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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 365 Documents
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DEKOMPOSISI TERMAL PROPELAN KOMPOSIT BERBASIS AMONIUM PERKLORAT/HYDROXY TERMINATED POLYBUTADIENE (AP/HTPB) (THE THERMAL DECOMPOSITION ANALYSIS OF AMMONIUM PERCHLORATE/HYDROXYTERMINATED POLYBUTADIENE (AP/HTPB) COMPOSITE SOLID PROPELLANT) Dewi, Wiwiek Utami; Ismah, Yulia Azatil
Indonesian Journal of Aerospace Vol. 14 No. 1 Juni (2016): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2016.v14.a2944

Abstract

Thermal decomposition process of AP/HTPB solid propellant type RUM, 450 and 1220 were investigated by DTG60 (Differential Thermogravimetric) with operational parameters: temperature 30 – 400oC, nitrogen flow rate 50 ml/min, and heating rate 2.5 C/min. Thermal decomposition analysis will be the first step of decomposition kinetics research in determining life time of the propellant. TGA curve of propellant RUM was found to be two staged meanwhile the thermal decomposition of propellant 450 and 1220 has become one staged. The DTA curve/thermogram of propellant RUM show the formation of intermediate product before full-length decomposition. Unlike propellant RUM, DTA curves of propellant 450 and 1220 do not show the formation of intermediate product. Decomposition process of propellant 450 and 1220 accelerate by Al presence. The difference between AP modal on propellant 450 and 1220 show insignificance effect to the amount of decomposition energy consumption.
(AUTOMATIC IDENTIFICATION SYSTEM (AIS) SATELIT DATA CORRECTION USING INTERPOLATION AND EXTRAPOLATION METHODE, (Case Study : LAPAN-A2 and LAPAN-A3 Satellite)) Karim, Abdul; Permala, Rizki; Mukhayadi, M; Hasbi , Wahyudi
Indonesian Journal of Aerospace Vol. 16 No. 2 Desember (2018): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2018.v16.a3049

Abstract

Nasional Institute Aerounautics and Space (LAPAN) has two satellites (LAPAN-A2 and LAPAN-A3) that are carry Automatic Identification System (AIS) sensors. It can be use for monitoring Indonesian maritime. The altitude of the satellite about 642 Km and 500 km so it has a wide area covered and receive big data. The problem is the AIS technology use the Time Division Multiple Access (TDMA) system that has limitations in handling big data so that some data received can be damaged due to collision. Therefore, in this research has been done the analysis and correction data using interpolation and extrapolation methods. The results is improvements of valid data about 22,6 % for LAPAN-A2 satellite and 20,8 % for LAPAN-A3 satellite.
PENGEMBANGAN PERANGKAT LUNAK ANALISIS LINTAS TERBANG ROKET MULTI-STAGE (DEVELOPMENT OF TRAJECTORY ANALYSIS SOFTWARE FOR MULTI-STAGE ROCKET) Poetro, Ridanto Eko; Jenie, Yazdi I; Sasongko, Rianto Adhy; Utama , Satriya
Indonesian Journal of Aerospace Vol. 10 No. 1 Juni (2012): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

This paper discusses the development of a computer software for simulating and analyzing flight trajectory of rocket systems. Many aspects may influence the trajectory, such as those related to the internal characteristic of the system, those representing external or environmental influence, and also the ones corresponding to the procedures of the launching and the operation during its flight. The software is developed based on the mathematical equations representing the balance of forces and moments occur during the flight of a rocket. Some conditions related to rocket internal characteristic variation, external perturbance, and flight procedure/operation are represented as parameters variations of the mathematical equations used for computing the rocket system attitude and movement variables. The software, developed using MATLAB/ SIMULINK application, is then used for simulating and analyzing the flight trajectory of a multi-stage rocket in some flight conditions. At this development stage, as the simulation results show, the software can perform its function quite well to compute the system variables during each of its flight phases and display the information required for further analysis. In future development, some validation tests still need to be accomplished for ensuring the accuracy and validity of the method used in this software.
APLIKASI CFD DALAM PENENTUAN PERFORMA MESIN TURBOFAN MODEL CFM56-5B YANG MENGALAMI CACAT PADA KIPAS UNTUK KEPUTUSAN MAINTENANCE Wuwung, Vicky; Wandani, Puspa; Bintoro , Carolus
Indonesian Journal of Aerospace Vol. 14 No. 1 Juni (2016): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2016.v14.a2945

Abstract

Penelitian ini membahas mengenai kajian kerusakan yang terjadi pada bilah kipas mesin turbofan CFM56-5B. Kerusakan tersebut memerlukan adanya sebuah keputusan maintenance, apakah bilah kipas tersebut masih layak digunakan ataukah perlu di repair atau diganti. Meskipun regulasi menetapkan bahwa kerusakan tersebut masih dapat diterima, namun perlu ditinjau dari segi performanya, apakah kipas masih dapat memberikan performa yang baik atau tidak. Kajian dilakukan dengan menyimulasikan model bilah kipas CFM56-5B pada kondisi baik dan cacat pada perangkat lunak CFD-Numeca di kondisi take-off dan cruise. Cacat pada bilah berupa dent dengan kedalaman 0.069†dan terletak seragam di semua bilah pada 70% span bilah di bagian leading edge sebagai simulasi kerusakan akibat adanya bird strike. Simulasi numerik dilakukan dengan kondisi pemodelan aliran steady, dan menggunakan model turbulen Spallart-Allmaras. Hasil simulasi numerik menunjukkan adanya penurunan performa mesin pada Thrust di kondisi take-off sebesar 14% dan penurunan efisiensi sebesar 16%, sedangkan pada kondisi cruise, penurunan Thrust dan efisiensi berturut-turut adalah sebesar 55%, dan 54%. Penurunan Thrust pada saat take-off berdasarkan regulasi AC 25-13 adalah aman dan tidak perlu dilakukan repair atau replacement. Namun, meskipun aman, mesin akan boros bahan bakar ketika berada dalam kondisi cruise sehingga perlu dilakukan repair atau replacement. Penentuan keputusan maintenance jika didasarkan pada regulasi AC 25-13 pada akhirnya adalah tidak diperlukannya repair atau replacement pada bilah kipas.
RAIM DALAM RANGKA MENDUKUNG IMPLEMENTASI SISTEM NAVIGASI PENERBANGAN BERBASISKAN SATELIT DI INDONESIA (RAIM IN THE IMPLEMENTATION OF SATELLITE BASED NAVIGATION IN INDONESIAN AIR TRAFFIC MANAGEMENT) Septiawan, Reza Septiawan; Sutedjo, Bayu; Sarotama , Afrias
Indonesian Journal of Aerospace Vol. 10 No. 1 Juni (2012): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Receiver Autonomous Integrity Monitoring (RAIM) is a method to monitor the integrity of GPS using mesurement to redundant satellites on the receiver side. Comonly 2 algorithm are used to perform RAIM, i.e. snapshot method and sequential method. In snapshot method, single set measurement of GPS signal is used, meanwhile in sequential method several sets of measurements (past and current) GPS signal are used. Therefore, the sequential method has the capacity to detect position failure due to low fault to noise ratio. The low fault to noise ratio is mostly caused by the satellite’s position at the time of position measurement. RAIM is very useful for GPS users to be able to determine the whether the GPS can give accurate position, based on its satellite’s positions, satellite’s service life or error in the receivers. Such accuracy is important especially for the use in GPS navigation sistem in Air Traffic Management (ATM). The disturbance can also be caused by ionosfer condition. In order to support the use of GPS navigation system in ATM in Indonesia, Communication Navigation Surveillance-ATM (GPS CNS-ATM) team of BPPT perform simply RAIM asessment that can be informed to the flightcrew or Air Traffic Center, to be informed via Notice To Air Men (NOTAM). The GPS signal observation is done in 5 different locations in Indonesia.
PENGARUH GANGGUAN LINGKUNGAN ANTARIKSA PADA SISTEM ELEKTRONIK LAPAN-TUBSAT (EFFECT OF SPACE ENVIRONMENT DISTURBANCE IN LAPAN-TUBSAT SATELLITE) Najati, Nayla
Indonesian Journal of Aerospace Vol. 10 No. 1 Juni (2012): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

LAPAN-TUBSAT has been operated more than five years. During the operation, LAPAN-TUBSAT faces several anomaly. It could be observed by using real time telemetry and long time telemetry. When and where an anomaly appeared can be detected with long time telemetry. Anomaly event on LAPAN-TUBSAT’s PCDH is caused by Single Event Latch-Up (SEL) that happen in scale of weeks.These conditions required LAPAN-TUBSAT operators to take action in order to make LAPAN-TUBSAT back to normal operation. This paper describes statistic of SEL that occur in LAPAN-TUBSAT. Almost 70% of SEL event take place at South Atlantic Anomaly (SAA) and the rest at polar.
FINITE ELEMENT MODELING OF LAPAN-A5/CHIBASAT DEPLOYABLE SOLAR PANEL COMPOSITE PLATE Triharjjanto, Robertus Heru; Budiantoro, Poki Agung
Indonesian Journal of Aerospace Vol. 16 No. 2 Desember (2018): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2018.v16.a3065

Abstract

LAPAN-A5/ChibaSat, that will carry synthetic aperture radar payload, requires a lot more power generation capacity, compared to its predecessor. Therefore, its solar panel will be deployed in orbit to ensure maximum sun exposure. Since the deployable system requires solar panel plate that lightweight and strong, honeycomb composite material is selected. The selection of such material requires special treatment in the satellite structural stiffness calculation. The objective of the research is to find simple stiffness model of the plate, so that later it can be integrated with the total satellite structural model and used by launch authority in its total vehicle modal analysis. The modeling used finite element software, and the simplified honeycomb model is validated using standar plate stiffnes problem. After model validation, the boundary condition as in the LAPAN-A5/ChibaSat deployable system is imposed. The result shows that the stiffness of the deployable solar panel plate has met the launch requirement of PSLV’s auxiliary payload. Therefore, the design mode can be used in the development of LAPAN-A5/ChibaSat. Â
PENINGKATAN KUALITAS FOKUS CITRA IMAGER MULTISPEKTRAL SATELIT LAPAN-A3 (IMAGE-FOCUSING QUALITY IMPROVEMENT ON LAPAN-A3 SATELLITE MULTISPECTRAL IMAGER) Tahir, Andi Mukhtar; Hakim, Patria Rachman; Syafruddin, A. Hadi
Indonesian Journal of Aerospace Vol. 14 No. 1 Juni (2016): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2016.v14.a2946

Abstract

Satelit LAPAN-A3 membawa imager multispektral sebagai muatan utama, yang memiliki empat kanal warna yaitu merah, hijau, biru, dan near-infrared. Sistem optik imager dirancang dengan menggunakan beam-splitter yang akan membagi cahaya yang melewati sistem lensa menuju detektor masing-masing kanal warna. Karena setiap detektor memiliki posisi dan juga orientasi yang berbeda terhadap pusat lensa, maka akan terjadi ketidakseragaman derajat kefokusan untuk setiap citra yang dihasilkan oleh masing-masing kanal warna, yang dapat mengurangi kualitas citra komposit yang dihasilkan. Penelitian ini bertujuan untuk meningkatkan kualitas citra komposit imager multispektral satelit LAPAN-A3 dengan cara memastikan agar setiap kanal warna akan menghasilkan citra dengan derajat kefokusan yang seragam. Metode yang digunakan yaitu dengan mengambil sejumlah data pengamatan terhadap obyek dengan pola geometri zebra-cross, dan kemudian diolah dengan menggunakan perangkat lunak Imatest. Penentuan kualitas fokus citra dilakukan dengan mengukur Modulation Transfer Function (MTF) pada frekuensi spasial tertentu. Berdasarkan sejumlah pengamatan dan perhitungan yang dilakukan, derajat kefokusan citra yang dihasilkan masing-masing detektor dapat diseragamkan dengan mengatur jarak detektor tersebut terhadap pusat lensa. Selain itu, percobaan yang dilakukan juga dapat mengurangi distorsi ko-registrasi kanal yang terjadi pada sumbu horisontal. Kedua hasil tersebut secara signifikan dapat meningkatkan kualitas citra imager multispektral satelit LAPAN-A3, terutama dalam aspek geometri. Hasil penelitian ini diharapkan dapat digunakan sebagai panduan dalam proses operasional satelit LAPAN-A3 selanjutnya dan juga dapat mendukung pengembangan imager multispektral eksperimen yang sedang dikembangkan untuk satelit LAPAN-A4.
METODE KALIBRASI RADAR TRANSPONDER ROKET MENGGUNAKAN DATA GPS (CALIBRATION METHOD OF RADAR TRANSPONDER FOR ROCKET USING GPS DATA) Widada, Wahyu
Indonesian Journal of Aerospace Vol. 10 No. 1 Juni (2012): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

This paper discusses the method of calibration of radar transponders for the rocket launch applications using GPS data. Calibration is performed by measuring the distance of two positions with GPS data and used as a reference for the calibration range radar transponder. Transponder is placed on the measured position and the radar transceiver is placed in a position of radar base station. The obtained results shows that the calibration method is very easy to do, reference to a longer distance can improve the accuracy result of the calibration. We obtained a calibration factor value for the radar system used in the experiment is 0.9275..Keywords: Radar transponder, GPS, Google-earth, Calibration method
RANCANG BANGUN PLATFORM GYMBAL UNTUK PAYLOAD UAV (DEVELOPMENT OF PLATFORM GYMBAL FOR UAV PAYLOAD) Prabowo, Gunawan S
Indonesian Journal of Aerospace Vol. 10 No. 1 Juni (2012): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Have been developing a platform gymbal sistem, this work beginning from conceptual desain, preliminary design, trade off component, and continued with critically design, analysis and integration in the laboratory. Also integration with kamera sistem for surveillance mission. This platform have designed to maintenance in Z direction axes. IMU is used for provide reference of airframe and servo as a actuator.In the parsial test, the eror in each axes is about 0,6º.

Page 19 of 37 | Total Record : 365

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