Article Per Year (5 Year)
p-Index From 2020 - 2025
3.51
P-Index
This Author published in this journals
All Journal E-Dimas: Jurnal Pengabdian kepada Masyarakat Jurnal Teknologi Dirgantara Jurnal Teknologi Kedirgantaraan (JTK) Bubungan Tinggi: Jurnal Pengabdian Masyarakat Jurnal Bakti Bagi Bangsa Prosiding Seminar Nasional Hasil Penelitian Sains, Teknik dan Aplikasi Industri Fakultas Teknik Universitas Lampung Eduvest - Journal of Universal Studies Jurnal Mahasiswa Dirgantara Jurnal Bakti Dirgantara Indonesian Journal of Aerospace
Budi Aji Warsiyanto
Universitas Dirgantara Marsekal Suryadarma
Religion Aerospace Engineering Agriculture, Biological Sciences & Forestry Arts Humanities Astronomy Chemical Engineering, Chemistry & Bioengineering Civil Engineering, Building, Construction & Architecture Computer Science & IT Control & Systems Engineering Decision Sciences, Operations Research & Management Economics, Econometrics & Finance Education Electrical & Electronics Engineering Engineering Environmental Science Health Professions Industrial & Manufacturing Engineering Languange, Linguistic, Communication & Media Materials Science & Nanotechnology Mechanical Engineering Neuroscience Physics Social Sciences Transportation Other

Published : 20 Documents Claim Missing Document
Claim Missing Document
Check
Articles

Found 20 Documents
Search

 1   2 
Peningkatan Pengetahuan dan Praktik Manufaktur Material Komposit untuk Siswa Sekolah Menengah Kejuruan Muhammad Hadi Widanto; Muhamad Jayadi; Riskha Agustianingsih; Budi Aji Warsiyanto; Rafika Arum Sari
E-Dimas: Jurnal Pengabdian kepada Masyarakat Vol 16, No 1 (2025): E-DIMAS
Publisher : Universitas PGRI Semarang

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.26877/e-dimas.v16i1.19894

Abstract

Penyelarasan keterampilan siswa SMK vokasi dengan kebutuhan industri sangat krusial untuk memastikan relevansi dan kesiapan tenaga kerja di industri penerbangan salah satunya pada pemanfaatan Pesawat Terbang Tanpa Awak (PTTA). Material komposit merupakan material yang sangat populer digunakan industri tersebut karena kekuatan yang tinggi dan berat yang ringan. Kegiatan pengabdian masyarakat di SMK Penerbangan Bogor berperan penting dalam menjembatani kesenjangan tersebut dengan fokus pada peningkatan pengetahuan dan keterampilan siswa dalam penggunaan material komposit. Melalui pelatihan intensif yang mencakup teori dasar serta praktik langsung, siswa mendapatkan pemahaman mendalam tentang karakteristik dan aplikasi material komposit, yang merupakan komponen esensial dalam industri penerbangan modern. Metode pengabdian dilaksanakan dengan memberikan materi dilanjutkan dengan praktikum pembuatan benda dari material komposit dan kuesioner. Dalam mengukur penambahan pengetahuan mitra dilakukan pre-test dan post-test menunjukkan perubahan pengetahuan dimana 84% siswa memiliki peningkatan jawaban benar serta 57.6% memiliki ketepatan menjawab diatas 70% soal. Kepuasan mitra diukur dengan kuesioner dan mendapatkan 94% siswa kegiatan pelatihan mudah dipahami dan siap menerapkan pembuatan material komposit. Selain itu, tetap perlu adanya peningkatan terutama dalam menanggulangi bau resin ketika praktikum.
Analisis Numerik Pengaruh Geometri Burung Terhadap Tekanan Impak Pada Kasus Bird Strike Dengan Smoothed Particle Hydrodynamics (SPH) Model endah yuniarti; Sahril Afandi S; Budi Aji Warsiyanto
Jurnal Teknologi Kedirgantaraan Vol 5 No 1 (2020): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v5i1.284

Abstract

his research studies influence of bird geometry on impact pressures during bird strike, namely Hugoniot and Stagnation pressure. Bird geometry is capsule or cylinder with hemisphere end. The geometry is simulated with different L/D ratio, 1.5, 1.7, and 1.9. Elastic-plastic hydrodynamic material model is used in simulation. Bird model simulation are using smooth particle hydrodynamics method and initial velocities are 100 m/s, 200 m/s, and 300 m/s. The results show variation of L/D ratio provide Hugoniot pressure 14-25 times higher than stagnation pressure in L/D = 1.5, 12-25 times in L/D = 1.7, and 11-34 times in L/D = 1.9. Hugoniot pressures show an increased value from L/D 1.5 to 1.9 at a velocity of 100 m/s. However, for Hugoniot pressure at a velocity 200 m/s shows a value that decreases from L/D 1.5 to 1.9. The stagnation pressure ratio of L/D is lower than L/D 1.5 and 1.7 at impact velocity 100 and 200 m/s.
Analisis Bird Strike Pada Bagian Struktur Sayap Pesawat UAV JATAYU-01 dengan Variasi Kecepatan dan Material Candra Pranoto; Budi Aji Warsiyanto; Endah Yuniarti
Jurnal Mahasiswa Dirgantara Vol. 4 No. 1 (2025): Jurnal Mahasiswa Dirgantara
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jmd.v4i1.129

Abstract

Keselamatan penerbangan merupakan aspek krusial dalam sistem transportasi udara, termasuk pada operasional pesawat tanpa awak (Unmanned Aerial Vehicle/UAV) yang kini semakin luas digunakan di berbagai sektor. Salah satu ancaman serius terhadap keselamatan dan kelayakan operasional UAV adalah bird strike, yaitu tumbukan antara pesawat dan burung yang dapat menyebabkan kerusakan struktural signifikan, terutama pada bagian sayap. Sayap merupakan komponen kritis yang rentan terhadap dampak tumbukan karena posisinya yang terbuka dan luas. Penelitian ini bertujuan untuk menganalisis tingkat kerusakan pada struktur sayap pesawat UAV JATAYU-01 akibat bird strike, dengan memvariasikan jenis material skin serta kecepatan tumbukan. UAV JATAYU-01 dikategorikan sebagai small UAV, sehingga sangat rentan terhadap dampak langsung bird strike. Simulasi dilakukan menggunakan perangkat lunak Abaqus CAE untuk memperoleh nilai energi internal, tegangan (stress), dan regangan (displacement) yang terjadi pada struktur sayap. Konfigurasi struktur sayap terdiri dari core berbahan Styrofoam, low spar dan upper spar dari material komposit Carbon UD, serta skin yang divariasikan antara Balsa wood dan Styrofoam. Kecepatan tumbukan burung dalam simulasi divariasikan pada 20 m/s, 30 m/s, dan 40 m/s. Hasil simulasi menunjukkan bahwa pada kecepatan 40 m/s, skin berbahan Balsa wood menyerap energi sebesar 22,759 J dengan displacement 2,207 mm, sementara skin berbahan Styrofoam menyerap energi sebesar 29,271 J dengan displacement 9,494 mm. Temuan ini menunjukkan bahwa pemilihan material skin sangat berpengaruh terhadap daya tahan struktur UAV terhadap bird strike, dan menjadi pertimbangan penting dalam desain UAV yang aman dan andal dalam operasional di wilayah rawan burung.   Aviation safety is a critical aspect of air transportation systems, including the operation of Unmanned Aerial Vehicles (UAVs), which are increasingly utilized across various sectors. One of the major threats to UAV operational safety is bird strike—collisions between birds and aircraft—that can cause significant structural damage, particularly to the wings, which are vulnerable due to their exposed and broad surface. This study aims to analyze the structural damage to the wing of the UAV JATAYU-01 resulting from bird strikes by varying the skin material and impact velocity. The JATAYU-01 is classified as a small UAV, making it especially susceptible to such impacts. Simulations were conducted using Abaqus CAE software to evaluate internal energy, stress, and displacement values on the wing structure. The wing configuration includes a Styrofoam core, carbon UD composite for the low and upper spars, and skin made of either Balsa wood or Styrofoam. Bird impact velocities of 20 m/s, 30 m/s, and 40 m/s were tested. Results indicate that at 40 m/s, the Balsa wood skin absorbed 22.759 J of energy with a displacement of 2.207 mm, while the Styrofoam skin absorbed 29.271 J with a displacement of 9.494 mm. These findings highlight the significant influence of skin material selection on a UAV’s structural resistance to bird strikes and underscore its importance in designing UAVs capable of safe and reliable operation in bird-prone airspace
Analisis Kelaiktabrakan (Crashworthiness) Badan Pesawat Tanpa Awak (UAV) Ritewing Drak Menggunakan Metode Elemen Hingga Eros Ray; Syarifah Fairuza; Budi Aji Warsiyanto
Jurnal Mahasiswa Dirgantara Vol. 4 No. 1 (2025): Jurnal Mahasiswa Dirgantara
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jmd.v4i1.130

Abstract

Pesawat Tanpa Awak (Unmanned Aerial Vehicle atau UAV) adalah kendaraan udara yang beroperasi tanpa pilot, dan semakin banyak digunakan untuk berbagai misi sipil maupun militer. Pemilihan material UAV sangat penting karena memengaruhi performa struktural, efisiensi, dan keselamatan. Penelitian ini menganalisis pengaruh variasi material dan kecepatan tumbukan terhadap respons struktural fuselage UAV Ritewing Drak menggunakan metode elemen hingga. Tiga material diuji, yaitu kevlar, carbon fiber, dan fiber glass, dengan kecepatan tumbukan 4 m/s, 6 m/s, dan 8 m/s. Hasil simulasi menunjukkan bahwa kevlar memiliki nilai indeks kegagalan Tsai-Hill terendah sebesar 0,03411, lebih baik dibandingkan carbon fiber (0,03788) dan fiber glass (0,04121). Ketiga material menunjukkan deformasi plastik pada foam, namun masih dalam batas aman karena nilai Tsai-Hill tidak melebihi kriteria kegagalan. Peningkatan kecepatan menyebabkan peningkatan nilai Tsai-Hill dan deformasi: pada 4 m/s, 6 m/s, dan 8 m/s berturut-turut menghasilkan nilai Tsai-Hill sebesar 0,0211; 0,0261; dan 0,0341, serta nilai equivalent plastic strain pada foam sebesar 5,125; 10,29; dan 18,74. Simulasi membuktikan bahwa struktur UAV dengan material kevlar mampu memenuhi syarat kelaiktabrakan dan layak digunakan untuk aplikasi yang membutuhkan ketahanan benturan.   Unmanned Aerial Vehicles (UAVs), commonly known as drones, are aircraft that operate without an onboard pilot and are increasingly used in both civil and military applications. Material selection plays a critical role in UAV design, as it directly affects structural performance, energy efficiency, payload capacity, and operational safety. This study investigates the effect of material variation and impact velocity on the structural response of the Ritewing Drak UAV fuselage using the Finite Element Method (FEM). Three materials—kevlar, carbon fiber, and fiberglass—were evaluated under impact velocities of 4 m/s, 6 m/s, and 8 m/s. Simulation results indicate that kevlar exhibits the best crashworthiness performance, with the lowest Tsai-Hill failure index of 0.03411, compared to carbon fiber (0.03788) and fiberglass (0.04121). All materials experienced significant plastic deformation in the foam component, yet remained within acceptable limits, as their Tsai-Hill values did not exceed the critical failure threshold. Increasing impact velocity resulted in higher Tsai-Hill values and greater deformation: at 4 m/s, 6 m/s, and 8 m/s, the Tsai-Hill indices were 0.0211, 0.0261, and 0.0341 respectively, with equivalent plastic strain in the foam of 5.125, 10.29, and 18.74. These findings suggest that kevlar is the most suitable material for UAV fuselages in applications requiring high crashworthiness, as it provides superior structural integrity under impact conditions.
Studi Numerik Perbandingan Perilaku Struktur Auxetic Chiral dan Honeycomb Pada Pembebanan Tekan dan Impact Simon Sindhu Hendradjaja; Algazali, Febri; Syarifah Fairuza; Budi Aji Warsiyanto; Riskha Agustianingsih
Jurnal Teknologi Kedirgantaraan Vol 10 No 2 (2025): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v10i2.128

Abstract

This study aims to compare the structural performance of auxetic chiral and honeycomb sandwich panels under compression and impact loading to identify their potential application in lightweight aerospace structures. Numerical simulations were conducted using the ABAQUS platform to analyze the mechanical response and failure behavior of both core designs. A mesh convergence study was performed to ensure accurate and reliable simulation results. The impact tests were conducted at energy levels of 5 J, 10 J, and 20 J, while compression tests were applied with a displacement of 4 mm. The results show that the auxetic chiral core demonstrates superior performance compared to the honeycomb core by achieving smaller deformations and better energy absorption under equivalent impact forces. Furthermore, the auxetic chiral core exhibits a higher compressive strength of up to 111 MPa, outperforming the honeycomb core, which withstands only 50 MPa. Failure analysis also reveals that facesheets on auxetic panels experience significantly smaller damage areas compared to honeycomb panels. These findings indicate that auxetic chiral cores offer promising advantages for designing lightweight, impact-resistant aerospace structures.
PENINGKATAN KOMPETENSI PEMBUATAN UAV SISWA SMK ANGKASA 1 JAKARTA MELALUI PELATIHAN TEKNOLOGI DIRGANTARA Widanto, Muhammad Hadi; Warsiyanto, Budi Aji; Agustianingsih, Riskha; Fairuza, Syarifah; Sari, Rafika Arum; Jayadi, Muhamad
An-Nizam Vol 4 No 2 (2025): An Nizam: Jurnal Bakti Bagi Bangsa
Publisher : Universitas Islam 45 Bekasi

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.33558/an-nizam.v4i2.11539

Abstract

The development of Unmanned Aerial Vehicle (UAV) technology has advanced rapidly and is now applied in agriculture, mining, forestry, and the creative industry. Indonesia, with its vast territory and diverse topography, has great potential for UAV utilization. However, mastery of this technology at the vocational school level remains limited. SMK Angkasa 1 Jakarta, particularly in its aviation department, faces this challenge and requires strengthened competencies in UAVs. In response, Universitas Dirgantara Marsekal Suryadarma carried out a Community Service program as a form of technology and innovation transfer. The program aimed to enhance students’ conceptual understanding and basic skills related to UAVs, introduce prototype design processes, familiarize them with UAV system components, and provide learning modules and equipment for independent learning. The methods included the preparation of teaching modules, delivery of UAV materials (theory, conceptual design, electrical and navigation systems), hands-on practice in building polyfoam UAV prototypes, interactive discussions, and evaluations through pre-tests, post-tests, and questionnaires. The results showed a significant improvement in students’ knowledge, indicated by the increase in post-test scores and positive feedback on the training. The provision of UAV prototypes and modules further strengthened practice-based learning at the school. In conclusion, the training successfully improved students’ competencies while contributing to the quality of vocational education in aviation. Recommendations include establishing a UAV laboratory, continuous teacher training, broader collaboration with industry, and promoting student work through UAV competitions and exhibitions.
Numerical Analysis and Taguchi Optimization of Bird Strike Resistance on Helicopter Engine Cowling Using Lattice Structure Warsiyanto, Budi Aji; Widanto, Muhammad Hadi; Sari, Rafika Arum; Rizki, Alfan; Putera, Rizky Akmal
Eduvest - Journal of Universal Studies Vol. 5 No. 8 (2025): Eduvest - Journal of Universal Studies
Publisher : Green Publisher Indonesia

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.59188/eduvest.v5i8.52086

Abstract

Bird strikes pose a major risk to the safe operation of aircraft. This study evaluates a sandwich structure design with a lattice material as a helicopter engine protection device. Advances in additive manufacturing have enabled the advancement and fabrication of architected cellular materials. The lattice structures were assessed computationally through nonlinear dynamic finite element method, considering variations in topology, materials, and relative density. The Taguchi approach was used to establish the ideal lattice structure by maximizing specific energy absorption (SEA). The results showed that a body-centered cubic Z (BCCZ) lattice structure using Ti-6Al-4V material and 30% relative density performed the best at absorbing impact energy. Additionally, the sandwich structure that uses BCCZ lattice, effectively protected the engine cowling under the operational speed of a helicopter. The findings indicate that the BCCZ lattice core enhances the impact resistance of composite materials by minimizing structural deformation. Moreover, a quasi-isotropic layup combined with a lattice material sandwich plate provides superior impact resistance, deformation control, and damage mitigation compared to other sandwich designs.
The Effect of Cross-section and Elliptical Hole Ratio on Crashworthiness Parameters of Crash-Box Structure Warsiyanto, Budi Aji; Widanto, Muhammad Hadi; Musthofa, Ilham; Maulana, Ichsan; Sitompul, Sahril Afandi; Yuniarti, Endah
Indonesian Journal of Aerospace Vol. 19 No. 1 (2021)
Publisher : BRIN Publishing

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 Warsiyanto, Budi Aji; Widanto, Muhammad Hadi; Musthofa, Ilham; Maulana, Ichsan
Indonesian Journal of Aerospace Vol. 19 No. 1 (2021)
Publisher : BRIN Publishing

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 Warsiyanto, Budi Aji; Nurrohmad, Abian; Fitriansyah, Rizky; Utama, Agus Bayu; Sitompul, Sahril Afandi; Yuniarti, Endah
Indonesian Journal of Aerospace Vol. 19 No. 2 (2021)
Publisher : BRIN Publishing

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.
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 Maulana, Ichsan muftiarifin Muhamad Jayadi Muhammad Hadi Widanto Musthofa, Ilham nugraha, sultan Nurrohmad, Abian Putera, Rizky Akmal R Fitriansyah Rafika Arum Sari Riskha Agustianingsih Rizki, Alfan S A Sitompul Sahril Afandi S Sari, Rafika Arum Simon Sindhu Hendradjaja Sitompul, Sahril Afandi Sultan Nugraha A Tambunan, Pangihutan Utama, Agus Bayu