajuddin Ayu Martina Candra Pranoto Endah Yuniarti, Endah Eros Ray Fairuza, Syarifah fitriansyah, Rizky Freddy, Franciscus muftiarifin Muhamad Jayadi Muhammad Hadi Widanto nugraha, sultan R Fitriansyah Rafika Arum Sari Riskha Agustianingsih S A Sitompul Sahril Afandi S Simon Sindhu Hendradjaja Sitompul, Sahril Afandi Sultan Nugraha A Tambunan, Pangihutan