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INDONESIA
Indonesian Journal of Aerospace
Published by Badan Riset dan Inovasi Nasional
ISSN : -     EISSN : 30320895     DOI : https://doi.org/10.55981/ijoa
Core Subject : Science, Engineering,
Aerospace Engineering Astronomy
Indonesian Journal of Aerospace provides a broad opportunity for the scientific and engineering community to report research results, disseminate knowledge, and exchange ideas in various fields related to aerospace science, technology, and policy. Topics suitable for publication in the IJoA include (but are not limited to) Space science (astrophysics, heliophysics, magnetospheric physics, ionospheric physics, etc.), Aeronautics technology (dynamic, structure, mechanics, avionics, etc.), Space technology (rocket, satellite, payload system, control, etc.), Propulsion and energetic technology (propellant, rocket static-test, thermodynamics of propulsion system, etc.), Aeronautics and space policy, and Application of aerospace science and technology.
Arjuna Subject : Ilmu Bumi dan Planet (semua kategori) - Ruang Angkasa dan Ilmu Planet
Articles 364 Documents
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REVIEW VISUALISASI SCHLIEREN PADA TEROWONGAN ANGIN SUPERSONIK Hamonangan , Jefri Abner
Indonesian Journal of Aerospace Vol. 17 No. 1 Juni (2019): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2019.v17.a2999

Abstract

Terowongan angin merupakan sebuah fasilitas yang mensimulasikan aliran udara dengan berbagai variasi kecepatan pada sebuah benda. Peneliti dan perekayasa menggunakan terowngan angin untuk mengamati dan mengevaluasi perilaku sebuah benda pada kecepatan udara tertentu. Terdapat 2 metode dalam proses pengamatan perilaku benda pada pengujian terowongan angin, yaitu dengan menggunakan balance dan visualisasi dengan menggunakan schlieren.
IN-ORBIT IMPLEMENTATION OF ERROR PATCHING METHODS FOR LAPAN-A3/IPB OBDH FIRMWARE SYSTEM Taufik, Muhammad; Hasbi, Wahyudi; Karim, Abdul
Indonesian Journal of Aerospace Vol. 17 No. 1 Juni (2019): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2019.v17.a3012

Abstract

OBDH (On-board data handling) is a satellite subsystem that receives, processes, decides and executes commands from and to satellites. OBDH is built on two systems namely hardware and software integrated system (firmware system). In terms of hardware, OBDH uses a processor with 32bit RISC architecture, 128/256 Kbyte internal memory and a firmware system that is built using primitive programming. This programming uses the super loop architecture program and interrupt to manage the system to function properly. Problems occur when an error occurs in one of the functions in the interrupt routine resulting in failure of interpretation of commands or data from satellite sensors. This paper describes the implementation of the error patching methods on the LAPAN-A3/IPB Satellite OBDH firmware system in order to keep the system working well. Initial verification through testing on the ground have been successfully performed using engineering model of OBDH and hardware in the loop simulators (HWIL) module. Based on the test results, implementation on satellite has also been successfully done.
THE INFLUENCE OF THE ANGLE OF ATTACK ALPHA ON THE PRESSURE RECOVERY AT AERODYNAMICS INTERFACE PLANE INVESTIGATION Subagyo, Subagyo
Indonesian Journal of Aerospace Vol. 17 No. 1 Juni (2019): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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.
Analisis Kekuatan Struktur Komposit Dengan Ply Drop-off Pada Roda Pendarat Utama Pesawat Nir Awak Menggunakan Metode Elemen Hingga Wandono, Fajar Ari; Adhitya, Mohammad
Indonesian Journal of Aerospace Vol. 17 No. 1 Juni (2019): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2019.v17.a3037

Abstract

Penggunaan ply drop-off telah banyak digunakan untuk mengoptimalkan struktur komposit sehingga memiliki massa yang lebih ringan dibandingkan dengan struktur komposit dengan penggunaan ketebalan seragam. Tulisan ini akan memprediksi kekuatan dan potensi pengurangan massa struktur komposit dengan menggunakan ply drop-off pada roda pendarat utama pesawat nir awak terhadap beban operasional menggunakan metode elemen hingga. Beban operasional diasumsikan merupakan beban statik akibat landing sebesar 245 N arah vertikal dan sebesar 78.75 N arah horizontal. Struktur roda pendarat utama dimodelkan menggunakan elemen Quad4 dengan memasukkan sifat mekanis dari material e-glass Woven Roving 185 pada software MSC. Patran/Nastran. Kriteria kegagalan yang digunakan adalah berdasarkan kriteria kegagalan Tsai-Wu dalam indeks kegagalan dan margin of safety. Hasil yang didapatkan adalah struktur roda pendarat utama memiliki indeks kegagalan 0.62 dan margin of safety sebesar 1.39. Dari hasil tersebut menandakan struktur roda pendarat utama cukup kuat dan tidak terjadi kegagalan dalam menerima beban operasional yang diberikan. Di samping itu, potensi pengurangan massa pada struktur roda pendarat utama menggunakan ply drop-off adalah sebesar 18%.
EFFECT OF FLAT AND HEMISPHERICALLY ENDED CYLINDER BIRD MODEL WITH FINITE ELEMENT MODELLING OF BIRD STRIKE Yuniarti, Endah; Sitompul, Sahril Afandi
Indonesian Journal of Aerospace Vol. 17 No. 1 Juni (2019): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2019.v17.a3061

Abstract

This research studies influence of bird model on impact pressures during bird strike, namely Hugoniot and Stagnation pressure through initial modelling by numerical simulations using finite element method. Finite element simulation of bird strike have primarily modelled the bird as either a flat or hemispherically ended cylinder. The geometry is simulated with different L/D ratio, 1.4, 1.6, 1.8 and 2.0. Elastic-plastic hydrodynamic material model is used in simulation. Bird model simulation are using lagrangian method and initial velocities are 100, 200 and 300 m/s. Simulation results of hemispherically ended cylinder bird models show variation of L/D ratio provide Hugoniot pressure 10-19 times higher than stagnation pressure in L/D = 1.4, 8-18 times in L/D = 1.6, 9-17 times in L/D = 1.8 and 4-16 times in L/D = 2. The Hugoniot pressure shows a lower value at an L/D ratio of 1.6 compared to other ratios and the Stagnation pressure is higher at L/D ratio 2. As for cylindrical bird model show variation of L/D ratio provide Hugoniot pressure 35-38 times higher than stagnation pressure in L/D = 1.4, 30-47 times in L/D = 1.6, 31-52 times in L/D = 1.8 and 28-48 times in L/D = 2. The Hugoniot pressure shows a lower value at an L/D ratio of 1.4 and 1.6 compared to other ratios and the Stagnation pressure is higher at L/D ratio 2.
ANALYSIS OF ELECTRICAL LOAD ASSESSMENT LSU (LAPAN SURVEILLANCE UAV) 03 Setyadewi, Imas Tri; Sumarna, Encung; Prabowo, Yanuar
Indonesian Journal of Aerospace Vol. 17 No. 1 Juni (2019): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2019.v17.a3108

Abstract

LSU 03 Aircraft was used for LSU MISI with capability cruise up to 340 km. LSU 03 has an operation for marine safety from illegal fishing. To support the monitoring mission of illegal fishing with operation range up to 250 km or 3 hours flight, several required system are needed such as autopilot system, datalink, propulsion, and payload. All of system then analysed by an ELA (Electrical Load Assessment) of the aircraft system to know the necessary power required to conduct the initial mission of the aircraft. ELA analysis is done by calculating the power requirement from each component specification and function test of the component for validation of calculation result. From the results of the study, the amount of power consumption is 35% from the spec calculation, which is 32.43 Wh which can be accommodated by a battery system up to 4.2 hours. Whereas for ignition or aircraft engines whose source of battery uses LIPO 2S 7.4 Vdc batteries can accommodate the ignition energy requirements for more than 11 hours.
PENGEMBANGAN ANTENA HELIKS QUADRIFILAR 2,22 GHZ UNTUK SATELIT MIKRO Faizal, Iwan; Priyanto, Irwan; Ardinal, Rifki; Suhata, Suhata
Indonesian Journal of Aerospace Vol. 17 No. 1 Juni (2019): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2019.v17.a3116

Abstract

Bentuk dasar antena heliks quadrifilar dikembangkan oleh C. C. Kilgus dari Laboratorium Fisika Terapan, Universitas Johns Hopkins, USA. Antena ini memiliki beamwidth yang lebar sampai 2400 dengan pola radiasi berbentuk jantung, berpolarisasi sirkular dan tidak memerlukan reflektor. Antena heliks quadrifilar memiliki rasio diameter terhadap tingginya 0,66. Artinya antena ini ditempatkan di on-board satelit sebagai pemancar (Tx). Ukuran dari antena ini adalah ½ λ ½ putaran dan termasuk dalam varian putaran kecil. Tujuan dari riset ini adalah membuat prototip antena heliks quadrifilar dengan frekuensi 2,22 GHz dan selanjutnya diuji dalam skala laboratorium. Dari hasil pengujian laboratorium, besarnya RL adalah -18.55 dB, besarnya VSWR adalah 1,26, besarnya lebar pita adalah 6,04 %, besarnya lebar berkas adalah 1700 dan besarnya penguatan adalah 5,19 dB.
METODA COROTATIONAL BEAM 2D UNTUK ANALISIS STATIK STRUKTUR NONLINIER GEOMETRIK Andria, Novi; Zuhal, Lavi R.; Gunawan, Leonardo; Muhammad, Hari
Indonesian Journal of Aerospace Vol. 17 No. 1 Juni (2019): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2019.v17.a3117

Abstract

Makalah ini membahas sebuah metoda corotational beam dua dimensi (CBM 2D) yang dapat digunakan untuk analisis statik struktur yang nonlinier secara geometri. Kombinasi antara formulasi corotational beam dan Euler-Bernouli beam Theory (EBT) membuat implementasi numerik metoda ini menjadi sangat sederhana dengan beban komputasi yang rendah sehingga sangat praktis untuk diaplikasikan. Akurasi dan efisiensi metoda ini terverifikasi melalui beberapa uji numerik yang dilakukan pada beberapa model uji yang terdapat pada literatur. Metoda ini pun mampu memberikan hasil yang akurat untuk kasus extensible beam dan struktur beam yang dibebani follower load. Hasil penelitian ini memverifikasi validitas, efisiensi, dan kepraktisan dari metoda yang dikembangkan.
Front Pages JTD Vol 15 No 2 Desember 2017 Jurnal, Redaksi
Indonesian Journal of Aerospace Vol. 15 No. 2 Desember (2017): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar

Abstract

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PERANCANGAN AUTOPILOT LATERAL-DIREKSIONAL PESAWAT NIRAWAK LSU-05 (THE DESIGN OF THE LATERAL-DIRECTIONAL AUTOPILOT FOR THE LSU-05 UNMANNED AERIAL VEHICLE) Fajar, Muhammad; Ariffianto, Ony
Indonesian Journal of Aerospace Vol. 15 No. 2 Desember (2017): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2017.v0.a2760

Abstract

Autopilot pada pesawat dikembangkan berdasarkan pada modus gerak pesawat yaitu modus gerak longitudinal dan lateral-directional. Pada makalah ini, dirancang autopilot pada modus gerak lateral-directional untuk pesawat LSU-05. Autopilot dirancang pada range kecepatan operasi pesawat yaitu 15 m/dtk, 20 m/dtk, 25 m/dtk, dan 30 m/dtk dengan ketinggian 1000 m. Autopilot yang dirancang adalah Roll Attitude Hold, Heading Hold dan Waypoint Following. Autopilot dirancang berdasarkan model linier dalam bentuk state-space. Pengendali yang digunakan adalah pengendali Proportional-Integral-Derivative (PID). Hasil simulasi menunjukan nilai overshoot/undershoot tidak melebihi 5% dan settling time kurang dari 30 detik jika diberikan perintah step.

Page 8 of 37 | Total Record : 364

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