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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 6 Documents
 1 
Search results for , issue "Vol. 1 No. 1 (2003): Jurnal Teknologi Dirgantara" : 6 Documents clear
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.
PENGEMBANGAN POLIURETAN BERBASIS CPO SEBAGAI LINER ADHESIVE Heri BW,; Henny S; Geni R
Indonesian Journal of Aerospace Vol. 1 No. 1 (2003): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

In effort to increase the economic value of CPO (Crude Palm Oil), a research to use it as polyurethane raw material for the liner adhesive has been conducted. In order to get monoglyceride, CPO is glycerolized with glycerol, KOH is used as a catalyst and Pyridine solvent at 105 degree C for 4-8 hours. In the presence of isocyanate, such as TDI (Toluen Diisocyanate) monoglyceride as a diol becomes Polyurethane. Based on the adhesive strength test, this polyurethane polymer, produce a low conductivity and heat resistance up to 400 degree C(better quality compared with polyurethane to be used available in the local market). Therefore the polyurethane with CPO base a good potential material as a liner adhesive.
OPTIMASI PEMANFAATAN SISTEM PEMOMPAAN TENAGA ANGIN(SPTA) UNTUK SUMBER-SUMBER AIR DALAM DENGAN TURBIN ANGIN LISTRIK SUDU MAJEMUK SEBAGAI PENGGERAK POMPA Pakpahan, Sahat; Soeripno
Indonesian Journal of Aerospace Vol. 1 No. 1 (2003): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

The application of WInd Energy Conversion Systems (WECS) for supplying water for households, irrigation, livestock or other purposes have been developed to increase the contribution of renewable source of energy to support people, particularly at locations where accessibility to public utility networks not available or when the system itself needed by the consumer. Various WECS available in market as well as commercial pumps which can be used for bored hole., deep well or surface water and must be matched for optimal performance of the whole system; therefore, the analysis for selection of a pump due to its design characteristics for matching with an existing wind turbine that result-in optimal conditions of supply and demand has to be performed. A wind turbine with 6 blades rotor installed at BBUG samas Bantul is taken as a case study.
PREDIKSI TRAYEKTOR WAKTU-NYATA ROKET BALISTIK DENGAN MENGGUNAKAN GPS Widada, Wahyu
Indonesian Journal of Aerospace Vol. 1 No. 1 (2003): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

This paper described the real-time prediction of the trajectory of a balistic rocket based on gps data. The method was used a parabolic motion under the assumption of a constant gravitational acceleration. The algorithm was successfully applied to GPS flight data of a RX150 rocket launched at Pameungpeuk, Jawa Barat
RANCANGAN KAPAL UDARA (AIRSHIP) UNTUK VIDEO MONITORING DARI UDARA Sugiarmadji HPS; Robertus Heru T; Setiadi; Ediwan
Indonesian Journal of Aerospace Vol. 1 No. 1 (2003): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Remotely controlled non rigid helium airship type is chosen in airship design criteria for video monitoring. The design consists of airship dimensions and volume determination, maximum take of weight (MTOW) and W (weight empty plus payload) calculations, weight and structures analysis, airship stabilization analysis, airship guidance system, power plant system, position monitoring system, material and process, and payload systems. Here, Helium gas will be filled for generating a lift that is equal to the weight of the displaced air. An Airship Demonstrator Model LPN-01 is built to represent the design results. The model has length of L=8.5 m and 2.2 m diameter, so that the envelope volume is of 20 m. This Demonstrator Model will be used for studying capability or performance of airship, especially on ascent and descent manuever, airship's stability, position monitoring and payloads.

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