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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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RANCANG BANGUN ENJIN ROKET CAIR DENGAN GAYA DORONG 1000 KGF MENGGUNAKAN PROPELAN ASAM NITRAT – KEROSEN (DESIGN OF LIQUID ROCKET ENGINE WITH 1000 KGF THRUST USING NITRIC ACID – KEROSENE PROPELLANT) Hakim , Arif Nur
Indonesian Journal of Aerospace Vol. 13 No. 1 Juni (2015): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Enjin roket cair bergaya dorong maksimum 1000 kgf dengan pendinginan regenerative menggunakan fuel telah dirancang sebagai langkah awal untuk menjawab kebutuhan sistem propulsi roket yang memiliki impuls spesifik yang lebih tinggi, waktu pembakaran yang lebih lama dan kemampuan kontrol untuk Program Roket Pengorbit Satelit. Enjin didesain menggunakan pasangan asam nitrat dan kerosen avtur masing-masing sebagai oksidator dan fuel dengan sistem pengumpan gas inert bertekanan untuk mendorong propelan ke ruang bakar. Untuk mendistribusikan propelan, enjin mengadopsi injektor tipe impinging stream dengan 3 jet asam nitrat menabrak 1 jet kerosene yang dikelilinginya. Uji subsistem dilakukan untuk mengetahui kinerja masing-masing komponen enjin, sedangkan uji bakar dilakukan untuk mengetahui kinerja enjin secara keseluruhan. Hasil pengujian menunjukkan bahwa enjin ECX1000H2 dengan injektor konfigurasi kedua dapat menghasilkan semburan gas hasil pembakaran yang lurus dan cukup stabil dengan thrust rata-rata sebesar 610 kgf dan maksimum 670 kgf. Rendahnya thrust disebabkan oleh konfigurasi injektor yang masih belum optimal dan kecepatan suplai gas pendorong yang tidak cukup untuk membuat dorongan maksimum.
PERANCANGAN IGNITER UNTUK MOTOR ROKET PADAT RX 420/4000 Rohili, Sukandi Nasir
Indonesian Journal of Aerospace Vol. 4 No. 2 (2006): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Igniter is a rocket component with the function of providing activated energy to the surface of solid propellant in the burning chamber of the rocket motor. Igniter design needs overall data of the rocket especially initial free volume and stable combustion pressure of the propellant. The properties of either primer or main charge especially its density and fraction of condensed particles of it combustion products are also needed. This paper presents the design of igniter for RX-420/4000 solid rocket with wagon wheel-cylinder dual configuration. The design result gives data as follows main case length = 302.6 mm, diameter = 52 mm; main charge weight of 338.31 g; volume = 212.19 cc and nozzle throat area = 12.6 mm; the intermediate case of 200 mm length; 30 mm diameter with black powder weight = 310.87 g and volume of 141.37 cc, the overall length of igniter included stick of 402.6 mm.
MULTI FREKUENSI ENCODER FLIGHT TERMINATION SYSTEM (MULTI FREQUNECY ENCODER FLIGHT TERMINATION SYSTEM) Arisandi , Effendi Dodi
Indonesian Journal of Aerospace Vol. 13 No. 1 Juni (2015): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Flight Termination System (FTS) adalah suatu sistem yang digunakan untuk menghentikan suatu misi peluncuran wahana udara apabila wahana tersebut mengalami kegagalan dalam misinya. Encoder FTS adalah bagian dari FTS yang akan memberikan sinyal perintah dalam bentuk gelombang sinus dengan frekuensi tertentu. Sinyal sinus yang secara umum disebut sinyal tone ranging dapat dibangkitkan dalam rentang frekuensi audio, 20Hz-20KHz. Metode Direct Digital Synthesis (DDS) dapat digunakan untuk membangkitkan sinyal tone ranging yang berupa sinyal sinus atau kotak (pulse). Kerahasiaan sinyal tone ranging yang dikirimkan pada bagian penerima FTS sangat penting agar tidak bisa diganggu oleh sinyal lain. Dengan menggunakan metode DDS AD9850, dapat dihasilkan sinyal sinus multi frekuensi pada endcoder FTS; 750Hz, 1000Hz, dan 1250Hz.
DESAIN DAN PENGUJIAN STRUKTUR SATELIT MIKRO LAPAN-TUBSAT Triharjanto, Robertus Heru
Indonesian Journal of Aerospace Vol. 4 No. 2 (2006): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

The paper discuss about the design and test of the structure of LAPAN-TUBSAT micro-satellite, which is the task done by the writer during his time as the member of LAPAN-TUBSAT integration and test. The discussion includes the design requirment for the structure as mechanical interface and its implementation as well as its design validataion process via test as accordance to the requirement set by the launcher authority.
SIMULASI PENGUJIAN PRESTASI SUDU TURBIN ANGIN Atmadi, Sulistyo; Fitroh, Ahmad Jamaludin
Indonesian Journal of Aerospace Vol. 4 No. 2 (2006): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Identification of whether aerodynamic performances of a rotor blades has met the criteria according to its design or not, the general procedure is to fabricate and perform a field testing; or testing its model in a windtunnel. Both method require high cost however; therefore, a simulation method using Fluent software had used for obtaining lower cost. The model used in an LS (1)-0417 Mod airfoil having 3 blades and rotor diameter 7.21 m. Simulation test shows a good result with a difference of 4.61 percent for torque and power from design result.
RANCANG BANGUN GENERATOR TURBIN ANGIN TIPE AKSIAL KAPASITAS 200 W Nurtjahjomulyo, Agus
Indonesian Journal of Aerospace Vol. 4 No. 2 (2006): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Generator is the component of wind turbine that convert mechanical to electrical energy and has a specific character which operates at low speed rotation ( 1000 rpm). Engineering design of wind turbine generator capacity 200 W discussed in this paper represents the results of fabrication and testing of the generator as a model. The experiment showed that the generator can be producing power 200 W at rotation 450 rpm with torque about 8.5 Nm.
RANCANG BANGUN SISTEM PENAHAN PANAS PADA MOTOR ROKET CIGARETTE BURNING Sutrisno
Indonesian Journal of Aerospace Vol. 4 No. 1 (2006): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

The thrust of cigarette burning rocket motor is relatively lower but the is burning time is too long than that of the radial burning. The cigarette burning rocket motor structure easy to be fail due to the thermal stress thermal effect. Hence the thermal insulation sistem becomes very important. This paper discuss about the design and preparation of thermal insulation system in the cigarette burning rocket motor. The carbon and polyester fiber were used as the thermal protector materials in burning chamber. The liner matrix and inhibitor in the cap side were made from epoxy. O-ring spacer was applied to avoid the gas leakage from the combustion chamber. The performance of thermal insulation system was tested through static test of rocket motor. The result of the test provide that thermal insulation system showed the good performance. It is found that the burning time of the rocket motor is 116 second and the maximum temperature of the outer surface of the tube is 139 degree celcius.
EFEK DEFLEKSI PADA SUDU TURBIN ANGIN TERHADAP KELUARAN DAYA Atmadi, Sulistyo; Fitroh, Ahmad Jamaludin
Indonesian Journal of Aerospace Vol. 4 No. 1 (2006): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

The type of material used in the fabrication of wind turbine blade is a very important factor so that it will not exceed the allowable maximum deflection. An analysis is conducted to study this deflection effect to that power output and as case study, a 7.6 m blade of 10 kW LPN 10000 E turbine is used. Several assumption as such as deflection due to wind speed at perpendicular to local plane local blade are diameter blade and direction of aerodynamic at aerofoil plane local blade are considered. The distribution of blade deflection along the twisted span is assumed uniform. Calculation is performed for the polynomial order of 2,3 and 4, with variety of deflection of 0.2 m, 0.5m, 1 m and 1.5 m. for design wind speed of 9 m per s it was found that for 0.5 deflection, the losses of 6 percent, 9 percent and 12 percent for blade shape polynomial order 2,3 and 4 consequentively are produced; whereas for 1.5 m deflection, losses are 46 percent, 53 percent, and 56 percent for the same polynomial shape. If a maximum loss of 10 percent is taken, then the max allowable deflection is 0.5 m.
SISTEM WIND-DIESEL UNTUK PEMBANGKIT LISTRIK DI LOKASI DENGAN KECEPATAN ANGIN MENENGAH DI INDONESIA Pakpahan, Sahat
Indonesian Journal of Aerospace Vol. 4 No. 1 (2006): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Windspeed is used as a reference in utilization of windturbine as a generating system and will be the main variable for calculation of the energy produced at a certain location. Windspeeds are classified in small scale, medium and large scales. Applications of small scales are generally in the stand-alone mode, while the large systems are intended for interconnection into the utility grid. In between, there are medium scale applications with the annual average windspeed of 4.0 m/s - 50 m/s. Examples of applications are hybrid of windturbine with local diesel generating sets, known as wind-diesel system using one or more windturbines of the size of 10 kW-100 kW and to be matched with the capacity of the existing deisel. most applications are in the intermittent mode of operation in order to obtain higher fuel saving which is used to operate the diesel. Some configurations, selection of components, modelling and calculations are presented to identify more detailed behaviour of the system.
PENGEMBANGAN MODEM AFSK UNTUK TELEMETRI MUATAN ROKET UHF Widada, Wahyu
Indonesian Journal of Aerospace Vol. 4 No. 1 (2006): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Modem is an important component in the telemetry data system of the rocket. The telemetry data based on amateur radio is usually used an AFSK modem. This paper describes the development of AFSK modem using a microcontroller which the speed can be set to the maximum bandwidth of the radio. The prototype is use a 16 MHz of microcontoller and the speed can be set to 2.4 kbps that available to the standard bandwidth of an amateur radio.

Page 26 of 37 | Total Record : 365

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