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Andri Agus Rahman
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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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PENGARUH DARI POSISI PUSAT MASSA ROKET YANG TIDAK TERLETAK PADA SUMBU AXIS SIMETRI TERHADAP DINAMIKA TERBANG ROKET BALISTIK (THE DYNAMIC OF THE ROCKET DUE TO THE OFFSET OF ITS CENTER OF MASS RELATIVE TO THE SYMMETRIC AXIS) Riyadl, Ahmad
Indonesian Journal of Aerospace Vol. 13 No. 2 Desember (2015): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Dalam uji terbang roket balistik kadang terjadi suatu gerakan wobbling yaitu suatu gerakan yang tidak linear menbentuk lintasan yang konus. Fenomena ini dapat terjadi dikarenakan berbagai sebab, dimana salah satu penyebabnya adalah posisi pusat massa roket yang tidak terletak pada sumbu axis simetri roket. Sehubungan roket LAPAN pada umumnya termasuk roket balistik maka perlu dilakukan penelitian untuk mengetahui kemungkinan dapat terjadinya gerakan wobbling pada saat uji terbang yang disebabkan oleh posisi pusat massa roket yang tidak terletak pada sumbu axis simetri. Dari hasil perhitungan pada penelitian ini terlihat bahwa posisi pusat massa roket yang tidak terletak pada sumbu axis simetri roket menyebabkan terjadinya gangguan momen roll, pitch dan yaw pada roket, dimana gangguan dari momen roll, pitch dan yaw tersebut memicu gerakan wobbling.
Full Pages JTD Vol 18 No.1 Juni 2020 Jurnal, Redaksi
Indonesian Journal of Aerospace Vol. 18 No. 1 Juni (2020): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

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IMPLEMENTASI CHIRP SIGNAL GENERATOR PADA FPGA UNTUK MISI PENCITRAAN LAPAN SURVEILLANCE AIRCRAFT - SYNTHETIC APERTURE RADAR (LSA-SAR) (IMPLEMENTATION OF CHIRP SIGNAL GENERATOR ON FPGA FOR IMAGING MISSION OF LAPAN SURVEILLANCE AIRCRAFT - SYNTHETIC APERTUR Tahir, Andi Mukhtar; Jayani , Ade Putri Septi
Indonesian Journal of Aerospace Vol. 13 No. 2 Desember (2015): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Radar bekerja dengan memanfaatkan sinyal gelombang elektromagnet yang dihasilkan olehperangkat waveform generator. Sinyal yang dipancarkan oleh radar akan dipantulkan sebagian olehtarget dan pantulan ini ditangkap oleh radar untuk diolah dengan cara membandingkan sinyal yangdipancarkan dengan sinyal yang dipantulkan kembali sehingga menghasilkan informasi berupakecepatan, jarak, atau citra dari suatu target. Waveform generator merupakan perangkat yang memegangperanan awal dalam sebuah sistem radar yang turut menentukan kinerja dari suatu sistem radar,oleh karena itu pada penelitian ini penulis akan membuat sebuah waveform generator sebagailangkah awal dalam percobaan di bidang teknologi radar. Waveform generator yang dibuatmenghasilkan sinyal chirp dengan menggunakan metode Direct Digital Synthesizer (DDS) yangmenggunakan memori yang lebih kecil dibandingkan Memory-based Chirp Generator, karena sinyalreferensi yang digunakan hanya berupa sebuah sinyal sinus dan cosinus. DDS chirp generator inidiimplementasikan pada board Field Programmable Gate Array Altera tipe Cyclone IV yang merupakandevelopment board produksi Terasic tipe DE2-115 dan menghasilkan keluaran berupa sinyal chirp.Hasil pengukuran sinyal keluaran menggunakan osiloskop menunjukkan sinyal chirp denganfrekuensi sampling 200 MHz, jumlah sample 6415 dan periode sampling 32 us, sedangkanpengukuran menggunakan spectrum analyzer terlihat terjadi pergeseran nilai frekuensi sehinggabandwidth tercapai sebesar 75,9 MHz. Namun secara keseluruhan hasil ini menunjukkan bahwasistem berjalan dengan baik.
THE COMPARATION OF TWO LAPAN'S PROPELLANTS OF DIFFERENT COMPOSITION Jihad, Bagus H.; Soemardi, Tresna P.; Priadi, Dedi
Indonesian Journal of Aerospace Vol. 5 No. 1 (2007): Vol 5, No.1 Juni (2007)
Publisher : BRIN Publishing

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Abstract

This paper compares two LAPAN'S propellant compositions. The A propellant has a composition of AP/AL/Binder with ratio of 70/10/20, and propellant B has ratio 75/7.5/17.5, both with HTPB base but different curing agent. As comparator of this simulation is RX-1512.01 rocket that has flight tested. The performances which compared are specific impulse and efficiency characteristic. Result shows that the propellant B gives higher specific impulse, however higher losses is, about 5.373 percent. One to be considered is that the propellant B produce combustion temperature higher than propellant A by 200 k, that may influence the rocket structures. Keywords: Impuls specific, characteristic efficiency, propellant, simulation.
DESAIN NOSEL ROKET CAIR RCX250 MENGGUNAKAN METODE PARABOLIK DENGAN MODIFIKASI SUDUT EKSPANSI Priamadi, Eko; Hakim, Arif Nur; Bura, Romie O
Indonesian Journal of Aerospace Vol. 9 No. 1 Juni (2011): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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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.
RANCANG BANGUN TABUNG KOMPOSIT TEKANAN TINGGI UNTUK PROPELAN ROKET CAIR KOROSIF (DESIGN OF COMPOSITE OVERWRAPPED PRESSURE VESSEL FOR CORROSIVE LIQUID ROCKET PROPELLANT) Hakim, Arif Nur
Indonesian Journal of Aerospace Vol. 13 No. 2 Desember (2015): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Rancang bangun tabung komposit tekanan tinggi (COPV) telah dilakukan untuk memperkecil berat struktur tabung propelan wahana roket cair. Tekanan operasi yang diharapkan dari tabung ini adalah 150 bar dan harus mampu menahan asam nitrat yang bersifat sangat korosif. Simulasi numerik dilakukan untuk memprediksi kekuatan struktur tabung SS304. Stainless steel SS304 dipilih sebagai tabung liner karena karakteristik ketahanan yang bagus terhadap korosi dan biaya yang relatif murah. Tabung liner kemudian dilapisi dengan serat karbon dan resin epoxy EPR 174 secara manual dengan metode hand lay up. Uji hidrostatik dilakukan untuk menguji kekuatan tabung dan uji X-ray digunakan untuk menganalisa kondisinya setelah uji hidrostatik. Berat riil tabung komposit adalah 9,1 kg, atau 67% dari berat tabung yang menggunakan SS304 setebal 5,5 mm. Hasil pengujian menunjukkan bahwa tabung komposit tersebut dapat menahan tekanan statis hingga 200 bar, namun masih ada sedikit kebocoran. Stretching dilakukan pada pembebanan pertama dengan menaikkan tekanan secara perlahan-lahan sehingga tabung akan meregang secara tepat dan menjaga komposit tetap terikat pada tabung liner dan dapat mencegah kegagalan struktur hingga tekanan 200 bar.
Front Pages JTD Vol 18 no.2 Desember 2020 Jurnal, Redaksi
Indonesian Journal of Aerospace Vol. 18 No. 2 Desember (2020): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

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OPTIMALIZATION OF MICROSTRIP SLOT ARRAY ANTENNAS FOR MULTI-WIDEBAND Fitri, Iskandar
Indonesian Journal of Aerospace Vol. 5 No. 1 (2007): Vol 5, No.1 Juni (2007)
Publisher : BRIN Publishing

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Abstract

Microstrip slot antenna fed by matching network of microstrip line to increase very wide-bandwidth and multiband is proposed. The microstrip line composed of multi tuning stubs is used to control slots antenna real impedance to match with impwdance cahracteristic of feeding line so that it could increase the bandwidth. The design are achieves good input impedance in the ranges frequency of 1.3 - 5.1 GHz for single slot and 1.1 - 6.4 GHz for two slots. The bandwidths of antennas become very wide if the slots made in array configuration. The measured return loss S11 agrees well with the simulation results for single slot as axample. Keywords: microstrip slot antenna, array configuration, network impedance, multi tuning stub.
DESAIN ALAT UJI NOSEL DENGAN MENGGUNAKAN PRINSIP TEROWONGAN ANGIN SUPERSONIK Jihad, Bagus H; Priadi, Dedi
Indonesian Journal of Aerospace Vol. 9 No. 1 Juni (2011): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

The accuracy of nozzle design can be improved by validation. Two methods of validation is software or hardware application. The software can be either CFD software or special software for the nozzle design, such as NOZZLE ® or Aerospike ®. The limitations of CFD software is on unsteady flow conditions. while the limitations of special software is the obscurity of assumptions used. Therefore, the flow validation experimental is important to be implemented. Lapan has three units of wind tunnels, namely subsonic, transonic and supersonic. They have the capability to measure the external flow of the body. While the nozzle design purpose is mostly to investigate the internal flow of the nozzle. Therefore, the nozzle flow testing system which is called a mini wind tunnel has been designed. This wind tunnel is designed to have speed of Mach 2.4, but the effective speed of 2 Mach. By using a calculation we obtain the run time of 46 seconds. If we assume the pressure drop is 40%, then actually the run time is 28 seconds.
SISTEM KONTROL SUN SEEKER SUATU MODEL UNTUK MENGENDALIKAN PERILAKU WAHANA ANTARIKSA Purwanto, Eko Budi
Indonesian Journal of Aerospace Vol. 5 No. 1 (2007): Vol 5, No.1 Juni (2007)
Publisher : BRIN Publishing

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Abstract

Sun seeker control system doing by monitoring the sun as main reference. The result of monitoring the sun position used for the line correction of space vehicle. In these paper used simulation method for gated parameter value control system. To know the influence of sun seeker control system, simulation was doing with and without lead compensator. The result of simulation show that without sun seeker control system the time settling is ts = 0.35 second and maximum overshoot Mp = 44,4 percent. These results not reasonable for controling of plan with high velocity like rocket and satellite. Later simulation with phase lead sun seeker control system, give settling time ts = 0,12 second and maximum overshoot Mp 5 percent. From the simulation data that sun seeker control system can used for space vehicle control and agree with steady state error specification.Keywords: Sun seeker control system, FFase lead, Waktu penetapan, lewatan maksimum, kondisi tunak

Page 23 of 37 | Total Record : 365

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