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All Journal Bulletin of Electrical Engineering and Informatics Jurnal Aplikasi Bisnis dan Manajemen (JABM) E-Journal Jurnal RESTI (Rekayasa Sistem dan Teknologi Informasi) SINERGI: Jurnal Ilmiah Ilmu Manajemen Jurnal Pertahanan : Media Informasi tentang Kajian dan Strategi Pertahanan yang Mengedepankan Identity, Nasionalism dan Integrity JURNAL EDUCATION AND DEVELOPMENT NUSANTARA : Jurnal Ilmu Pengetahuan Sosial Jurnal Riset Informatika Jurnal Teknologi Dirgantara INSIST (International Series on Interdisciplinary Research) Journal of Robotics and Control (JRC) ASEAN Journal of Community Engagement Budapest International Research and Critics Institute-Journal (BIRCI-Journal): Humanities and Social Sciences Journal of Strategic and Global Studies Jurnal Multidisiplin Madani (MUDIMA) Journal Research of Social Science, Economics, and Management Indonesian Journal of Community Services
Bura, Romie O.
Universitas Pertahanan Republik Indonesia
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Journal : Jurnal Teknologi Dirgantara

 1 
PERANCANGAN DAN ANALISIS INTEGRASI HYPERSONIC WAVERIDER–INLET SCRAMJET (DESIGN AND ANALYSIS OF HYPERSONIC WAVERIDER– SCRAMJET INLET INTEGRATION) Deden Ridwan Malik; Romie Oktovianus Bura
Jurnal Teknologi Dirgantara Vol. 12 No. 1 Juni 2014
Publisher : National Institute of Aeronautics and Space - LAPAN

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Hingga saat ini, sudah banyak desain wahana hipersonik yang telah hadir dan waverider adalah salah satunya. Waverider telah diperkenalkan lebih dari 50 tahun namun hanya beberapa wahana yang pernah diterbangkan. Ini disebabkan oleh beberapa kesulitan dalam proses perancangan dan integrasi sistem propulsi. Penelitian ini dilakukan dengan mendesain general wedge-derived waverider dan diintegrasikan dengan inlet scramjet. Proses desain waverider ini berdasarkan pada analisis aliran satu dimensi, sementara integrasi inlet scramjet berdasarkan pada analisis exergy. Melalui investigasi ini, suatu variabel desain – laju penghancuran exergy (EDR) – dapat diperoleh untuk mengkorelasikan desain waverider dengan integrasi inlet scramjetKata kunci: General wedge-derived waverider, Inlet scramjet, Laju penghancuran exergy, Perancangan dan integrasi
DESAIN DAN PENGUJIAN INTAKE KONIKAL SISTEM PROPULSI RAMJET PADA KECEPATAN SUPERSONIK (DESIGN AND TEST OF CONICAL INTAKE OF RAMJET PROPULSION SYSTEM AT SUPERSONIC SPEED) - Sofyan; Romie Oktovianus Bura
Jurnal Teknologi Dirgantara Vol.13 No. 1 Juni 2015
Publisher : National Institute of Aeronautics and Space - LAPAN

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Riset ini bertujuan untuk mendesain intake supersonik untuk aplikasi sistem propulsi ramjet. Desain intake ramjet sangat penting bagi proses pembakaran dalam ruang bakar mesin ramjet. Dalam desain intake konikal ini, kondisi Mach 2 dijadikan sebagai acuan, dengan kompresi eksternal. Penelitian ini juga menguji intake ramjet dalam terowongan angin supersonik. Desain dilakukan dengan menempatkan gelombang kejut pada bibir cowl intake untuk memperoleh pressure recovery yang tinggi dan gaya hambat serendah mungkin. Hasil desain analitik dibandingkan dengan hasil numerik pada berbagai kondisi intake – subkritikal, kritikal, dan superkritikal. Hasil numerik juga divalidasi dengan eksperimen model. Intake yang didesain memberi pressure recovery sebesar 0,93, namun hasil ini cukup berbeda dengan hasil eksperimental. Ini disebabkan karena efisiensi kompresi tidak diikutkan dalam proses desain.Kata kunci: Intake supersonik, Ramjet, Pressure recovery, Rasio laju massa
DESAIN NOSEL ROKET CAIR RCX250 MENGGUNAKAN METODE PARABOLIK DENGAN MODIFIKASI SUDUT EKSPANSI Eko Priamadi; Arif Nur Hakim; Romie O. Bura
Jurnal Teknologi Dirgantara Vol 9, No. 1 Juni (2011)
Publisher : National Institute of Aeronautics and Space - LAPAN

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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. Key words:Liquid rocket, Parabolic nozzle, Thrust, CFD
Co-Authors - Sofyan A. Octavian Agus Bayu Utama Amarulla Octavian Amperiawan, Gita Andi Fathurrachman Batara Sulo Andiarti, Rika Arif Nur Hakim Artono, Endro Aziz Ikhsan Bachtiar Boshra Algandouz Dadang Gunawan Deden Ridwan Malik Dwicahyono, Taufik Eko Priamadi Eko Putro, Idris Emhamed Boras Faisa Lailiyul Mutho' Affifah Faishal Irfan Farraz, Muhammad Gamantyo Hendrantoro Hakim, Arif Nur Hanif, Azizul Haryanto A.R, Timbul Henry Setyanto Heri Yansyah Herma Yudhi Irwanto Irdam Ahmad Irvan Arianto Randa Lembang Irwanto, Herma Yudhi Jamal Elbakay Elbakay Larasmoyo Nugroho Lilis Mariani, Lilis Luhut Simbolon Luky Adrianto Lutfi Adin Affandi Marimin , Martharaharja, Januar Arief Maspin Apit Mirad Fahri Muhammad Adnan Utomo Muhammad Farraz Muhammad Hanifudin Al Fadli Octavian, A. Oka Sudiana Pujo Widodo, Pujo R Djoko Andreas Navalino Raden Andhika Ajiesastra Ratno Nuryadi Riska Nurtantyo Sarbini Salwa Muftah Eljamay Sarjito, Aris Shahed Muftah Shahrazad Eteer Siswo Hadi Sumantri Sovian Aritonang Sudiana, Oka Timbul Haryanto AR Utama, Yudki Utomo, Muhammad Adnan Wisnu Ari Adi Yudki Utama Yusgiantoro, Purnomo Zainal Abidin Sahabuddin, Zainal Abidin