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All Journal Jurnal Teknologi Conference SENATIK STT Adisutjipto Yogyakarta Angkasa: Jurnal Ilmiah Bidang Teknologi Aviation Electronics, Information Technology, Telecommunications, Electricals, Controls (AVITEC) Jurnal Pengabdian Masyarakat Sains Indonesia (Indonesian Journal Of Science Community Services) ARMATUR : Artikel Teknik Mesin dan Manufaktur Vortex Majalah Teknik Mesin

Buyung Junaidin, Buyung

Institut Teknologi Dirgantara Adisutjipto

Author-ID : 5273502

Aerospace Engineering Automotive Engineering Civil Engineering, Building, Construction & Architecture Computer Science & IT Earth & Planetary Sciences Economics, Econometrics & Finance Education Electrical & Electronics Engineering Energy Engineering Industrial & Manufacturing Engineering Library & Information Science Materials Science & Nanotechnology Mechanical Engineering Public Health Social Sciences

Published : 26 Documents Claim Missing Document

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STRENGTH ANALYSIS OF CARGO-X UAV WING STRUCTURE USING SANDWICH COMPOSITE MATERIALS Hartini, Dwi; Junaidin, Buyung; Habibi, Habibi
Vortex Vol 3, No 1 (2022)
Publisher : Institut Teknologi Dirgantara Adisutjipto

The Cargo-X UAV aircraft is a UAV aircraft designed to carry medicines, packages and blood bags in areas that require fast and efficient handling. One of the important components of the Cargo-X UAV aircraft is the wing, so the strength of the wing structure must be seriously considered to ensure safety during flight under unexpected conditions. The purpose of this study was to analyze the wing structure of the UAV Cargo-X aircraft made of sandwich composite material to determine the level of safety of the wing structure. The loading of the wing structure uses the load due to the lift. The wing structure modeling uses CATIA software, while the analysis uses PATRAN/NASTRAN software. From the analysis results, the skin and spar wing structures are safe against loading, while the core section is not safe against loading.

THE SIMULATION OF UNMANNED AERIAL VEHICLE EAGLE-X AS SPARROWS PESTS REPELLENT Retnowati, Nurcahyani Dewi; Junaidin, Buyung; Dasrial, Dasrial
Vortex Vol 3, No 2 (2022)
Publisher : Institut Teknologi Dirgantara Adisutjipto

The technology that can be developed from Unmanned Aerial Vehicle (UAV) in agriculture is the Unmanned Aerial Vehicle Eagle-X. This technology can help farmers in carrying out their daily activities to repel bird pests on agricultural land. However, people have difficulty understanding how to use UAVs. So, with this simulation, it is hoped that it can help farmers and producers understand the workings of the eagle-x aircraft. The simulation is made using 3Ds Max software which functions to create all 3D objects and also uses Unity software to create animations and simulations. This simulation can run well on a PC or laptop that has a Windows 10 operating system with 64bit and a minimum of core i-3 specifications. Trials using simulations were carried out on 30 farmers and the results showed that 86.67% of farmers stated that this simulation was effective in providing an overview of how the Unmanned Aerial Vehicle Eagle-X works in repelling sparrow pests.

GLIDER MODEL FLYING DYNAMICS SIMULATION EAGE-X ON LONGITUDINAL MATRA Retnowati, Nurcahyani Dewi; Junaidin, Buyung; Rande, Engelbertus
Vortex Vol 3, No 1 (2022)
Publisher : Institut Teknologi Dirgantara Adisutjipto

The Glider Eagle-X aircraft is an unmanned aircraft which is expected to fly with a height of 7 meters above the ground in Yogyakarta (120 m above sea level) with a flying speed of 10 m/s. In order for the Eagle-X glider to fly stably, it is necessary to analyze the flight stability of the Eagle-X glider model. Therefore, in this study, the analysis phase of static stability and dynamic response of disturbances in the longitudinal dimension was carried out. This can be useful for students so that they can better understand the analysis of static stability and dynamic response of disturbances in the longitudinal dimension. The results of the analysis show that the flight dynamics is a value of CM-α < 0 indicating the plane is statically longitudinal and the initial response of the graph is getting smaller which indicates the plane's motion is dynamically stable. The output of the stability analysis of the flying dynamics of the Eagle-X glider model is in the form of a graph. The simulation of the flying dynamics of the Eagle-X glider in the expected longitudinal dimension is shown by the aircraft movement following the graph from the results of the stability analysis which is used as the path of the Eagle-X glider model.

AERODYNAMIC ANALYSIS OF SPORT UTILITY VEHICLE (SUV) BY COMPUTATIONAL FLUID DYNAMICS (CFD) APROACH Junaidin, Buyung
Vortex Vol 3, No 1 (2022)
Publisher : Institut Teknologi Dirgantara Adisutjipto

The main purpose of aerodynamics analysis of a vehicle is optimizing it’s form to increase aerodynamics efficiency. More streamline of aerodynamic design of a vehicle not just effecting to lower fuel consumption which is cause by lower drag due to wind at highspeed, but also increasing stability dan control of the vehicle itself. The vehicles are existed with many variations of form so they have difference aerodynamic characteristics. For a personal vehicle like cars, have many variants such as sedan, sport utility vehicle (SUV), multipurposes utility vehicle (MPV), ect. It becomes a motivation to do research about aerodynamic analysis of a SUV car which is a car variant with huge utilize in Indonesia. In this research, aerodynamic characteristics of SUV car are evaluated by computational simulation with computational fluid dynamics (CFD) approach. CFD simulation yields aerodynamic characteristics data and flow behaviors around car model. Simulation results show that critical drag coefficient (CDcrit) of SUV car is 0.36 with lift coefficient is 0.25. the CDcrit of the car is lower than typical value for a modern car. So that, optimalization of SUV car form which analyzed is needed. Contours of pressure at car surfaces show that high pressure area are located at front of grill and windshield, and low-pressure area are located at nose and leading-trailing roof due to the form nose and leading-trailing roof are streamlines. At back surface of the car, low pressure area are formed by flow separation which creates wake.

DEVELOPMENT AND ANALYSIS OF A 7040 PROPELLER AIRSCREW TEST BENCH USING EXPERIMENTATION AND CFD Sarjito, Sarjito; Prabowo, Anggit Bayu; Wijianto, Wijianto; Junaidin, Buyung
Media Mesin: Majalah Teknik Mesin Vol. 26 No. 2 (2025)
Publisher : Universitas Muhammadiyah Surakarta

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.23917/mesin.v26i2.12059

This study presents a performance evaluation of a 7×4 propeller using both experimental and computational approaches. A test bench was developed to measure static thrust and power consumption across various rotational speeds (RPM), while Computational Fluid Dynamics (CFD) simulations were performed using ANSYS CFX to analyze the aerodynamic behavior and thrust generation under identical conditions. The experimental setup employed an Arduino-based system integrated with sensors for thrust, voltage, current, and RPM measurements. Thrust values increased proportionally with RPM, reaching a maximum of 2.7468 N at 9000 RPM. In comparison, the CFD simulation predicted a higher thrust of 3.6358 N at the same speed. Although some deviations were observed—particularly at higher RPMs—the overall trends between experimental and CFD results were consistent, indicating that both methods effectively capture the propeller’s performance characteristics. The findings confirm that the test bench provides reliable measurements under static conditions and that CFD can serve as a predictive tool for propeller performance. Further improvements through dynamic testing and simulation refinement are recommended to enhance accuracy and represent real-world flight conditions.

Simulator Respon Pesawat Berbasis Mikrokontroler: Media Edukatif bagi Siswa dan Komunitas Radio Kontrol Junaidin, Buyung; Wahju Santoso, Djarot; Sudibya, Bambang; Prakoso, Agung; Tri Wahyudi, Makus
Jurnal Pengabdian Masyarakat Sains Indonesia (Indonesian Journal Of Science Community Services) Vol. 7 No. 2 (2025): Desember
Publisher : Universitas Mataram

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.29303/jpmsi.v7i2.1556

Interactive learning media are essential in aerospace engineering education, particularly for understanding flight control systems that are difficult to grasp through theory alone. Aircraft responses to aileron, elevator, and rudder deflections require clear visualization to help learners connect control inputs with changes in aircraft attitude. To address this need, this community service program developed a microcontroller-based aircraft response simulator equipped with an attitude sensor as an educational tool for students and radio control (RC) enthusiasts. The microcontroller processes real-time data from an Inertial Measurement Unit (IMU) and displays the aircraft’s attitude angles (yaw, pitch, and roll) on an LCD screen, allowing participants to directly observe how control inputs influence attitude changes. The miniature aircraft responds according to the displayed attitude angles, enabling learners to better understand the relationship between control inputs and aircraft dynamics. Evaluation results show that the simulator operates reliably, provides accurate attitude information, and significantly enhances participants’ understanding of flight control concepts and attitude dynamics. Users also reported that the simulator is easy to operate, engaging, and effective for foundational training in RC aviation. Thus, the microcontroller and IMU-based simulator serves as a practical, replicable, and modern learning medium aligned with contemporary aerospace education.

Co-Authors Abd. Rasyid Syamsuri Agung Prakoso Anggraeni Kusumaningrum Bambang Sudibya, Bambang Cahyono, M. Ardi Dasrial, Dasrial Dwi Hartini Habibi Habibi Hendrix Novianto Firmansyah Hendrix Novianto Firmansyah, Hendrix Novianto Herlambang, Santo M. Fatha Mauliadi M. Fatha Mauliadi, M. Fatha Nurcahyani Dewi Retnowati Prabowo, Anggit Bayu Rande, Engelbertus Santo Herlambang Sarjito - Satya Wicaksono Tri Wahyudi, Makus Wahju Santoso , Djarot Wahju Santoso, Djarot Wijianto Wijianto Wisnu Prayogih Yosep Reo

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