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Samosir, Ganda
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PERANCANGAN SISTEM PROPULSI FFAR DENGAN NOSEL TUNGGAL Samosir, Ganda; Nuryanto, Agus
Indonesian Journal of Aerospace Vol. 7 No. 2 (2009): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Roket FFAR (Folding Fin Aerial Rocket), merupakan roket taktis dengan diameter dan panjang, berturut-turut 70 mm dan 680 mm. Roket ini dapat digunakan, baik dari darat ke darat, udara ke udara, dan bahkan dari udara ke darat. Roket FFAR 2.75”, mempunyai 4 (empat) buah nosel kecil-kecil sejenis (Multi Nosel) yang pemasangannya diatur sedemikian rupa, sehingga satu dengan lainnya membentuk sudut tertentu. Dengan posisi nosel-nosel seperti ini, dapat menghasilkan efek puntir (sebagai mana gerak laju peluru) pada saat terbang, sehingga roket ini mempunyai jangkauan horizontal sekitar 8 km pada sudut elevasi 40º. Roket substitusi FFAR (RX-70) mempunyai 1 (satu) nosel (Nosel Tunggal), berbahan bakar propelan padat jenis komposit, sementara FFAR asli menggunakan tipe double base. Paper ini membahas simulasi perancangan sistem propulsi, pembuatan dan pengujian (statik maupun terbang) roket RX-70 dengan nosel tunggal sebagai pengganti FFAR nosel jamak. Dari hasil uji terbang yang telah dilaksanakan mulai tahun 2004 di Pandanwangi-Jawa Timur dan dilanjutkan di Pameugpeuk-Jawa Barat, diketahui bahwa roket RX-70 mempunyai jangkauan horizontal 7,8 km pada sudut elevasi 40°, terjadi penyimpangan 2,5 % dari rancangan.
PERHITUNGAN DAN PERANCANGAN IGNITER BERBASIS KALKULASI PROPULSI ROKET (Studi Kasus Roket RX-320) Samosir, Ganda
Indonesian Journal of Aerospace Vol. 9 No. 2 Desember (2011): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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The solid rocket motors, like all the LAPAN’s rocket, has been using the composite fuel of Hydroxyl Terminated Poly Butadiene (HTPB) type which is not easy to self-igniting. The quite extreme environment conditions are needed in order to ignite this non-hypergolic solid fuel, such as the ambiance pressure and temperature must be about 40 bar and 280°C respectively. The aforementioned conditions must be well given by the prime igniter designed or commonly known as igniter. The performance of an igniter could be very influenced by 2 (two) massive variables; first one is the internal factor, such as: squib ingredient, filament material, primer composition, igniter main charge, and the second one is external factor, such as: propellant’s type, dimension and the configuration of the rocket’s combustion chamber. In other word, chosen the proper rocket’s igniter are depending on the type and its mission.The propulsion calculation applied in this paper to design the igniter of the rocket RX-320, gives some major variables, i.e.: the biggest tube length; = 357 mm, its outside diameter; = 51 mm, total orifices and its diameter are 165 and 4 mm respectively.
PENERAPAN FEM UNTUK MENENTUKAN MATERIAL KOMPONEN PROPULSI ROKET RKX-10C16 Samosir, Ganda
Indonesian Journal of Aerospace Vol. 8 No. 2 Desember (2010): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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One of the most important rocket propulsion components is nozzle where the thermal energy is converted to kinetics and finally became the mechanics energy in the form of thrust. During the combustion process of the propellant, the nozzle will be influenced by some constraints, namely the pressure and the thermal. The nozzles material chosen, must than be strength enough to minimize those constraints, but still, the nozzle must be weight enough. The Finite Element Method (FEM) used to analyze the nozzles structure strength must be applied to those constraints separately. The result is then compared to the technical specification of the nozzle material chosen. From the static test of the rocket 100 mm clases, it is known that the operating pressure is 46 kg/cm2= 4,51 MPa and 3000ºC of temperature but about 90 % are absorbed by the tube liners (inhibitor). If the calculated safety factor minimum, min F S ≥ 1, the selected material then meets the requirement. Basically, the rocket nozzle consist of two different materials, the outer side is made from the metal (steel), the inner one is from the graphite, but the calculation in this paper was made to the metal part only. After being well analyzed, we arrive then to the conclusion that the metal part of the nozzle is made from the carbon steel S-45C.
EVALUASI UNJUK KERJA SISTEM PROPULSI MOTOR ROKET RX-150-1200 DENGAN MENGGUNAKAN PIRANTI LUNAK PRODUK LAPAN Samosir, Ganda
Indonesian Journal of Aerospace Vol. 5 No. 2 (2007): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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The propulsion calculations of the rocket motor RX-150-1200 was done by using the propulsion simulation software developed bya the researchers of the Propulsion Division-LAPAN. The results were compared to that of motor rocket static test to find out the occurary of the motor rocket propulsion system design. Mostly, if there is a difference between those two results are less than 10 percent, we may concluded that the propulsion rocket motor design is correct or pseudo-correct classified, because the deviation obtained in this paper is 1.05 percent only. Keywords: Propulsion, Rocket motor.
Co-Authors Agus Nuryanto