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"ABSTRACTPerforma terbang untuk objek yang memiliki kemampuan terbang mesti memenuhi beberapa parameter pengujiannya, yang bergantung pada bentuk dan konfigurasi yang memengaruhi karakteristik aerodinamisnya. Penelitian ini berfokus pada sebuah desain konsep kendaraan terbang baru, yang mampu mengangkut dua penumpang dengan berbagai bawaan dan bahan bakarnya, terbang pada kecepatan 300km/h pada ketinggian 7000m sejauh 750 km, dengan kemampuan bermanuver yang sesuai dengan kelasnya baik dalam level turn, jarak takeoff, dan landing. Hal tersebut memerlukan analisis performa untuk mengidentifikasi kemampuan terbang desain, yang dinilai dari performa aerodinamis, performa terbang steady flight, dan performa terban accelerated flight. Penelitian dimulai dengan mencari benchmark dan parameter desain awal, dan menggunakan data aerodinamis dari hasil pengujian model CAD menggunakan CFD pada software ANSYS Fluent. Tujuan umum dari penelitian ini untuk memeroleh nilai dari berbagai parameter aerodinamis penting koefisen lift maksimum, lift-to-drag ratio, dll dari kendaraan terbang untuk memenuhi target desainnya cruising speed, maximum altitude, range, maximum take-off load, dan runway length . Analisis performa pada desain juga akan mengungkap thrust required dan power required sebagai bahan pertimbangan mesin yang cocok untuk dipakai, dan masukan desain untuk pengembangan lebih lanjut untuk iteras konsep selanjutnya.

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ABSTRACTFlight performance for anything that has flight capabilities have a number of parameters to measure its capabilities, depending on its shape and configuration that determined its aerodynamic characteristics. This study focuses on a new conceptual design for a flying vehicle, which capable to carry 2 passengers, with payload and fuel, that capable to cruise at 300km h at 7000m altitude for 750km, with acceptable for its class manueverability in turn radius, takeoff, and landing distance. Thus, required a performance analysis to identify its capabilities, judging by aerodynamic performance, steady flight performance, and accelerated flight performance. This study will begin with determining the benchmarks and initial design goals, which using aerodynamic data from CFD testing result of the CAD models by using ANSYS Fluent software. This set as goal for this research is to obtain the value of the important parameters max lift coefficient, lift to drag ratio, wing loading, and thrust to weight ratio from flying vehicle design to meet its various design performance goals cruising speed, maximum altitude, range, maximum take off load, and runway length . The performance of the design will also reveal the thrust and power required to determine which engine suited best, and further improvement for the next iteration of the design."

"ABSTRAKSebagai negara kepulauan yang seharusnya dapat memanfaatkan potensi kemaritiman, sudah seharusnya Indonesia melakukan utilisasi pemanfaatan potensi dari aspek transportasi logistik, dalam konteks penelitian ini adalah Pelabuhan. Persebaran pelabuhan di indonesia belum merata jika dilihat dari Pendapatan Domestik Regional Bruto PDRB , dalam kasus ini adalah Kota Dumai yang memiliki pelabuhan yang terletak di alur laut kepulauan Indonesia ALKI 1, walaupun terletak dalam lokasi yang strategis, hal itu tidak tercermin dari PDRB kota Dumai yang bisa dikategorikan tertinggal dibanding kota-kota Pelabuhan lain di Indonesia. Untuk melakukan optimasi pemanfaatan pelabuhan yang ada dan meningkatkan pertumbuhan ekonomi di Kota Dumai, PT. Pelindo 1 perwilayahan Dumai berencana untuk melakukan pengembangan kapasitas pelabuhan dengan membangun segmen khusus kegiatan bongkar muat peti kemas yang didasari oleh semakin meningkatnya intensitas kapal bermuatan peti kemas yang berlabuh di Pelabuhan Dumai. Untuk menanggapi fenomena yang terjadi, maka penelitian ini bermaksud untuk melakukan analisis desain konseptual pengembangan pelabuhan berbasis Seatropolis dengan mempertimbangkan biaya operasional dan pemeliharaan serta proyeksi pendapatan menggunakan sistem dinamik. Berdasarkan hasil analisis yang dilakukan dalam penelitian ini, telah didapatkan estimasi biaya operasional dan pemeliharaan desain konseptual kawasan Seatropolis yaitu sebesar Rp 898.799.348.398,27 dan untuk proyeksi pendapatan sebesar Rp 21.298.015.775.555 pada tahun yang sama yaitu tahun 2027.

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ABSTRAK For an archipelago country that can exploit the maritime potential, Indonesia should be utilizing the potential of logistics transportation aspect, in this research context is Port. The distribution of ports in Indonesia is not evenly distributed if seen from Gross Regional Domestic Product PDRB , in this case is Dumai City which has a port in the Indonesian archipelagic sea lane ALKI 1, although it is in strategic location, it is not reflected from Dumai city PDRB that can be categorized as lagging compared to other Port cities in Indonesia. To optimize the utilization of existing ports and increase economic growth in Dumai City, PT. Pelindo 1 of Dumai territory plans to develop port capacity by building a special segment of container loading and unloading activities based on the increasingly cheap vessels of containers docked at Dumai Port. To add to the phenomenon that occurs, the research is intended to design the conceptual design of port development. By using dynamic system. Based on the results of analysis conducted in this study, has obtained estimation of operational cost and arrangement of conceptual design of Chair area amounting to Rp 898.799.348.398,27 and for profit and loss projection Rp 21.298.015.775.555 in the same year that is year 2027."

"Perkembangan penelitian untuk pesawat tanpa awak mulai banyak dilakukan. Penggunaan pesawat tanpa awak sangat beragam seperti contohnya dari sekedar hobi bermain menerbangkan pesawat tanpa awak dengan menggunakan remote control hingga penggunaan pesawat tanpa awak untuk keperluan fotografi udara. Manfaat atau penggunaan dari pesawat tanpa awak bisa disebut sebagai sebuah misi. Misi dari suatu pesawat menjadi acuan awal untuk melakukan proses perancangan atau desain. Dari misi pesawat tersebut didapatkan sejumlah persyaratan tertentu yang harus bisa dipenuhi oleh desain pesawat itu sendiri.Pada tahap desain konseptual pesawat akan diawali dengan penentuan sejumlah persyaratan yang akan menjadi titik acuan dalam proses tahapan perancangan. Kemudian setelah persyaratan misi pesawat telah ditentukan maka proses selanjutnya adalah penentuan berat pesawat. Dari penentuan berat pesawat ini maka akan didapatkan data awal untuk menentukan luas sayap yang berfungsi untuk dapat menghasilkan gaya angkat. Kemudian akan diperhitungkan juga berapa besar tenaga yang dibutuhkan unutk dapat mendorong pesawat tersebut. Ukuran badan pesawat akan diperhitungkan dengan memperkirakan kebutuhan muatan yang akan dibawa didalam badan pesawat. Dimensi ekor pesawat akan ditentukan dengan memperkirakan besarnya momen yang terjadi untuk mengembalikan sikap pesawat pada posisi semula. Hasil akhir dari desain konseptual adalah sebuah tampilan konsep pesawat dalam tiga tampilan gambar. Dari hasil konsep desain pesawat tanpa awak tersebut selanjutnya akan dilakukan analisis awal yang meliputi pengujian model dalam perangkat lunak XFLR5 dan pengujian model dalam terowongan angin subsonik. Dari hasil pengujian adalah pemenuhan terhadap persyaratan prestasi terbang yang pada fase jarak take off, rate of climb,jarak landing dan jarak tempuh terbang sudah dapat memenuhi persyaratan misi yang telah ditentukan namun untuk prestasi terbang kecepatan stall belum dapat terpenuhi.

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Research developments for unmanned aircraft have been made. The use of unmanned aircraft is very diverse as for example from a hobby of flying unmanned aircraft by using the remote control until the use of unmanned aircraft for the purposes of aerial photography. The benefits or use of an unmanned aircraft may be referred to as a mission. The mission of a plane becomes the initial reference for the design or design process. From the mission of the aircraft is obtained a number of certain requirements that must be met by the design of the aircraft itself. In the conceptual design stage the aircraft will begin with the determination of a number of requirements that will be the reference point in the design stage process. Then after the aircraft mission requirements have been determined then the next process is the determination of the aircraft weight. From the determination of this aircraft weight will be obtained preliminary data to determine the area of the wing that serves to produce lift. Then will also be taken into account how much energy needed to be able to push the plane. The size of the fuselage will be calculated by estimating the need for the load to be carried inside the fuselage. The tail dimension of the aircraft will be determined by estimating the magnitude of the moment to restore the aircraft 39 s original position. The final result of the conceptual design is a concept airplane display in three display images. From the results of the draft concept of unmanned aircraft will then be conducted preliminary analysis which includes model testing in XFLR5 software and model testing in subsonic wind tunnel. From the test results is the fulfillment of the requirements of the achievement of the fly in the phase of the distance take off, rate of climb, landing distance and range of flying can meet the requirements of the mission that has been determined but for the achievement of flying stall speed can not be achieved.Keywords conceptual design unmanned aircraft wind tunnel."

"As a consequence of an improvement in productivity, due to shorter travel time and further development in connectivity, a High Speed Train (HST) project is one kind of infrastructure which has a potential for positive impact on economic development and growth. However, HST project feasibility rarely meets related stakeholders’ expectations, since the benefits and added value are considered low, when compared to the value of investment. Therefore, a comprehensive study is required by producing innovative ideas to improve the feasibility of HST projects, from the viewpoint of both technical and economic aspects. This study is aimed at improving the feasibility of project investment for the conceptual design of Jakarta-Surabaya HST project by using Value Engineering (VE). The methodology uses both qualitative and quantitative approaches through in-depth interviews and life cycle cost analysis. Route 1 selected as the best scenario that has 4 stations connecting Jakarta to Cirebon to Semarang, and to Surabaya. The HST project requires a budget of 36 Trillion IDR with operational and maintenance costs estimated for about 1.2 Billion IDR per year for 685 km of high speed train infrastructure."

"This book introduces a stability and control methodology named AeroMech, capable of sizing the primary control effectors of fixed wing subsonic to hypersonic designs of conventional and unconventional configuration layout. Control power demands are harmonized with static-, dynamic-, and maneuver stability requirements, while taking the six-degree-of-freedom trim state into account. The stability and control analysis solves the static- and dynamic equations of motion combined with non-linear vortex lattice aerodynamics for analysis. The true complexity of addressing subsonic to hypersonic vehicle stability and control during the conceptual design phase is hidden in the objective to develop a generic (vehicle configuration independent) methodology concept. The inclusion of geometrically asymmetric aircraft layouts, in addition to the reasonably well-known symmetric aircraft types, contributes significantly to the overall technical complexity and level of abstraction. The first three chapters describe the preparatory work invested along with the research strategy devised, thereby placing strong emphasis on systematic and thorough knowledge utilization. The engineering-scientific method itself is derived throughout the second half of the book. This book offers a unique aerospace vehicle configuration independent (generic) methodology and mathematical algorithm. The approach satisfies the initial technical quest: How to develop a ‘configuration stability & control’ methodology module for an advanced multi-disciplinary aerospace vehicle design synthesis environment that permits consistent aerospace vehicle design evaluations?"