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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 364 Documents
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ON-BOARD FUNDAMENTAL FREQUENCY ESTIMATION OF ROCKET FLIGHT EXPERIMENTS USING DSP MICROCONTROLLER AND ACCELEROMETER Syah, Agus Harno Nurdin; Kliwati, Sri; Widada, Wahyu
Indonesian Journal of Aerospace Vol. 7 No. 1 Juni (2009): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Fundamental frequency vibrasi roket pada saat terbang sangat penting diukur untuk pengembangan sistem elektronik maupun mekanik muatan roket. Tulisan ini membahas metode pengukuran fundamental frekuensi tersebut dengan menggunakan sensor accelerometer dan 32 bit DSP (Digital Signal Processor) microcontroller. CPU ini digunakan untuk akuisisi data dan perhitungan algoritma DFT (Discrete Fourier Transform) serta algoritma penentuan frekuensi fundamentalnya. Deteksi fundamental frekuensi berbasis envelope (lowpass filter) spektrum frekuensi. Sistem yang telah dibuat dapat dikombinasikan dengan radio modem untuk pengiriman data dengan kecepatan serta sampling rate yang cukup tinggi. Maksimum frekuensi yang dapat diestimasi hingga 2 kHz, cukup untuk parameter roket.
ANALISA PENGARUH SUDUT PITCH, UNTUK MEMPEROLEH DAYA OPTIMAL TURBIN ANGIN LPN-SKEA 50 KW PADA BEBERAPA KONDISI KECEPATAN ANGIN Atmadi, Sulistyo; Fitroh, Ahmad Jamaludin
Indonesian Journal of Aerospace Vol. 7 No. 1 Juni (2009): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Kurva daya merupakan indikator utama prestasi sebuah turbin angin. Dengan sudut pitch tertentu, turbin angin mempunyai kurva daya yang tertentu juga. Rotor dirancang agar turbin angin LPN-SKEA 50kW dapat menghasilkan daya 50 kW pada kecepatan angin 10 m/det dan kecepatan putar 80 rpm. Penambahan sudut pitch biasanya dilakukan untuk menambah torsi awal rotor sehingga rotor menjadi lebih mudah berputar dari kondisi diam. Pengaruh penambahan sudut pitch adalah berkurangnya kecepatan putar rotor sehingga daya yang dihasilkan juga menjadi lebih kecil. Hasil perhitungan menunjukkan bahwa penambahan sudut pitch hingga 10ยบ akan mengurangi daya dari 50 kW menjadi 23,3 kW pada kecepatan angin 10 m/det. Dengan penambahan sudut pitch yang sama dan dengan mengasumsikan bahwa kurva daya merupakan polinomial pangkat tiga, maka daya sebesar 50 kW dapat dicapai pada kecepatan angin 12,9 m/det.
ANALISA POTENSI ENERGI ANGIN DAN ESTIMASI ENERGI OUTPUT TURBIN ANGIN DI LEBAK BANTEN MS, Soeripno; Ibrochim, Malik; Widodo, Thomas Sri
Indonesian Journal of Aerospace Vol. 7 No. 1 Juni (2009): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Analisa potensi energi angin untuk daerah Lebak Banten dilakukan dengan metode simulasi dengan data masukannya berupa peta vektor dan data kecepatan angin hasil pengukuran selama setahun periode bulan Maret 2006 - Maret 2007. Output simulasi dengan menggunakan software WAsP menghasilkan kecepatan angin rata-rata tahunan sebesar 5,86 m/s dan rapat daya angin rata-rata tahunan sebesar 225 W/m2. Lokasi yang dianalisa adalah area terbuka dengan sedikit rintangan (obstacles) berupa bukit-bukit kecil dan pepohonan yang tidak rapat serta tersebar, sehingga nilai hasil simulasi menggunakan peta vektor untuk parameter indikator RIX diambil nilai rata-rata sebesar 1,0%, sehingga gesekan antara laju angin dengan obstacles relatif kecil. Dengan mengasumsikan dipasang SKEA kapasitas 1,5MW di lokasi tersebut maka nilai rata-rata energi listrik yang dapat dihasilkan oleh SKEA tersebut dalam setahun adalah sebesar 3,263 GWh/tahun.
PENGARUH KETIDAKLURUSAN DAN KETIDAKSIMETRISAN PEMASANGAN SIRIP PADA PRESTASI TERBANG ROKET RX-250-LPN Atmadi, Sulistyo; Riyadi, Ahmad
Indonesian Journal of Aerospace Vol. 1 No. 2 Desember (2003): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2003.v1.a778

Abstract

The performance of a rocket depend on several factor, one of which is the value of drag experienced during flight. This drag is contributed by the shape and the many components of the rocket. This paper discussed the fin misalignment and asymetrisness in respect to its main axis, which results in a change in the drag of RX-250-LPN rocket. The discussion was conducted with assuming the variation of this fin alignment from 1 degree to 2 degree. DATCOM was used to obtain aerodynamic parameters of the rocket. In addition, MATLAB 6.3 was used to calculate the performance of rocket. The knowledge of this fin misalignment can be used to get the minimum accuracy needed for better fin setting during rocket assembly.
PERHITUNGAN BEBAN KRITIS STRUKTUR PLASTIS DENGAN MENGGUNAKAN METODE SOUTHWELL Sebayang, Darwin
Indonesian Journal of Aerospace Vol. 1 No. 2 Desember (2003): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2003.v1.a779

Abstract

The structure of the cylinder can be found in the structure of a rocket, an aircraft of chimney. The stability of the cylinder is very important to know the capability cylinder to support the load. It is required to give a load up to plastic region in order to optimize the load capability of the material. Therefore it is required to obtain the procedure to calculate the plastic buckling. Herewith it is shown the Southwell's Method to calculate the plastic buckling of the cylinder made of the non linear material. The approximation based on the Ramberg-Osgood is used to illustrate the stress-strain diagram. The diagram of Karman is used to obtain the Modulus of elasticity which is valid for the plastic region. The result based on this method are campared to the experimental data. The results are satisfactory. This method can be used to calculate the critical load of the LAPAN's rocket by considering the plasticity of the material and structure can be lighter.
PENGARUH TEMPERATUR SISTEM PADA FIGURE OF MERIT STASIUN BUMI PITA S DAN PITA X Surjo, Achmadi; Atmadi, Sulistyo
Indonesian Journal of Aerospace Vol. 1 No. 2 Desember (2003): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2003.v1.a780

Abstract

One of the veri important in a satellite communications system is the figure of merit for space segment as well as for the ground segment. The parameter which will be discussed in this paper is the figure of merit of a ground station of S band and X band for remote sensing system application. The parameters which influences it are antenna gain and temperature of system. The antenna which will be used is parabola antenna whose magnitude gain depends on diamter and efficiency of reflector. While the ground station antenna moves to track the desired satellite, so the elevation angle changes as well as the azimuth angle. On S band system influence of rain cab be ignored, while on the X band the influence needs to be considered. From the analysis conducted at 0.1 time percentage, the result is influence of rain to the "figure of merit is necessary to be estimated.
PENELITIAN PEMBUATAN POLI METIL METAKRILAT Wahyuni, Dwi; Dewi, Sri Rukmini
Indonesian Journal of Aerospace Vol. 1 No. 2 Desember (2003): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2003.v1.a781

Abstract

The poly methyl methacrylate (PMMA) research has been excecuted. Methyl methacrylate is polymerized by the free radical inisiation with the suspension condition using benzoyl peroxyde inisiator, water as a solution and the gelatine stabilizer, in this reseaarch is executed as a standard ratio (part per part:monomer : water : stabilizer = 100 : 350 : (0.1 1) with the inisiator to monomer ratio variation (part per part) are: 0.1 per 50; 0,175 per 50; 0,25 per 50; 0,25 per 50, the temperature variation are : 30 degree C, 45 degree C, 60 degree C and the time polymerization until 320 minutes. The result showed that the optimum monomer polymerizeation was at the inisiator to monomer ratio 0,25 per 50, the temperature at 45 degree C and at the time polymerization until 300 minutes with the monomer conversion was 86 percent. The Infra Red Spectroscopy analyses showed that there are poly methyl methacrylate in the product. The Gas Liquid Chromatography analysis showed the evolution of the monomer (methil methacrylate concetration.
RANCANGAN AWAL SISTEM KOMUNIKASI SATELIT IMAGE PROCESSING LAPAN-TUBSAT Suwarjo, Minto
Indonesian Journal of Aerospace Vol. 1 No. 2 Desember (2003): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2003.v1.a782

Abstract

The LAPAN-TUBSAT is a joint reseaverd between LAPAN and TECHNICAL UNIVERSITY OF BERLIN for image processing application. The satellite will be built in with half-duplex transmission system, with uplink frequency is uHF-band 435.075 Mhz in minimum data rate 1200 pbs, while the downlink frequency is S-band 2.2 GHz use data rate 38400 bps. The uplink frequency will functioned for command and donwlink frequencies for telemetry data and image data. The main communication payload consists of transmitter and antenna s-band, tranceiver and antenna UHF-band, two cameras with resolution 50 mm and 1000 mm with PAL standard, data and video multiplexes, on borad data handling and power control unit. The ground station consists of TT and C operates in UHF-band and ground receiver processing operates in S-band frequency. The minimum image signal quality received is 45 dB for BER 10.
RANCANGAN MISI LAPSAT-2 FM Adrianti P.S.; Prabowo, Gunawan S; Mukhtar, Andi; Nasser, Eriko; Mukhayadi, M.
Indonesian Journal of Aerospace Vol. 1 No. 1 (2003): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Now adays, itis widelly used the term Nano-satellite when we refer to those satellites whose mass less than about 10 kg. The design of LAPSAT-2 FM has weight more than 10 kg and less then of 15 kg but we consider as a nano-satellite continuing the previous design LAPSAT-1, This satellite designed as technology demonstrator, carrying store-and forward communication and remote sensing missions. Satellite build together with Malaysia in a same mission in parallel separately. This paper, discussed about mission definition and analysis referring to orbit, payload, budget and launch alternative and also mission operation.
PERANCANGAN TABUNG MOTOR ROKET RX-150-LPN BERDASARKAN ANALISIS PERHITUNGAN DAN EKSPERIMEN Bintoro, Atik
Indonesian Journal of Aerospace Vol. 1 No. 1 (2003): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

The rocket motor tube is primary construction of rocket motor, this function is as combustion propellant chamber. The inner pressure will be produced in the tube during the combustion process running and produce structural stress. That's why the tube design is necessary to look the tube endurance of the structural stress. Besides this, the structural weight factor often become constrains, cause the supply of the material structural has light and strength property was limited. Whit concern for the structural stress and the structural weigth, it has been design the tube of RX150-LPN rocket motor, by analysis and experiment method. The analysis method was run affinity by finite element method, and the experiment method affinity by static test of the rocket motor tube. The design has purposed to find the strength and stiffness tube construction and was made the material light relative property. From the design was found characteristic of the product design is in tin of wall= 33mm, inner diameter=15 cm, length of tube=1,4 m, material=alloy steel AISI H11, weigth=17 kg and the prototype has endurance with 35 kg per cm on inner pressure.

Page 34 of 37 | Total Record : 364

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