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Teknika STTKD: : Jurnal Teknik, Elektronik, Engine
Published by Sekolah Tinggi Teknologi Kedirgantaraan
ISSN : 24601608     EISSN : 26223244     DOI : https://doi.org/10.56521/teknika.v8i1
Core Subject : Science, Engineering,
Electrical & Electronics Engineering Energy Industrial & Manufacturing Engineering Materials Science & Nanotechnology Mechanical Engineering
Teknika STTKD: Jurnal Teknik, Elektronik, Engine adalah jurnal ilmiah yang diterbitkan oleh Sekolah Tinggi Teknologi Kedirgantaraan. Teknika STTKD: Jurnal Teknik, Elektronik, Engine pertama kali terbit pada tahun 2014. Jurnal ini sempat vakum pada tahun 2019, kemudian aktif kembali mulai volume 1 tahun 2020 dan akan terbit 2 volume setiap tahunnya yaitu pada bulan Juli dan Desember.
Arjuna Subject : Teknik (semua kategori) - Teknik (Lain-Lain)
Articles 187 Documents
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KAJIAN EXPERIMEN KEKUATAN TARIK MATERIAL KOMPOSIT SERAT BAMBU DAN PASIR BESI DENGAN SUSUNAN SERAT HORIZONTAL DENGAN MENGGUNAKAN METODE HAND LAY UP al mahdi pinem; Fery Setiawan; Edy Sofyan
Teknika STTKD: : Jurnal Teknik, Elektronik, Engine Vol 9 No 1 (2023): TEKNIKA STTKD: JURNAL TEKNIK, ELEKTRONIK, ENGINE
Publisher : Sekolah Tinggi Teknologi Kedirgantaraan

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.56521/teknika.v9i1.823

Abstract

Composite is a material formed from a combination of two or more constituent materials through homogeneous mixing. Where the mechanical properties of each of the constituent materials are different. Composite material is also a very important material because it has special properties, these properties include its stiffness, strength, non-corrosion and fatigue life which is better than other conventional materials. The purpose of this study is to determine the mechanical characteristics of Composite materials. bamboo fiber and iron sand on weight variations, the best mechanical properties characteristics of several variations and determine voids or bubbles in the resin. The process of making this bamboo fiber Composite material uses volume variations of bamboo fiber by 15%, 25% and 35% then followed by printing the material on the astm d369-90 tensile test mold. In the tensile testing process, the highest mechanical properties were found in the High variation with a tensile strength value of 2.70 kgf/mm2, and a strain of 0.51% of the initial size. While the lowest mechanical properties are found in the Low variation with a tensile strength value of 2.16 kgf/mm2 and a strain of 0.33% of the initial size.
RANCANG BANGUN ALAT UJI THRUST MOTOR BRUSHLESS DENGAN VARIASI PROPELLER Haqqah Risath Mas Intan; Muhammad Luqman Bukhori; Sabri Alimi
Teknika STTKD: : Jurnal Teknik, Elektronik, Engine Vol 9 No 1 (2023): TEKNIKA STTKD: JURNAL TEKNIK, ELEKTRONIK, ENGINE
Publisher : Sekolah Tinggi Teknologi Kedirgantaraan

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.56521/teknika.v9i1.836

Abstract

In drone design, the selection of components such as batteries, Electronic Speed ​​Controllers and propellers must be in accordance with the requirements, but not all components in the RC include measurement data to determine the specifications of the brushless motor. Therefore, a test tool is needed that can calculate the amount of thrust or use a tool trials. Brushless motors and propellers are important components that affect flying performance on drones. The greater the thrust generated by the brushless motor and propeller, the greater the load that can be lifted by the drone. The types of propellers commonly used in drones include 6x4, 9x6, and 10x5 propellers. To measure the amount of thrust, load sensors and current sensors can be used which are converted by the ADC HX711 converter. The test bench tool can be used to produce data experimentally using the help of the sensor. In testing the 6x4e propeller produced a current of 7.8 Ampere and a thrust of 1.13 kgf, the 9x6e propeller produced a current of 16.4 Ampere and a thrust of 1.63 kgf, and the propeller 10x5e produced a current of 18.6 Amperes and a thrust of 2.07 kgf with the right selection of brushless motors and propellers, drone performance can increase.
PENYEBAB PENURUNAN MEASURED GAS TEMPERATURE (MGT) MARGIN ENGINE ARRIUS 2R PADA HELIKOPTER BELL 505 JET RANGER X MENGGUNAKAN METODE FAULT TREE ANALYSIS (FTA) Angga Nur Cahyadi; Edi Sofyan; Erwan Eko Prasetiyo
Teknika STTKD: : Jurnal Teknik, Elektronik, Engine Vol 9 No 1 (2023): TEKNIKA STTKD: JURNAL TEKNIK, ELEKTRONIK, ENGINE
Publisher : Sekolah Tinggi Teknologi Kedirgantaraan

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.56521/teknika.v9i1.838

Abstract

The aviation industry has recovered from the pandemic, and airlines are confidently operating their fleets again, one of which is the Bell 505 helicopter. Helicopter maintenance is also carried out to maintain performance in good condition and ready to fly. The performance of the Bell 505 helicopter is also influenced by the condition of the engine, if the engine is said to have good performance, the engine must be able to be used in function according to the planned time. In Bell 505, a problem was found during the implementation of the Power Assurance Check, namely, the decrease in the MGT margin value which is close to the value of 0, resulting in a decrease in the performance of the engine itself. Therefore, analysis and corrective action are needed to determine the cause of the decrease in the MGT margin of the Arrius 2R engine. The method used is fault tree analysis, by taking a top down approach, starting with the assumption of failure from the Top Event then detailing down to the basic failure (Root Cause). After drawing the FTA construction, evaluation is carried out with the Minimum Cut Set until the basic event is obtained. The results of the analysis conducted with “Decrease in MGT Margin Engine Arrius 2R" as the Top Event on the Bell 505 Jet Ranger X helicopter with registration code PK-WSA in the period March 2022 to July 2022 at PT.Whitesky Aviation based on AFML (Aircraft Flight Maintenance Log) data, Interview with Bell 505 Engineer and Troubleshooting Manual Engine Arrius 2R using the Fault Tree Analysis method obtained, 13 intermediate events using the logic gate “OR” and 9 basic events that cause a decrease in MGT margin on the Arrius 2R Engine are Broken Packing Seal, Fuel Contamination, Issues With the Fuel Filter, Environmental Conditions, Filter Damage, Filter Deterioration, Un Tight Screw, IBF Rarely Cleaned, Not Familiar Maintenance Manual.
AERODYNAMIC ANALYSIS OF FOLDING FIN AERIAL ROCKET 70 MM ON INCOMPRESSIBLE FLOW USING CFD-BASED SimScale Dyah Rachmawati Berliet Haryadi; Edi Sofyan; Erwan Eko Prasetiyo
Teknika STTKD: : Jurnal Teknik, Elektronik, Engine Vol 9 No 1 (2023): TEKNIKA STTKD: JURNAL TEKNIK, ELEKTRONIK, ENGINE
Publisher : Sekolah Tinggi Teknologi Kedirgantaraan

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.56521/teknika.v9i1.844

Abstract

The rocket development process goes through several stages with the aim of ensuring rocket performance when simulated. One of the important stages in the rocket development process is knowing the aerodynamics on the rocket. Aerodynamics on rockets need to be known because they affect performance when the rocket is simulated. To obtain the results of aerodynamic analysis on rockets, analysis is needed on CM (Coefficient of Moment), CD (Coefficient of Drag), and CL (Coefficient Lift) prices. In this study, the object used was FFAR (Folding Fin Aerial Rocket) with a diameter of 70 mm. The aerodynamic analysis process is carried out through simulation with two software, namely SimScale and Datcom Missile. . The results of aerodynamic analysis on rockets by varying the time(s) and speed in simulations using SimScale showed quite convergent results with movements at Mach 0.1, 0.2, and 0.3 approaching each other. While the simulation results on the Datcom missile by varying the angle of attack (α) and speed also showed convergent results with movements at Mach 0.1, 0.2, and 0.3 approaching each other.
PERBANDINGAN METODE VACUUM INFUSION & VACUUM BAGGING PADA KOMPOSIT BERPENGUAT FIBER KARBON KEVLAR Muhammad Zulfikar; Ferry Setiawan; Dhimas Wicaksono
Teknika STTKD: : Jurnal Teknik, Elektronik, Engine Vol 9 No 1 (2023): TEKNIKA STTKD: JURNAL TEKNIK, ELEKTRONIK, ENGINE
Publisher : Sekolah Tinggi Teknologi Kedirgantaraan

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.56521/teknika.v9i1.860

Abstract

Tujuan dilakukannya penelitian ini yaitu untuk mengetahui perbandingan karakteristik spesifik uji bending dari material komposit dengan matrix resin epoxy lycal berpenguat fiber karbon kevlar yang di buat dengan metode vacuum infusion dan vacuum bagging di lanjutkan dengan uji SEM untuk mengetahui karakteristik ikatan material komposit. Hasil dari rata-rata pengujian Bending menunjukkan hasil spesimen vacuum infusion sebesar 253,68 MPa dan spesimen vacuum bagging sebesar 187,8 MPa dimana kita bisa mengetahui bahwa material dengan metode pembuatan vacuum infusion lebih baik dari metode vacuum bagging. Dari hasil analisis menggunakan SEM menunjukkan karakteristik mikroskopik material dari hasil uji bending dengan metode pembuatan vacuum infusion memiliki kerapatan yang lebih baik karena memiliki void yang sedikit dibuktikan dengan data kandungan gas pada metode vacuum infusion yang memiliki konsentrasi berat 33,6%, hasil dari pengujian SEM dengan metode pembuatan vacuum bagging memiliki kerapatan yang kurang baik karena memiliki void yang lebih banyak di mana dibuktikan data kandungan gas pada vacuum bagging memiliki konsentrasi berat 33,58%. Void terbentuk dari gas yang terperangkap dalam material komposit Ketika proses manufaktur sehingga mempengaruhi kekuatan bending karena semakin banyak void pada material menyebabkan kurangnya kerapatan pada material yang mempengaruhi kekuatan bending pada material.
Rancang Bangun Pembangkit Listrik Tenaga Air Jenis Turbin Pelton Skala Laboratorium Sebagai Media Pembelajaran Hasbi Assiddiq S; Jeffry Anggara; Hairul Anwar
Teknika STTKD: : Jurnal Teknik, Elektronik, Engine Vol 9 No 1 (2023): TEKNIKA STTKD: JURNAL TEKNIK, ELEKTRONIK, ENGINE
Publisher : Sekolah Tinggi Teknologi Kedirgantaraan

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.56521/teknika.v9i1.865

Abstract

The power plant type turbine pelton of scale laboratory was made to be used as a practical medium of students and lecturers of mechanical engineering in the environment Politeknik of Kotabaru. The purpose of this research was to obtain an ideal design for hydropower systems as learning media; Knowing the effect of the lamp load on the generator rotation, knowing the effect of the type of 12 VDC and 24 VDC lamp loads with varying loads on the generator power output. The method used in this study is a literature study and experimental methods. The research results obtained are the design has a table height of 90 cm and a width of 100 cm, the height of the loading panel is 80 cm, the air pressure from the pump is 270 psi with a nozzle size of 1,7 mm, a 12 blade Pelton turbine, a 36 V 60 A DC generator; the type of lamp load affects of generator rotation where when the type of load is 12 VDC the generator rotation is smaller than when the lamp load is 24 VDC, while the large lamp load given to the system causes of generator rotation to decrease or the effect of the lamp load on generator rotation is inversely proportional; the greater of lamp load lower the output power of generator, both with 12 VDC and 24 VDC load types or in other words, it is also reversed.
THE EFFECT OF VARIATION OF TEMPERATURE ON PULL TEST OF FIBERGLASS FIBER COMPOSITE MATERIALS WITH VACUUM ASSISTED RESIN INFUSION (VARI) Dialis Okta Saputa; Ferry Setiawan; Dhimas Wicaksono
Teknika STTKD: : Jurnal Teknik, Elektronik, Engine Vol 9 No 1 (2023): TEKNIKA STTKD: JURNAL TEKNIK, ELEKTRONIK, ENGINE
Publisher : Sekolah Tinggi Teknologi Kedirgantaraan

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.56521/teknika.v9i1.868

Abstract

To determine the effect of temperature variations on mixing fiberglass composite resin materials with the vacuum infusion method in the Tensile test. To determine the effect of the lowest and best temperature variations on mixing fiberglass composite resin materials with the vacuum infusion method on fotomikro. Variation fixed resin; polyester, fiber; fiberglass, vacuum; vacuum Infusion. Variable temperature of mixing resin 30˚C, 40˚C, and 50˚C. In this study, the vacuum infusion method was used, where the researcher made a specimen using the Vacuum Assisted Resin Infusion (VARI) process. In the VARI process, dry fiber is placed between the fixmold and the plastic bag, then the resin is injected after the space inside the plastic bag is under low pressure and the process continues until all parts of the fiber are wetted by the resin. After the specimen is made, then a tensile test is carried out to determine the mechanical strength of the specimen being tested. Then analyze the tensile test data using the equations used and displayed in the form of graphs and tables. This study was used to determine the effect of fiberglass composites with the vacuum infusion method on the tensile strength test. results of Tensile testing of fiberglass fiber composites and temperature variations of 30°C, 40°C, and 50°C. From the table it can be seen that the specimen with the best performance is found in the specimen with a temperature variation of 50°C, where the load that can be withheld reaches 508.56 kgf. So for maximum tensile strength it produces 11.07 MPa. Then on the specimen with a temperature variation of 40°C the best performance is 361.95 kgf. So for maximum tensile strength it produces 8.46 MPa. In specimens with a temperature variation of 30°C the best performance is 251.10 kgf. So for a maximum tensile strength of 5.67 Mpa. The average yield strength shows the results of the Tensile test of each variation, totaling 9 specimens. For the highest yield strength, a value of 9.67 MPa was obtained at a temperature variation of 50°C and for the lowest yield strength, a value of 4.13 MPa was obtained at a temperature variation of 30°C. Tensile test specimens have results where the highest yield strength or yield strength is obtained by specimens with a temperature variation of 50°C and as the stress increases, the yield strength value increases, and for the tensile strength of the material or tensile strength which has the highest value in the test, the specimens with 50°C temperature variation. Thus, the effect of temperature treatment is significant on the increase in tensile strength, but if the temperature is 30°C it will decrease the tensile strength, as at 30°C it produces an average tensile strength of 4.62 MPa. The results of the microphoto test show that at a temperature variation of 50°C there are a few voids while the 30°C variation has too many voids. Micro photo testing aims to determine the content in the composite.
ANALISA DESAIN KEKUATAN STUKTUR PART KONEKTOR DAN TUBE FRAME UAV VTOL MENGGUNAKAN FINITE ELEMENT ANALYSIS Mario Fernandez; Dhimas Wicaksono; Ferry Setiawan; Muhammad Kevin Adam
Teknika STTKD: : Jurnal Teknik, Elektronik, Engine Vol 9 No 1 (2023): TEKNIKA STTKD: JURNAL TEKNIK, ELEKTRONIK, ENGINE
Publisher : Sekolah Tinggi Teknologi Kedirgantaraan

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.56521/teknika.v9i1.871

Abstract

UAV The purpose of this study was to determine the effect of the use of carbon fiber and aluminum materials on the structural strength of the tube and connector parts by considering the safety factor obtained from the analysis results. This study uses the finite element method with the help of solidworks software. The research was conducted in stable flight conditions, namely the UAV's gravity was the same as the UAV's lift. From the results of the frame design, the weight mass is 25.6 kg. From the simulation results, the tube with carbon fiber material and aluminum 6061 alloy both have good strength because the maximum stress values ​​that occur are 15.71 MPa and 15.64 MPa, and these values ​​are still below the yield stress of carbon fiber material which is 551 MPa and aluminum 6061 alloy material, namely 55.1 MPa, with a safety factor obtained of 35 for carbon fiber and 3.5 for aluminum 6061 alloy, and a maximum displacement of 0.056 mm for carbon fiber and 0.812 mm for aluminum 6061 alloy. Whereas the connectors with carbon fiber and aluminum 6061 alloy materials also have good strength because the maximum stress values ​​that occur are 4,266 MPa and 4,139 MPa, and these values ​​are still below the yield stress of carbon fiber material and aluminum 6061 alloy material. with a safety factor obtained of 130 on carbon fiber and 3.5 on aluminum 6061 alloy, and the maximum displacement is 3,734 x 10-5 mm on carbon fiber and 5,416 x 10-4 mm on aluminum 6061 alloy. The use of carbon fiber material in tubes and connectors has better strength than aluminum 6061 alloy, due to the safety factor the value obtained is greater.
ANALISIS DAN DESAIN WING UAV VTOL MENGGUNAKAN FINITE ELEMENT ANALYSIS Andika wijaya; Edi Sofyan; Ferry setiawan; Muhammad Kevin Adam
Teknika STTKD: : Jurnal Teknik, Elektronik, Engine Vol 9 No 1 (2023): TEKNIKA STTKD: JURNAL TEKNIK, ELEKTRONIK, ENGINE
Publisher : Sekolah Tinggi Teknologi Kedirgantaraan

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.56521/teknika.v9i1.872

Abstract

Unmanned Aircraft (PTTA) or Unmanned Aerial Vehicle (UAV) is an aircraft that flies without a pilot and is controlled automatically. UAVs have a wide range of applications, including remote sensing, communication links, and natural disaster monitoring. One type of UAV being developed is LSU 05, using a composite of carbon fiber (CFRP) and glass fiber (GFRP) for its wing structure. This study aims to create a 3D model of the UAV VTOL wing, analyze the effect of material variations on the strength of the wing structure, and find the optimal wing design using the finite element analysis method. This study uses the SolidWorks 2021 software with maneuver conditions loading. The results of the analysis show that carbon fiber provides higher strength than fiberglass. In a fiberglass wing, the maximum stress is 229 MPa, while in a carbon fiber wing it is 197 MPa. The biggest displacement occurred in the fiberglass wing, which was 2.661 mm. The safety factor of the carbon fiber wing is 2.7, while that of the fiberglass is 1.9. This research provides an in-depth understanding of the behavior of VTOL UAV wing structures and contributes to the development of better wing designs. The optimized design can increase the performance, efficiency and reliability of VTOL UAV.
PENGARUH BERAT PENGENDARA TERHADAP WAKTU DAN KECEPATAN MAKSIMAL KENDARAAN MOTOR LISTRIK RODA TIGA KHUSUS DIFABILITAS Amarulloh Amarulloh; Fahra Diky Mustain; Haikal Haikal
Teknika STTKD: : Jurnal Teknik, Elektronik, Engine Vol 9 No 1 (2023): TEKNIKA STTKD: JURNAL TEKNIK, ELEKTRONIK, ENGINE
Publisher : Sekolah Tinggi Teknologi Kedirgantaraan

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.56521/teknika.v9i1.873

Abstract

Untuk membantu mobilitas penyandang disabilitas khususnya kaum difabel daksa perlu adanya pembutan kendaraan roda tiga yang mudah dioperasikan, ramah lingkungan dan hemat energi. Melalui penelitian ini akan dibuat kendaraan motor listrik roda tiga yang telah melewati analisa pengujian kemampuan kendaraan dan durabilitas. Proses pembuatan kendaraan motor listrik diawali dengan membuat rangka kendaraan yang terbuat dari besi hollow, sedangkan bodi memanfaatkan plat besi dengan ketebalan 0.5mm. Motor listrik BLDC 1200W 60V digunakan sebagai motor penggerak. Supplay energi listrik didapat dari baterai lithium ion dengan kapasitas 64V 30Ah yang ditanam dibagian belakang kendaraan Terdapat 2 jenis pengujian pada penelitian ini yakni yang pertama adalah pengujian untuk menganalisis pengaruh perbedaan berat penumpang terhadap kecepatan maksimal yang mampu dicapai kendaraan motor roda tiga sedangkan pengujian selanjutnya adalah menguji waktu yang dibutuhkan kendaraan roda tiga tersebut untuk mencapai kecepatan maksimal dengan memvariasikan beban pengendaranya. Hasil dari penelitian menunjukkan bahwa ketika berat pengendara adalah 65 Kg kecepatan maksimal dapat mencapai 38 Km/h dalam waktu 11.39 s, namun ketika berat pengendara bertambah menjadi 85 Kg kecepatan maksimal yang mampu dicapi hanya 36 Km/h dalam waktu 12.36 s dan kecepatan maksimal akan kembali berkurang ketika berat pengendara 100 Kg 34 Km/h dan membutuhkan waktu 13.15 s. Kecepatan maksimal dan waktu dibutuhkan untuk mencapai kecepatan maksimal oleh kendaraan motor listrik roda tiga tersebut sangat dipengaruhi oleh berat pengendaranya.

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