Simulasi Graphical User Interface Analisis Termodinamika Mesin Turboprop Menggunakan Perangkat Lunak Matlab R2020a

A turboprop engine is a hybrid engine that delivers thrust or jet thrust and also drives the propeller. This is basically similar to a turbojet except the turbine works through the main shaft which is connected to the reduction gear to rotate the propeller in front of the engine. This research was conducted to determine the development of engine performance in thermodynamic analysis so as to know the value of each parameter on a engine that has been developing for 20 to 50 years with different engine manufacturing. So that in this study a comparison of the thermodynamic analysis of the TPE-331, PT6A-42 and H85-200 engines was carried out. In the TPE331-10, PT6A-42, and H85-200 turboprop engines the value of fuel to air ratio and shaft work increases with increasing altitude while compressor work, fuel flow rate, shaft power, propeller thrust, jet thrust, total thrust, equivalent engine power and ESFC decrease with increasing altitude. Furthermore, the turbine's working value is relatively stable as the altitude increases. After that, the value of compressor work and turbine work on the PT6A-42 engine was greater than that of the TPE331-10, and H85-200 engines. However, the value of the fuel to air ratio, fuel flow rate, shaft power, jet thrust, equivalent engine power and ESFC on the H85-200 engine was greater than the TPE331-10 and PT6A engines. Furthermore, at sea level, the value of the axle, propeller thrust, and total thrust on the H85-200 engine is greater than that of the TPE331-10 and PT6A-42 engines but at an altitude of 25,000 ft, the PT6A-4 engine has a greater value than that of the TPE331-10 and PT6A-42 engines. TPE331-10, and H85-200 engines.

Analisis Pengaruh High Pressure Compressor Rotor Clearance Terhadap Exhaus Gas Temperature Margin pada CFM56-7

Exhaust Gas Temperatue is an parameter where the hot gases’s temperature leave the gas turbine. Exhaust gas temperature margin is the difference between highest temperature at take off phase with redline on indicator (???????????? ???????????????????????? °????=???????????? ????????????????????????????−???????????? ???????????????? ????????????). EGTM is one of any factor to determine engine performance. A good perfomance of an engine when it has a big margin (EGTM), during operation of an engine the EGTM could decrease untill 0 (zero). So many factors could affect EGTM deteroration there are: distress hardware such as airfoil erosion, leak of an airseals, and increase of clearance between tip balde and shroud. Increase of clearance happens in high pressure compressor rotor clearance. In CFM56-7 have 9 stage(s) of high pressure compressor and each stage give the EGT Loses. The calculation of EGT Effect/Losses is actual celarance – minimum clearance x 1000 x EGT Effect °C, where actual clearance define by the substraction of outside diameter’s rotor with inside diameter’s shroud, minimum clearance define in the manual, 1000 is adjustment from mils/microinch to inch, and EGT Effect is temperature that define in the manual. The analysist had done with 6 (six) engine serial number and proceed by corelation that shown linkage between clearance and EGT Effect, the corelation is strong shown the result of corelation (r) is 0.994275999 or nearest 1.

Modal Analysis Of Blended Wing-Body UAV

The modal analysis deals with the dynamic behavior of mechanical structures under the dynamic vibration. This study aims to analyze the vibration characteristic of the blended wing-body Unmanned Aerial Vehicle (UAV) using modal analysis. The numerical method is used to calculate the eigen frequencies of the system. The COMSOL Multiphysics is selected as the Finite Element Method (FEM) software to simulate the study. The resulted eigen frequencies are 278.05 Hz, 721.28 Hz, 816.39 Hz, 1601.7 Hz, 1699.5 Hz, and 1855.5 Hz. The study also evaluates the displacement of the leading edge of the wing in all axes to understand the modal shapes. The modal shapes found are updrift, swift back, flapping vertical, flapping horizontal, flapping opposite horizontal and flapping more wave in horizontal movement. The comparison of resulted eigen frequencies with a conventional aircraft wing is conducted to understand the difference in its vibration characteristics.

Simulasi Pendistribusian Spare Part Oxygen Crew Pesawat Airbus Milik Maskapai X Di Bandara Pattimura Ambon

Berdasarkan observasi lapangan, ditemukan adanya indikasi kebocoran oxygen crew pada saat pesawat terbang dari Bandara Soekarno Hatta menuju Bandara Pattimura Ambon. Sesuai dengan FCOM (Flight Crew Operating Manual) untuk pesawat airbus jika ada 2 crew dalam cockpit maka minimum tekanan oksigen darurat untuk flight crew adalah 540 PSI. Sehubungan dengan itu, maka diperlukan analisis pengaruh distribusi spare part oxygen crew pesawat airbus milik maskapai X di Bandara Patimura, dengan tujuan untuk mengetahui pendistribusian komponen pada setiap station yang saling berhubungan, mengetahui pengaruh ketersediaan spare part oxygen crew bagi pesawat yang akan beroperasi, dan mengetahui lokasi penyimpanan dan kebutuhan spare part. Penelitian ini menggunakan metode riset operasi yang terdiri dari metode VAM (Vogel Approximation Methode), metode inspeksi (Least Cost) dan metode NWC (North West Corner). Setelah dilakukan perhitungan menggunakan 3 metode tersebut, diperoleh metode yang tepat untuk proses pendistribusian spare part oxygen crew adalah metode VAM (Vogel Approximation Methode) dengan biaya US$ 141 untuk memenuhi seluruh kebutuhan station.

Analisis Radiografi Sinar-X Terhadap Sambungan Pelat Baja Tahan Karat Aisi 304 Hasil Pengelasan Tungsten Inert Gas Dengan Arus 40–60 Ampere

X-Ray Radiographic Analysis of Aisi 304 Stainless Steel Plate Joints From Inert Gas Tungsten Welding Results with 40 – 60 Ampere Current. Metal welding process is one of the main processes in machine construction. The quality of welded joints determines the strength and toughness of a machine construction. The quality of welded joints of installed construction can be determined by the non-destructive test method using X-ray radiography equipment. This study aims to obtain a butt joint obtained from TIG welding of AISI 304 stainless steel plate with a current of 40 - 60 A, identification of defects in the 1G butt joint, and analysis of the quality of the weld joint. The research method used is testing of welded joints using X-ray radiography which refers to the ASME V article II standard and the connection quality refers to ASME section IX. The results showed that TIG welding with a current of 60 Ampere produced a butt joint butt joint that was penetrated and there was no gap between the plates, whereas with a current of 40 A and 50 A the weld joint was not see-through but there was still a gap between the plates. Incomplete penetration weld defects were found in the welded SS 304 plate joints with a current of 40 A. Welded porosity defects were found in the welded SS 304 plate joints with a current of 50 A. Weld defects were not found in the SS 304 plate joints with a current of 60 A. Butt joint connections TIG welded SS 304 plate with the best current of 60 A compared to the current of 40 A and 50 A.

Sistem Propulsi Roket Padat Untuk Rudal Anti Tank

Abstrak-Indonesia membutuhkan ketersediaan alat peralatan pertahanan dan keamanan (Alpalhankam). Namun hal ini belum didukung oleh kemampuan industri pertahanan secara optimal, sehingga menyebabkan ketergantungan terhadap produk Alpalhankam dari luar negeri. Dengan demikian perlu adanya upaya untuk dapat menguasai teknologi, sehingga kebutuhan terhadap Alpalhankam dapat terpenuhi oleh industri dalam negeri. Indonesia menggunakan Taktik gerilya yang dalam Implementasinya menggunakan senjata-senjata yang dapat menghancurkan Alat utama Sistem Persenjataan (Alutsista) musuh yang masuk ke Indonesia seperti Tank Musuh. Maka berkaitan dengan hal tersebut diperlukan suatu senjata ringan dan senjata Penghancur Tank. Anti Tank Guided Missile (ATGM) memiliki kemampuan untuk menghancurkan Tank tempur utama yang kuat dari jarak yang sangat jauh. Secara umum kinerja rudal sebagian besar bergantung pada sistem propulsi nya. Sistem propulsi roket padat pada rudal digunakan terutama pada saat memerlukan percepatan yang besar, misalnya meningkatkan kecepatan tinggi dalam waktu singkat sehingga cocok diterapkan pada rudal Anti Tank. Selain itu motor roket padat juga memiliki tingkat keselamatan, keandalan, kesederhanaan desain, serta masa penyimpanan yang baik, sehingga sering digunakan dalam aplikasi militer. Kata kunci: Alpalhankam, Alutsista, Rudal, Propulsi, Roket Padat,

Analisis Penentuan Komposisi Optimum Kargo Dan Pax Pesawat Boeing 787 - 8 Dan Airbus 330 – 900 Pada Rute Jakarta – Dubai Menggunakan Optimasi Linear Programming

- The need for airplanes is increasing every day, this is due to the increasing number of passengers and cargo shipments from one area to another. Therefore, airlines need to provide optimal, safe, and efficient cargo and passenger transportation services so that the delivery of goods and passengers can run according to correct procedures. Opportunities in the business of transporting passengers and shipping cargo must be utilized properly by each airline by purchasing planes so that the shipping process from one area to another can quickly arrive at its destination. The purpose of this paper is to find the optimum value of the two aircraft between the Boeing 787-8 and the Airbus 330-900 in terms of the effect on the range, operational costs and to find out which aircraft is more profitable for operating costs on the Jakarta - Dubai route, using linear optimization. programming. Based on the results of the analysis that the optimum point for the calculation of linear programming optimization, the Boeing 787-8 aircraft obtained results (Max payload 41,075 kg, Fuel 6,657 kg, Max Fuel 101,323 kg) where these three results become a limitation for airlines to know the maximum usage of payload and fuel compared Airbus 330-900 aircraft obtained results at the point (Max payload 45,000 kg, Fuel 4,728 kg, Max Fuel 111,272 kg) so that the optimization results are obtained, for Boeing 787-8 aircraft with a max payload of 41,075 kg, max pax 359, max cargo 15,945 kg , compared to Airbus 330-900 with a max payload of 45,000 kg, max pax 460, max cargo 12,800 kg, so it can be concluded that the results of linear programming optimization and the calculation of the operational costs of the Boeing 787-8 aircraft are more optimal with a figure of Rp. 1,541,334,803.96 but in terms of revenue the Airbus 330-900 is bigger than the Boeing 787-8.

Analisis Numerik Part Spar Pada Sub System Wing To Fuselage Joinner Assembly Pesawat Berkategory Utility Menggunakan Metode Elemen Hingga

Pesawat Utility adalah kategori pesawat udara yang memiliki konfigurasi tempat duduk kurang dari 9 yang tidak termasuk tempat duduk pilot, Maximum Takeoff Weight 12.500 pounds serta memiliki kemampuan pesawat dapat bermanouver layaknya akrobatik yang di batasi pada sudut 60 sampai 90 derajat[2]. Berdasarkan CASR subbagian 23.305, struktur harus sanggup menahan beban limit tanpa merugikan dan membuat kerusakan permanen. Selain itu struktur juga harus mampu menahan beban ultimate tanpa kegagalan paling tidak selama 3 detik, kecuali kegagalan lokal atau ketidakstabilan struktur antara beban limit dengan beban ultimate yang dapat diterima jika struktur mampu menopang beban ultimate paling tidak selama 3 detik[2]. Penelitian ini melakukan analisis numerik part spar untuk pesawat berkategori utility dengan load sebesar 6G menggunakan material komposit. Selain itu dilakukan proses reduksi berat spar berdasarkan variasi jumlah lamina/ply dengan metode ply drop-off laminate. Tujuan Penelitian ini untuk mengetahui keamanan struktur berdasarkan kriteria kegagalan dan mendapatkan berat yang optimal pada spar. Proses penyelesaian masalah menggunakan metode elemen hingga dengan bantuan software CAE. Penelitian dilakukan pada kondisi statik dengan asumsi pembenanan gaya angkat yang terjadi pada spar. Perhitungan gaya angkat dilakukan dengan metode Schrenk. Tegangan tertinggi terdapat pada arah transversal atau arah tegak lurus serat setelah dilakukan optimisasi sebesar 301.7 MPa. Optimisasi menghasilkan pengurangan massa sebesar 30.41% dari sebelum optimisasi. Berat spar yang optimal sebesar 47.82 kg. Hasil kriteria kegagalan Tsai-Hill menghasilkan struktur spar tersebut aman untuk digunakan.

Analisis Masalah Pengaturan Ruang Udara Di Atas Alur Laut Kepulauan Indonesia (ALKI)

United Nations Convention on the Law of the Sea 1982 (UNCLOS) was formed at 10 December 1982. Archipelagic State (Article 46) means a state constituted wholly by one or more archipelagos and may include other islands. Article 53, paragraph (2) UNCLOS 1982, stated: “all ships and aircraft enjoy the right of archipelagic sea lines passage in such sea lines and air routes”. However, this article could cause overlapping in applications, because ICAO already states all air areas in flight routes (ATS). In another article, the right of archipelagic sea lines passage, especially for military aircraft regarding the necessity to get permission from Archipelagic State, has been perceived differently by every states. This research with the grounded theory methode, involves expert respondents to see and synchronize few aspects or articles. Findings from this research are to complete the sentence of “all ships and aircraft enjoy the right of archipelagic sea lines passage .... “, with the understanding that all aircraft can provide overflight on archipelagic sea lines air area, which determined as an ATS route according to ICAO rules. Every military aircraft which uses the ATS route should have permission from Archipelagic State Goverment.

Analisis Numerik Part Bulkhead Pada Sub System Wing To Fuselage Joinner Assembly Pesawat Aerobatik Menggunakan Metode Elemen Hingga

Analisis rancangan bulkhead dilakukan untuk memperoleh geometri terbaik untuk mencari berat yang efisien dengan mengubah geometri bentuk pada bulkhead yang merupakan sub system wing to fuselage untuk pesawat berkategori aerobatik dan berat yang optimal yang memenuhi persyaratan regulasi FAR 23 dan mengetahui respon distribusi tegangan, bending yang dihasilkan dan kriteria kegagalan struktur berdasarkan variasi geometri bentuk bulkhead. Pada penelitian ini untuk analisis statik bulkhead untuk pesawat berkategori aerobatik menggunakan material Aluminium Alloy 7075-T6 dan menggunakan metode pendekatan Schrenk untuk menghitung beban eksternal distrbusi gaya angkat pada sayap. Selain itu dilakukan proses optimisasi berat bulkhead berdasarkan metode pendekatan topologi yaitu perubahan geometri bentuk pada bulkhead untuk mereduksi berat, sudut insiden spar yang berbeda dan menghitung magin of safety. Proses penyelesaian masalah menggunakan perangkat lunak metode elemen hingga (Abaqus CAE). Optimisasi topologi pada part bulkhead sudut insidet 0° dan 4° menghasilkan volume yang berkurang pada benda sehingga mereduksi berat, tetapi nilai dari margin of safety MS = 0. The bulkhead design analysis was carried out to obtain the best geometry to find an efficient weight by changing the shape geometry of the bulkhead which is a sub-system of the wing to the fuselage for an aircraft categorized as aerobatics and an optimal weight that meets the requirements of FAR 23 regulations and sees the stress distribution response, the resulting bending and structural failure criteria based on the geometric variation of bulkhead shapes. In this study, to analyze the bulkhead static for an aerobatic category aircraft using Aluminum Alloy 7075-T6 material and using the Schrenk Approximation method to calculate the external distribution load of lift force on the wing. In addition, the optimization of bulkhead weight based on the topological approach method is to change the shape geometry of the bulkhead to reduce weight, in different spar incidents and calculate margin of safety. The problem solving process uses finite element method software (Abaqus CAE). Topological optimization of the bulkhead part with an incidence angle of 0 ° and 4 ° results in a reduced volume of the object so that it reduces weight, but the value of the margin of safety MS = 0.