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Heri Budi Wibowo
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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 FAKTOR KOREKSI PERHITUNGAN TRAYEKTORI ROKET LAPAN, STUDI KASUS: RX200 LAPAN-ORARI (CORRECTION FACTOR ANALYSIS OF TRAJECTORY CALCULATION OF LAPAN'S ROCKET, CASE STUDY: RX-200 LAPAN-ORARI ROCKET) Novi Andria
Jurnal Teknologi Dirgantara Vol.11 No.1 Juni 2013
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Selama ini perbedaan profil trayektori antara hasil simulasi dengan hasil uji terbang roket-roket Lapan masih cukup besar. Upaya perbaikan perhitungan trayektori roket dikonsentrasikan pada tiga parameter yakni nilai koefisien gaya hambat (Cd), nilai kecepatan awal (Vi) dan penyekalaan gaya dorong. Perhitungan trayektori dilakukan menggunakan simulator trayektori roket berbasiskan Simulink yang dikembangkan oleh peneliti dinamika terbang - Lapan. Model RX 200 LAPAN-ORARI 2 digunakan sebagai wahana uji. Dibandingkan dengan hasil uji terbang, error terkecil perhitungan trayektori terdapat pada simulasi dengan menggunakan nilai Vi 0 m/s dengan menyekalakan gaya dorong sebesar 97% gaya dorong yang diperoleh dari uji statik tanpa adanya perubahan nilai Cd. Penelitian ini menyimpulkan bahwa penyebab utama tidak akuratnya perhitungan trayektori roket RX 200 LAPAN-ORARI adalah bukan karena tidak tepatnya nilai Cd yang di-input-kan. Keakurasian perhitungan trayektori dapat ditingkatkan dengan menetapkan nilai kecepatan awal seperti kondisi nyata yakni 0 m/s dan nilai gaya dorong yang tepat dengan menambah frekuensi uji statik untuk motor roket sejenis.Kata kunci: Trayektori roket, Akurasi, Koefisien gaya hambat, Kecepatan awal, Variasi gaya dorong
A FINITE ELEMENT ANALYSIS OF CRITICAL BUCKLING LOAD OF COMPOSITE PLATE AFTER LOW VELOCITY IMPACT Redha Akbar Ramadhan; Muhamad Giri Suada; Hendri Syamsudin
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.a3328

Abstract

Composite is a material formed from two or more materials that macroscopically alloyed into one material. Nowadays, composite has been generally applied as lightweight structure of aircraft. This is due to the fact that composites having high strength-to-weight ratio. It means the composites have the capability to take on various loads, despite their lightweight property.Laminate composite is one type of composite that has been generally used in aircraft industries. This type of composite is susceptible to low-velocity impact induced damage. This type of damage can be happening in manufacture, operation, or even in maintenance. Low-velocity impact could cause delamination. Delamination happens when the plies of laminated composites separated at the interface of the plies. This type of damage is categorized as barely visible damage, means that the damage couldn’t be detected with visual inspection. Special method and tool would be needed to detect the damage. Delamination will decrease the strength of the laminated composite.Delamination can be predicted with numerical simulation analysis. With increasing capability of computer, it is possible to predict the delamination and buckling of laminated composite plate. This research presents the comparisons of buckling analysis results on laminated plate composite and damaged laminated plate composite. By the result of LVI simulation, it is shown that low velocity impact of 19.3 Joule causing 6398 mm2 C-Scan delamination area inside the laminated composite. The delamination causing structural instability that will affect buckling resistance of the plate. The result of analysis shows that the existence of delamination inside laminate composite will lower its critical buckling load up to 90% of undamaged laminate’s critical buckling load.Keywords : composite, laminate, delamination, buckling.
TINJAUAN ASPEK KESELAMATAN UJI STATIK ROKET DENGAN PROPELAN KEROSEN–ASAM NITRAT TERHADAP MANUSIA DAN LINGKUNGAN Arif Nur Hakim; Azis Trianto; Pramujo Widiatmoko; Risky Darmawan
Jurnal Teknologi Dirgantara Vol 6, No.2 Desember (2008)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Roket propelan cair memiliki beberapa kelebihan bila dibandingkan dengan roket propelan padat. Jumlah dan perbandingan bahan bakar terhadap oksidator dapat diatur untuk menghasilkan gaya dorong yang diinginkan. Salah satu propelan yang digunakan saat ini adalah pasangan kerosen dan asam nitrat. Namun, penggunaan propelan ini memunculkan masalah akibat karakter propelannya. Asam nitrat adalah cairan yang sangat korosif dan dapat menyebabkan efek yang serius terhadap tubuh manusia. Tinjauan terhadap keselamatan dalam uji statik roket cair telah dilakukan. Pada uji statik, kerosen dan asam nitrat akan diinjeksi ke dalam ruang bakar dan bereaksi sehingga menghasilkan gas bertekanan dan bertemperatur tinggi yang kemudian disemburkan melalui nosel untuk menghasilkan gaya dorong. Dari hasil kajian, daerah pengujian dibagi menjadi 5 zona. Zona 1, daerah yang paling berbahaya berjarak 0 – 3 m, dan zona 2, 3 – 40 m, adalah daerah yang masih dipengaruhi oleh gas-gas berbahaya. Pengamatan langsung dapat dilakukan pada jarak 50 m dengan perlindungan bangunan.
OPTIMALISASI AKURASI ANTENA PENJEJAK SATELIT ORBIT RENDAH MENGGUNAKAN MOTOR STEPPER HYBRID 2 FASA (OPTIMIZATION OF LOW EARTH ORBIT TRACKING ANTENNA USING STEPPER MOTOR HYBRID 2-PHASE) Agus Herawan; Chusnul Tri Judianto
Jurnal Teknologi Dirgantara Vol.11 No.1 Juni 2013
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Untuk mendukung kinerja pemanfaatan satelit Lapan di orbit maka dibutuhkan sistem antena penerima yang handal di stasiun bumi. Kinerja sistem penerima data satelit orbit rendah ini sangat ditentukan oleh akurasi motornya disamping sistem RF Front (LNA, Feed, Cable dan Receiver) yang digunakan dalam menjejak satelit yang bergerak sangat cepat pada orbit rendah. Kecepatan pergerakan satelit pada orbit rendah pada ketinggian sekitar 630 km adalah 7.5 km/detik. Dengan kondisi tersebut sistem antena membutuhkan motor penggerak antena dengan akurasi yang tinggi agar penjejakan terhadap pergerakan satelit akan tetap terjaga dan antena selalu dalam posisi line of sight tanpa terjadi kehilangan sinyal. Agar diperoleh sistem antena yang handal dengan akurasi pergerakan motornya yang lebih baik, maka digunakan rancangan motor stepper Hybrid 2 phase. Motor stepper standar ini memiliki akurasi 1,8/step, dengan menambah rancangan gear dengan perbandingan 100:1 sehinga diperoleh akurasi motor 0.018/step. Detail Rancangan dan implementasi sistem motor stepper ini akan dibahas dalam tulisan ini.Kata Kunci: Motor stepper hybrid, Orbit rendah, Antena penjejak satelit
DESAIN NOSEL ROKET CAIR RCX250 MENGGUNAKAN METODE PARABOLIK DENGAN MODIFIKASI SUDUT EKSPANSI Eko Priamadi; Arif Nur Hakim; Romie O. Bura
Jurnal Teknologi Dirgantara Vol 9, No. 1 Juni (2011)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

 The present research is conducted to design the optimum nozzles for RCX250 engine, that is designed to produce maximum thrust of 250 kgf with combination of LOX and Kerosene as its propellant. The new nozzles were determined to be parabolic nozzle, with conical nozzle as its comparison. The parabolic nozzle was designed using Thrust Optimized Parabolic (TOP) method invented by G.V.R.Rao. TOP nozzle design method is performed by approximating a Thrust Optimized Contoured (TOC) Nozzle using parabolic equation. The method would result more efficient nozzle than conical or ideal bell nozzle. Further, the parabolic nozzle were modified in its initial and exit angle to create uniform velocities distribution at nozzle exit. A Computational Fluid Dynamics Method (CFD) is used to simulate the nozzle designs. The simulation was carried out in axis-symmetric condition using commercial CFD software. The simulation results show that MOD 1 nozzle, with initial angle (θN) 26 deg and exit angle (θe) 12 deg, gives maximum thrust, which is 4.67 % higher than reference conical nozzle. Key words:Liquid rocket, Parabolic nozzle, Thrust, CFD
(AUTOMATIC IDENTIFICATION SYSTEM (AIS) SATELIT DATA CORRECTION USING INTERPOLATION AND EXTRAPOLATION METHODE, (Case Study : LAPAN-A2 and LAPAN-A3 Satellite)) Abdul Karim
Jurnal Teknologi Dirgantara Vol. 16 No. 2 Desember 2018
Publisher : National Institute of Aeronautics and Space - LAPAN

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.
RANCANGAN DAN ANALISA SISTEM ORIENTASI TURBIN ANGIN KAPASITAS 2,5 KW Agus Bayu Utama
Jurnal Teknologi Dirgantara Vol 6, No.1 Juni (2008)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Telah dirancang satu sistem orientasi dengan rotor eksentrik dan ekor pengarah dengan hinge (sumbu gantung) untuk turbin angin skala kecil kapasitas 2.5 kW, kemudian dilakukan analisa statis rumusan matematis berdasarkan teori kesetimbangan momen pada sumbu menara pada 2 kondisi kecepatan angin yaitu kecepatan angin sampai kecepatan angin rancagan (V ≤ Vdisain) dan kecepatan angin di atas kecepatan angin rancangan (V > Vdisain). Dengan kecepatan angin rancangan Vdisain = 10 m/s, maka nilai γo (sudut serang angin terhadap daun ekor) pada kondisi V ≤ Vdisain , adalah 6.16°. Nilai berat ekor G yang tadinya 250 N harus diturunkan menjadi 209 N, yaitu dengan mengubah nilai berat batang ekor menjadi m1=12.5kg dan nilai berat daun ekor menjadi m2=8.4 kg. Pada kondisi V > Vdisain rotor mulai berputar dengan sudut serang angin terhadap rotor δ.
PENGEMBANGAN METODE PENENTUAN KARAKTERISTIK RANCANGAN AWAL ROTOR TURBIN ANGIN Sulistyo Atmadi; Ahmad Jamaludin Fitroh
Jurnal Teknologi Dirgantara Vol 5, No.1 Juni (2007)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

A method for determining design characteristics of a wind turbine rotor has been developed. Given the desired power and operational wind speed, the approximate design diameter and rotor rpm can then be determined. The size of the rotor diameter is governed by the blade performance, in which is normally given as power coefficient Cp; designed rotor spedd can be known after calculating the tip spedd ratio. Using this method, the blade and rotor characteristics can be designed quickly as a preliminary design parameter. Keywords: Rancangan awal, Koefisien daya, Tip speed ratio.
APLIKASI PERANGKAT LUNAK SISTEM AKUISISI KECEPATAN REACTION WHEEL (SOFTWARE APPLICATION OF REACTION WHEEL SPEED ACQUISITION SYSTEM) Harry Septanto
Jurnal Teknologi Dirgantara Vol. 15 No. 2 Desember 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.v0.a2870

Abstract

Transfer of technology activity through reverse engineering is an effort done by developing country in order to decrease technology gap, including in satellite technology, from developed country. To perform measurement anddata acquisition in order to extract design information of a satellite component are the first step in reverse engineering process. This paper reports the result of research on the development of data acquisition software for satellite actuator called reaction wheel speed. In satellite development phase, the wheel speed acquisition system is also possible to be utilized as a testing tool for componente level verification. The wheel speed data obtained from the experiment was represented in graphic of transient response. Based on the data analysis, the developed data acquisition system was possible to be utilized to measure dynamic characteristic of the reaction wheel unit in order to extract its design information. Meanwhile, the analysis done has represented basic part of component level verification test. This fact showed that the developed acquisition system was also possible to be used as testing tool in satellite development phase.  ABSTRAKKegiatan alih teknologi melalui reverse engineering merupakan upaya yang dilakukan oleh negara berkembang dalam rangka memperkecil jarak ketimpangan dari negara maju dalam hal teknologi, termasuk teknologi satelit. Melakukan pengukuran dan akuisisi data dalam rangka mengurai informasi desain suatu komponen satelit adalah tahap pertama proses reverse engineering. Makalah ini melaporkan hasil penelitian mengenai pengembangan perangkat lunak sistem akuisisi data kecepatan wheel dari sebuah aktuator satelit yang disebut reaction wheel unit. Dalam aspek fase pengembangan satelit, sistem akuisisi data ini dapat digunakan sebagai perangkat pengujian untuk verifikasi di tingkat komponen. Data kecepatan wheel, yang diperoleh dari eksperimen yang dilakukan, ditampilkan dengan grafik respon transien. Berdasarkan analisis atas data tersebut, sistem akusisi data yang dikembangkan menjanjikan untuk digunakan dalam rangka pengukuran karakteristik dinamik reaction wheel sebagai upaya mengurai informasi desainnya. Selain itu, analisis yang telah dilakukan merepresentasikan bagian dasar dari tahap verifikasi di tingkat komponen. Hal ini menunjukkan bahwa sistem akusisi data ini menjanjikan untuk digunakan sebagai perangkat pengujian di dalam fase pengembangan satelit.
AKTIVASI LITIUM SEBAGAI KATALISATOR PADA REAKSI PEMBENTUKAN HTPB Heri Budi Wibowo; Geni Rosita
Jurnal Teknologi Dirgantara Vol 2, No.2 Desember (2004)
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2004.v2.a804

Abstract

HTPB usually used as propellant fuel binder. This paper studied anionic polymerization of butadiene to form HTPB (Hydroxy Terminated Polybutadiene) with litium as catalyst. In practice, litium must be reactivated to remove antioxidant that surround it. Butadiene is polymerized in a 250 mL autoklave at room temperature and free oxygen. Litium was reactivated by melting and deforming. The polymer form was terminated by ethylene oxide to form HTPB. After it was washed by benzene and aquadest, HTPB structure was analyzed with FTIR at 910 cm and 970 cm. Investigation of the polymerization could produced HTPB if litium as catalyst was reactivated. HTPB resulted contain maximum 30 percent structure cis-1,4 HTPB. The average molecule weight can be control very well based on amount of litium (catalyst).

Page 14 of 34 | Total Record : 333

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