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INDONESIA
Jurnal Teknologi Dirgantara
Published by Lembaga Penerbangan dan Antariksa Nasional
ISSN : 14128063     EISSN : 25977849     DOI : https://doi.org/10.30536
Core Subject : Science, Engineering,
Aerospace Engineering Chemical Engineering, Chemistry & Bioengineering Computer Science & IT Mechanical Engineering Physics
Jurnal Teknologi Dirgantara (Journal of Aerospace Technology) is an Indonesian accredited scientific publication that covers topics of Rocket, satellite, and aeronautics technology, as well as a spin-off from aerospace technology, such as aerodynamics, astronautics, aerospace structure, power and thermal system of satellites, flight controls. Propulsion and energetic technologies, such as propellant, rocket static-test, thermodynamics of propulsion system. Launch vehicle technology and space operations, such as satellite telecommunication systems, space payloads, and ground station technologies.
Arjuna Subject : Teknik (semua kategori) - Teknik Ruang Angkasa
Articles 333 Documents
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ANALISIS PENENTUAN POWER LOADING PADA DESAIN AWAL PESAWAT TERBANG TANPA AWAK LSU-05 NG Novita Atmasari; Eries Bagita Jayanti; Nur Mufidatul Ula; Mohamad Luthfi Ramadiansyah; Redha Ramadhan Akbar; Prasetyo Ardi Probo Suseno; Ardian Rizaldi; Kurnia Hidayat; Angga Septiyana
Jurnal Teknologi Dirgantara Vol. 17 No.2 Desember 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.a3162

Abstract

Penelitian ini berfokus pada analisa penentuan power loading pada awal desain pesawat LSU-05 NG. Dengan menentukan power loading maka kebutuhan daya engine untuk pesawat LSU-05 NG dapat diestimasi. Artinya pemilihan engine dapat dilakukan sehingga menghasilkan gaya dorong agar pesawat dapat melakukan misi pemantauan dan foto udara dengan baik.  Metode yang digunakan untuk analisa penentuan power loading adalah teknik Matching Chart atau Matching Plot dengan memilih titik optimal dari lima konstrain yaitu jarak take-off, climb rate, stall speed, cruise speed, dan landing. Hasil penelitian menunjukkan bahwa dengan massa 85 kg dan luas sayap 3,22 m2 pesawat LSU-05 NG membutuhkan daya 9.7 hp. Penjelasan lebih detail akan dijabarkan pada bagian selanjutnya.
PENELITIAN KARAKTERISTIK AERODINAMIKA SAVONIUS BERSUDU BANYAK DENGAN METODA PENGGESERAN MESH Agus Aribowo
Jurnal Teknologi Dirgantara Vol 4, No.1 Juni (2006)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Rotation of Savonius blades could be simulated using Sliding Mesh methode. The effective solution can be obtained by interfacing between moving zone and fixed zone by coordinating the linked cell. The number of tested blades 2,3,4 and 6. The result is the Savonius turbine with 3 blades having torque coefficient higher and efficiency level the compared which the other blades. The spacing of blade axis make airflow infiltrate and causing increase of force momen and negative drag force. By increasing the number of blades will result in the reduction of negative and positive force between one blade to the other. As a result, the performance will be reduced due to the increased number of blades. Keywords: Energi angin, Savonius, Koefisien Momen, Sliding Mesh.
ANALISIS CFD KARAKTERISTIK AERODINAMIKA PADA SAYAP PESAWAT LSU-05 DENGAN PENAMBAHAN VORTEX GENERATOR (ANALYSIS OF CFD AERODYNAMIC CHARACTERISTICS AT THE WING OF AIRCRAFT LSU-05 WITH THE ADDITION OF VORTEX GENERATOR) Awalu Romadhon; Dana Herdiana
Jurnal Teknologi Dirgantara Vol. 15 No. 1 Juni 2017
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2017.v15.a2518

Abstract

LSU-05 aircraft is one of the unmanned aerial vehicles (UAV), which is being developed by the Aeronautics Technology Center of LAPAN, whose mission is for research, observation, patrol, border surveillance, and investigation of natural disasters. This study aims to determine the effect of vortex generators on the aerodynamic characteristics of the LSU-05 Unmanned Aircraft wing. The method used is a numerical analysis with CFD simulation for predicting aerodynamic characteristics and flow phenomena that occur. The models used are the aircraft wing of the LSU-05 without vortex generator and with vortex generator designed with CATIA software. The simulation is using ANSYS Fluent software to determine changes in the aerodynamic characteristics of the wing after the addition of vortex generators such as the lift coefficient and drag coefficient. The results of the addition of vortex generator on LSU-05 wings are the increasing value of the maximum lift coefficient of the wing which becomes 1,34840 from 1,26450, it increases 0,0839 (6.63%) point, the increasing value of the drag coefficient on the angle of attack from -9⁰ to 11⁰, the decreasing value of the drag coefficient on the angle of attack 12⁰ up to 15⁰ and the increasing stall angle of wing from 11⁰ to 14⁰ or increased by 3⁰ (27,7%). AbstrakPesawat LSU-05 adalah salah satu pesawat tanpa awak (UAV) yang sedang dikembangkan oleh Pusat Teknologi Penerbangan LAPAN, yang mempunyai misi untuk kegiatan penelitian, observasi, patroli, pengawasan perbatasan wilayah, dan investigasi bencana alam. Penelitian ini bertujuan untuk mengetahui pengaruh penambahan vortex generator terhadap karakteristik aerodinamika dari sayap Pesawat Tanpa Awak LSU-05. Metode yang digunakan adalah analisis numerik dengan simulasi CFD untuk memprediksi karakteristik aerodinamika dan fenomena aliran yang terjadi. Model yang digunakan adalah sayap pesawat LSU-05 tanpa vortex generator dan dengan vortex generator yang didesain dengan software CATIA. Simulasi menggunakan software ANSYS Fluent untuk mengetahui perubahan karakteristik aerodinamika sayap setelah penambahan vortex generator seperti koefisien lift dan koefisien drag. Hasil yang diperoleh dari penelitian penambahan vortex generator pada sayap Pesawat LSU-05 adalah peningkatan nilai koefisien lift maksimum sayap dari 1,26450 menjadi 1,34840 atau naik sebesar 0,0839 (6,63%), peningkatan nilai koefisien drag pada sudut serang -9⁰ s/d 11⁰, penurunan nilai koefisien drag pada sudut serang 12⁰ s.d 15⁰ dan peningkatan sudut stall sayap dari 11⁰ menjadi 14⁰ atau naik sebesar 3⁰ (27,7 %).
EVALUASI KINERJA INSULINER BERBASIS EPOKSI MELALUI UJI STATIK MOTOR ROKET CASE BONDED (PERFORMANCE EVALUATION OF EPOXY BASED INSULINER OF CASE BONDED ROCKET MOTOR THROUGH STATIC TEST) - Sutrisno; Fathur Rohman; Ronny Irianto AH; Wiwiek Utami Dewi
Jurnal Teknologi Dirgantara Vol.11 No.1 Juni 2013
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Kegiatan penelitian yang telah dilakukan sebelumnya telah diperoleh material insuliner berbasis epoksi dan metode aplikasinya pada motor roket case bonded. Hasil penelitian ini juga telah diperoleh bahwa insuliner tersebut dapat direkomendasikan untuk digunakan pada motor roket case bonded yang menggunakan propelan radial burning sehingga perlu dibuktikan. Guna menguji kinerja insuliner tersebut telah dibuat dua unit motor roket case bonded mengggunakan insuliner berbasis epoksi dan satu unit motor roket free standing yang menggunakan insulasi termal berbasis epoksi dan lapisan fiber glass cloth untuk diuji statik. Tiga unit motor roket telah diuji statik. Berdasarkan pengujian diperoleh bahwa insuliner berbasis epoksi yang dibuat dapat berfungsi dengan baik. Kegagalan motor roket case bonded yang kedua tidak disebabkan oleh gagalnya insuliner tetapi oleh proses perakitan motor roket yang kurang sempurna.Kata kunci: Insuliner,Motor roket, Case bonded, Free standing, Radial burning
DESIGN OF FORCE MEASURING SYSTEM ON MAIN LANDING GEAR WEIGHT DROP TESTING MACHINE FOR THE APPLICATION OF LSU SERIES Yusuf Giri Wijaya; Abian nurrohmad
Jurnal Teknologi Dirgantara Vol. 18 No.2 Desember 2020
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2020.v18.a3377

Abstract

In this research, the design of the force measuring system on main landing gear weight drop test for the LSU series that developed by LAPAN was carried out. The principle of this machine is to apply the load according to the weight of the aircraft on the main landing gear and drop it at a certain height assisted by the guiding rail. At the bottom of this machine there is a impact platform where each angle is mounted with a load cell that functions to measure the reaction force due to the impact of the main landing gear. In addition, there is a data acquisition system whose function is to process the output signal from load cell and display measurement data. The data acquisition system used consists of DAQ measurement hardware made by national instruments and LabVIEW software installed on a PC. The design of this testing tools aims to carry out a dynamic impact test on the main landing gear structure of the UAV. In this study, static calibration has also been successfully performed on the impact platform and shows consistent results for various test masses.
OPTIMASI PEMANFAATAN SISTEM PEMOMPAAN TENAGA ANGIN(SPTA) UNTUK SUMBER-SUMBER AIR DALAM DENGAN TURBIN ANGIN LISTRIK SUDU MAJEMUK SEBAGAI PENGGERAK POMPA Sahat Pakpahan; - Soeripno
Jurnal Teknologi Dirgantara Vol 1, No.1 Juni(2003)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

The application of WInd Energy Conversion Systems (WECS) for supplying water for households, irrigation, livestock or other purposes have been developed to increase the contribution of renewable source of energy to support people, particularly at locations where accessibility to public utility networks not available or when the system itself needed by the consumer. Various WECS available in market as well as commercial pumps which can be used for bored hole., deep well or surface water and must be matched for optimal performance of the whole system; therefore, the analysis for selection of a pump due to its design characteristics for matching with an existing wind turbine that result-in optimal conditions of supply and demand has to be performed. A wind turbine with 6 blades rotor installed at BBUG samas Bantul is taken as a case study.
METODE ADAPTIF FREKUENSI-CUTOFF UNTUK COMPLEMENTARY FILTER PADA ACCELEROMETER DAN GYROSCOPE UNTUK SUDUT PITCH DAN ROLL WAHANA TERBANG (ADAPTIVE CUTOFF-FREQUENCY METHOD FOR COMPLEMENTARY FILTER OF ACCELEROMETER AND GYROSCOPE FOR PITCH AND ROLL ANGLES FLIGH Wahyu Widada
Jurnal Teknologi Dirgantara Vol.13 No. 1 Juni 2015
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Unit pengukuran inersia (Inertial Measurement Unit/IMU) adalah perangkat elektronik yang digunakan untuk mengukur kecepatan, orientasi, dan gaya gravitasi, dengan menggunakan kombinasi sensor accelerometer dan gyroscope, dan juga magnetometer pada wahana terbang. Tulisan ini membahas metode complementary filter dengan variabel adaptif cut-off frequency untuk integrasi sensor accelerometer dan gyroscope pada pengukuran pitch dan roll pada aplikasi wahana terbang seperti roket kendali dan pesawat tanpa awak. Accelerometer dapat digunakan untuk mengukur sudut tetapi terpengaruh oleh derau frekuensi tinggi, sedangkan gyroscope digunakan untuk mengukur sudut tetapi dipengaruhi drift noise. Filter ini dapat mengintegrasikan kedua sensor untuk mengukur sudut dengan lebih akurat, dari hasil percobaan menunjukkan Root Mean Square Deviation (RMSD) menjadi lebih baik sekitar 5,6 kali dibanding dengan pengukuran tanpa menggunakan filter.Kata kunci: Complementary filter, Accelerometer, Gyroscope, Integrasi sensor, Wahana terbang
ANALISIS LOSSES PIPA LURUS BERDIAMETER 40 cm PADA TEROWONGAN ANGIN LAPAN Ahmad Jamaludin Fitroh
Jurnal Teknologi Dirgantara Vol 9, No. 1 Juni (2011)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

 One of LAPAN’s programs is design and build the ramjet open tested wind tunnel. The lenght of pipe connecting between wind tunnel and storage tank was designed long enough so it was estimated there is big losses along the pipe. The object of this research is to calculation that losses, specially for the straight part only. The magnitude of the losses was gotten from simulation using software based on CFD theory. This research used two methods, i.e. based on pressure method and based on mass flow rate method. The simulation’s result using based on mass flow rate method gave the higher losses for the straight pipe so that result was chosen as the final result. That result was processed become the losses as a function of mass flow rate. The higher mass flow rate will produce the bigger losses. At mass flow rate of 60 kg/s, the losses is 0.135 %/m and at 100 kg/s the losses is 0.299 %/m. The relation between both parameter is close to linier curve. Key word:Pipe, losses, CFD, wind tunnel
THE INFLUENCE OF THE ANGLE OF ATTACK ALPHA ON THE PRESSURE RECOVERY AT AERODYNAMICS INTERFACE PLANE INVESTIGATION Subagyo Subagyo
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.a3033

Abstract

In the process of design, anaircraft to know the performance and stability requires testing in a wind tunnel.Similarly, the selection of engines for aircraft design embedded on conducted tests in a wind tunnel model air intake with some variation of the angle of attack.This paper examines the effect ofthe high angle of attack alpha testing aircraft air intake with a position of beta 0° on the subsonic regime with wind speeds of 65 ms-1.  Combat aircraft flying with an unexpected manoeuvre to avoidenemy attack nor did defence against missiles.Often the aircraft must fly to the position of a very high angle of attack.The theoretical value of the Pressure Recovery is approaching one in order to make the machine pinned can work optimally.Experimental observations of Pressure Recovery plotted against the variation of the angle of attack alpha.The observations show the performance design of aircraft engine inlet on the angle of attack alpha large can still give adequate pressure recovery.
ORBITAL HEATING RATES ANALYZING ON G2-SAT MATERIAL Bustanul Arifin
Jurnal Teknologi Dirgantara Vol 6, No.1 Juni (2008)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Telah dianalisa orbital heating rates pada material body G2-SAT, salah satu program pengembangan satelit di bidang Mekatronika LAPAN Rancabungur. Analisa ini dilakukan untuk mengetahui apakah material body pada G2-SAT memerlukan kontrol lebih lanjut seperti pemakaian material pelindung dalam hal ini MLI (Multy Layer Insulation dan penggunaan whitepaint pada solar array) jika G2-SAT mengalami pemanasan di orbitnya. Peralatan yang dipakai untuk menganalisa orbital heating rates ini adalah perangkat lunak Thermal Desktop 5.0 dengan menggunakan pendekatan Monte Carlo yang terdapat di dalamnya serta dengan mempertimbangkan semua data yang berhubungan dengan properties material, power dan orbit. Dalam pendekatan Monte Carlo ini berkas cahaya (array) dipancarkan dari permukaan sedangkan hal yang harus dilakukan adalah mencari permukaan mana yang terkena berkas cahaya. Selain itu, analisis tersebut dilakukan dengan berpijak dari konsep awal sistem thermal satelit yang telah ditentukan serta sumber radiasi panas yang terjadi pada G2-SAT. Hasil yang diperoleh berupa grafik yang menggambarkan besaran distribusi total absorbed flux yang terjadi pada G2-SAT body selama mengalami heating rates di orbitnya. Dari hasil analisa diketahui, sampai di orbit material tersebut memerlukan kontrol thermal lebih lanjut.

Page 10 of 34 | Total Record : 333

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