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Heri Budi Wibowo
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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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ESTIMASI BIAYA DAUR HIDUP DAN OPTIMISASI HARGA PESAWAT TERBANG Rais Zain; Odi Ahyarsi
Jurnal Teknologi Dirgantara Vol 9, No. 1 Juni (2011)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

 Since the conceptual design phase, the estimate of airplane life cycle cost (LCC) is carried out to support a decision making process. The LCC consist of research, development, testing, and evaluation cost, where an airplane estimated price (AEP) is a part of this calculation. Furthermore, AEP is employed as a non linear objective funtion for developing a constrained optimization algorthm. Rosen’s gradient projection is applyed in the development of computer program named Cost Analysis implementing object oriented approach on Microsoft Visual C++ 6.0. In order to verify the application, some data of Ourania jet airplane were utilized for carrying out a case study. The result of Cost Analysis shows that the estimated LCC are similar to the reference. Also, the optimization problems can be solved by Rosen’s algorithm less than ten iterations. Keywords:Conceptual aircraft design, Life cycle cost, Object oriented approach, Visual C++
Analisis Kekuatan Struktur Komposit Dengan Ply Drop-off Pada Roda Pendarat Utama Pesawat Nir Awak Menggunakan Metode Elemen Hingga Fajar Ari Wandono
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.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%.
ANALISIS SISTEM PAYLOAD UNTUK SATELIT IMAGER LAPAN Gunawan S. Prabowo; Ery Fitrianingsih
Jurnal Teknologi Dirgantara Vol 6, No.1 Juni (2008)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Berbasis pada informasi persyaratan misi dan berbagai masukan tentang kebutuhan satelit untuk mendukung program ketahanan pangan, serta dikaitkan dengan program LAPAN dalam proses penguasaan teknologi sistem satelit mikro, maka dibuatlah sebuah konsep pengembangan satelit yang memadukan penguasaan teknologi dan aplikasi riel untuk remote sensing. Dalam paper ini akan disampaikan analisa beberapa sistem muatan untuk mendukung program ketahanan pangan, dianalisis 3 buah sistem kamera yang akan dipergunakan sebagai muatan pokok dari satelit Imager LAPAN.
IMPLEMENTASI STASIUN BUMI TT AND C SATELIT LAPAN-TUBSAT DI BIAK Chusnul Tri Judianto
Jurnal Teknologi Dirgantara Vol 5, No.2 Desember (2007)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

LAPAN-TUBSAT as a satellite pioner project established by LAPAN finally successfully launched on 10 January 2007. The usage of the main payload of the satellite especially can be used for capturing the surface of the globe. All data are captured by the camera in the video analog format and will be transmitted through s-band frequency in FM video modulation. For controlling the attitude and monitoring the health of the satellite, all data telemetry will be transmitted to the ground station on UHF frequency (437,325 MHz). The space craft control center for LAPAN-TUBSAT satellite has been established in Rumpin Bogor. This station will cover from west part until centre part of Indonesia's archipelago. Rumpin ground station situated on 6.22 Deg South and 106.37 Deg East. For covering entire part of Indonesia, its planed to establish a new ground station in Biak Island PApua at 1.17 Deg South and 136.1 Deg East. Design until implementation of this ground station will be elaborated deeply in this paper. Keywords: LAPAN-TUBSAT, TT and C Ground station.
Full Pages JTD Vol 14 No 1 Juni 2016 Redaksi Jurnal
Jurnal Teknologi Dirgantara Vol. 14 No. 1 Juni 2016
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2016.v14.a2923

Abstract

KARAKTERISTIK DINAMIKA STRUKTUR SATELIT MIKRO LAPAN-TUBSAT Robertus Heru Trihajanto; - Sugiarmadji HPS
Jurnal Teknologi Dirgantara Vol 3, No.2 Desember (2005)
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2005.v3.a814

Abstract

The TUBSAT-LAPAN micro satellite is planned to be launched using PSLV rocket. The design constraints of the mechanical system of the satellite are able to accomodate structural requirment for PSLV, which are first resonance frequency in the rocket longitudinal axis 90 Hz and first resonance frequency in the lateral axis 45 Hz. Therefore, the structural dynamic characteristic data of the satellite is important to be evaluated, such as natural frequency and mode shapes of the satellite structures, The normal modes analysis made is done usingh Finite Element Methods commercial software NASTRAN. To simplify the FEM modeling the satellite components inside the compartmens is replaced by a dummy load simulating their contribution to satellite mass, centerof gravity and inertia, which was made by the same material as the satellite's structure, i.e. Al-Alloy 2024T351. Meanwhile, the FEM modeling for both the UHF antena used the Stainless Steel materials as the real antena. The analysis results show that the lowest local natural frequency of the satellite occurs on the UHF antena. The first natural frequency of the antena structures in lateral direction is 52,29 Hz. The first natural frequency of the satellite in lateral direction 151.47 Hz completing the satellite integration, vibration test was done to the satellite. The test shows that the first global frequency is 72-75 Hz in the lateral direction and 148 Hz in longitudinal direction. Structural dynamic characteristic of TUBSAT_LAPAN micro satellite in free flying condition are also analyzed using no-constraint condition to check the safe separation clearance scenario. The results show that the first natural frequencies for satellite structures (combination) become very small, less than 0.00032 Hz. But, the lowest of the first natural frequency for UHF antena structures is almost constant, 52.30 Hz in lateral direction.
PERUBAHAN KARAKTERISTIK PEMBENTUKAN POLIURETAN BERBASIS HTPB DAN TDI BERDASARKAN KOMPOSISI REAKSI (CHANGES IN THE FORMATION CHARACTERISTICS OF POLYURETHANE BASED ON HTPB AND TDI REACTION COMPOSITION) Geni Rosita
Jurnal Teknologi Dirgantara Vol. 14 No. 2 Desember 2016
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2016.v14.a2420

Abstract

Polyurethane formation occurs through crosslinking of a reaction between the hydroxyl group (OH) of HTPB and isocyanate (NCO) of TDI. Polymer network formation reaction will be formed from the linear bond and a combination of crosslinking. At longer reaction, the polyurethane chains are formed increasingly long and followed by changes in the characteristics. If the reaction has been perfect then the polyurethane chain is  straight and it will become more flexible.  This research aimed to obtain polyurethane as fuel binder, which was indispendable in solid composite propellant manufacturing.Several samples of existing HTPB were made into a different composition of HTPB/TDI. The process used  reaction kinetics methods based on the composition in order to obtain the mechanical properties of polyurethane.  Average molecular weight, crosslinking density, hardness, and swelling were analized to determine the quality of polyurethane as fuel-binder. The analysis was a consideration for determining the most suitable fuel-binder composition. It was also to test the quality of experimental HTPB produced by LAPAN HTPB Laboratory (HTPBlocal) as an initial procedure in the propellant manufacturing. The analysis showed different results for each composition. The compositions that could be used as the fuel-binder for the formation of polyurethanes were: HTPBA at 7: 1; HTPBB at 9: 1; HTPBC at 8: 1; and HTPBD at 8: 1; whereas HTPBE could not be used because required advanced processing. Abstrak:Pembentukan poliuretan terjadi melalui ikatan silang dari hasil reaksi antara gugus hidroksil (OH) dari HTPB dan gugus isosianat (NCO) dari TDI. Reaksi pembentukan jaringan polimer akan terbentuk dari hasil ikatan linier dan kombinasi ikatan silang. Semakin lama reaksi maka panjang rantai poliuretan yang terbentuk semakin panjang dan diikuti dengan perubahan karakteristik. Apabila reaksi telah sempurna maka rantai poliuretan adalah rantai lurus dan akan menjadi lebih fleksibel. Penelitian ini untuk memperoleh poliuretan sebagai fuel-binder yang diperlukan untuk pembuatan propelan padat komposit. Dari beberapa macam sampel HTPB yang ada, dibuat menjadi beberapa komposisi HTPB/TDI yang berbeda. Prosesnya menggunakan metode kinetika reaksi berdasarkan komposisi tersebut untuk mendapatkan sifat mekanik poliuretan. Untuk mengetahui kualitas poliuretan sebagai fuel binder dilakukan analisis berat molekul rata-rata ikatan silang, kerapatan ikatan silang, kekerasan, dan swelling (derajat pengembangan polimer) sebagai bahan pertimbangan untuk menentukan komposisi fuel binder terpilih dan juga untuk menguji kualitas HTPB hasil experimen Lab HTPB LAPAN (HTPBlocal). Analisis menunjukkan hasil yang berbeda-beda untuk masing-masing komposisi. Komposisi yang dapat digunakan sebagai fuel-binder untuk pembentukan poliuretan adalah: HTPBA pada 7:1; HTPBB pada 9:1; HTPBC pada 8:1; dan HTPBD pada 8:1; sedangkan HTPBE tidak dapat digunakan karena masih membutuhkan pengolahan lanjutan.
PENGARUH NILAI KOEFISIEN AERODINAMIKA DAN PADA KESTABILAN TERBANG GERAK PERIODE PENDEK (SHORT PERIOD) RKX-200 LAPAN [EFFECT OF AERODYNAMICS COEFFICIENT VALUE AND TO THE STABILITY OF THE FLY MOTION SHORT PERIOD RKX-200 LAPAN] Endang Mugia GS
Jurnal Teknologi Dirgantara Vol.10 No.2 Desember 2012
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

The rocket flew of short period modes of motion, can be used as a way to measure the stability of the rocket flying. By performing simulation using software Missile DATCOM obtained aerodynamic coefficient and , each of which affects the value of the natural frequency and damping motion short period. RKX-200 Lapan rocket is a quite stable rocket. And the magnitude of the aerodynamic coefficient : -0,12 to -.0,02 and value of : -2,4 to -1,2, with each value remains negative at cruising speed prediction of 0,1 M s.d 2,0 M. It’s good enough to be the guided missile with value 0,18  SM  0,46. Key words: A short period modes of motion
INCREASING DATA TELEMETRI SOUNDING ROCKET LAPAN WITH PULSE CODE MODULATION METHODE effendi dodi arisandi
Jurnal Teknologi Dirgantara Vol. 18 No.1 Juni 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.a3353

Abstract

The telemetry data of the sounding rocket when flight in the space is very important to known. This data will be used for next mission or evaluation the last rocket flight. Commonly the data of the sensor in the sounding rocket are accelerometer, gyroscope, magnetometer, GPS and so on. As much data as possible than can be sent to the ground control system when the rocket flies. The problem is when the baud rate is low so not much data can be transmitted. Another problem is when the using serial bit standard communication such as the baud rate is 115.200 which mean that the maximum data in one second is 14,400 characters. It is less than when using the PCM bit rate. Application of PCM in the telemetry for sounding rocket LAPAN is new and need development to reach the optimal. With the PCM method the communication data can transmit around 1.25Mbps or 156,250 characters based on the TR FM02-S-2 full S-band transmitter. In this research, focus to the implementation the PCM method on the FPGA for sending and receiving the data via cable. Two FPGA boards can work together for sending and receiving data with PCM method with the total bit is 1.25Mbps.
ANALISIS PENGUKURAN KETIDAKSTABILAN BIAS DARI SENSOR GYRO FORS-4 SATELIT LAPAN-A2 Hasan Mayditia
Jurnal Teknologi Dirgantara Vol 6, No.2 Desember (2008)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Bias instability (drift atau offset) merupakan salah satu jenis deviasi (error) pengukuran yang pasti ditemukan di dalam sensor-sensor inersial seperti halnya rategyro. Nilai error ini berbeda untuk setiap unit sensor, sehingga pengukuran nilai bias untuk masing-masing unit harus dilakukan. Ini dilakukan untuk memperoleh unitunit sensor dengan performa yang terbaik. Pengukuran nilai error bias (drift) telah dilakukan pada keenam unit sensor gyro (tipe FORS-4) dengan memanfaatkan pergerakan rotasi bumi sebagai nilai referensi. Empat dari enam unit sensor gyro telah dipilih untuk selanjutnya digunakan dan diterbangkan pada satelit LAPAN-A2.

Page 17 of 34 | Total Record : 333

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