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Irza Sukmana
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INDONESIA
International Journal of Aviation Science and Engineering
Published by Institut Teknologi Bandung
ISSN : 27215342     EISSN : 27156958     DOI : https://doi.org/10.47355/avia.v1i1.6
Core Subject : Engineering,
Aerospace Engineering Automotive Engineering Electrical & Electronics Engineering Mechanical Engineering Transportation
AVIA : International Journal of Aviation Science and Engineering is published by Faculty of Mechanical and Aerospace Engineering, FTMD Institut Teknologi Bandung, Indonesia - in cooperation with Faculty of Engineering, Universitas Lampung and Java Scientific Academy, Indonesia. International Journal of Aviation Science and Engineering aims to publish original research articles and critical review manuscript in the field of Aviation Science and Engineering as well as Aerospace and applied Mechanical Engineering. The topics are including, but limited to: aviation sciences and technology, aerospace engineering, aeronautics, defense system and engineering, safety and energy, mechanical engineering, aeronautics education and training, interdisciplinary engineering and applied sciences.
Arjuna Subject : Teknik (semua kategori) - Teknik Ruang Angkasa
Articles 5 Documents
 1 
Search results for , issue "Vol 2, No 1: (June, 2020)" : 5 Documents clear
Development of Aircraft Movement Simulation in Airport Airside Area M Sadono; D Y Putra; S A Harahap
AVIA Vol 2, No 1: (June, 2020)
Publisher : Institut Teknologi Bandung

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.47355/avia.v2i1.13

Abstract

Soekarno-Hatta Intl Airport had become busier every and each year passed. Based on Airnav’s data in 2016, there was about 1.200 aircraft movement, included take-off and landing, happened in Soekarno-Hatta Intl Airport in one day. These numerous movements made Soekarno-Hatta Intl Airport became the 12th busiest airport in the world based on Airport Council International (ACI). The long queue of the aircraft at the taxiway is deniable and became one of the problems that needs to be resolved. This research would make aircrafts movement simulation in Soekarno-Hatta Intl Airport’s taxiway(s) using Rockwell Arena Simulation software. The simulation results would be total taxiing time of an aircraft, which intersection(s) that traffic happened, and the total of aircraft(s) that doing taxi in and taxi out. This simulation would help to determine and evaluate the factors that initiated the queue in the taxiway and modify taxiing route to reduce the traffic. The results of this research can be applied by the airport as a reference for scheduling aircraft’s departing or arriving, develop airport airside facility, and to improve taxiing route so the duration of aircraft’s taxiing time can be reduced
A Probabilistic Modeling of the Demand and Supply for Rotable Aircraft Components (Case Study: Brake Assembly of Boeing 737-800) C D W Kuswardani; E Suwondo
AVIA Vol 2, No 1: (June, 2020)
Publisher : Institut Teknologi Bandung

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.47355/avia.v2i1.14

Abstract

Spare parts control is an important factor in every airlines company. The unavailability of the spare parts may affect the airlines operationally, thus a delay and even a cancellation may happen. A common assumption used to calculate spare part requirements is that the demand is stochastic and the supply is constant. But in real operational circumstance, both of those are stochastic. This research develops the spare parts demand and supply model, and the calculation method of service level and safety stock in the bi-variate distribution from a real data of demand and supply of a rotable component. A fit test is conducted to determine the probability density function of the distribution. An analysis is then carried out after implementing the model in a case study. Historical data of brake assembly used in Boeing 737-800 New Generation is used in the case study. The result of this research are a model to determine demand and supply of aircraft spare part components, a method to calculate service level and safety stock for probabilistic model of demand and supply, and the amount of spare parts required for a brake assembly inventory system
On Hypothesis of the Existence of Superfine Fluid that Producing Electromagnetic Field Bintang A.S. W.A.M; E Amalia; D Sardjadi
AVIA Vol 2, No 1: (June, 2020)
Publisher : Institut Teknologi Bandung

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.47355/avia.v2i1.15

Abstract

Based on previous work of reformulation of equation for compressible fluid flow by analogy with Maxwell equation, further effort is successfully done to show similarity between governing equations for continuum, incompressible, non-viscous fluid flow and Maxwell equation for homogeneous medium without electric charge and without magnetic pole. From mathematical analysis of both system of equations, impulse vector in fluid field is equivalent with electric field in electromagnetic field, vorticity in fluid field is equivalent with magnetic fields in electromagnetic field, and speed of sound in fluid field is equivalent with speed of light in electromagnetic field. The success of finding the similarity leads to a hypothesis about the existence of a “superfine fluid” that forming background field in universe that having a characteristic similar with fluid field which is continuum, incompressible and inviscid
Design of Single Stage Axial Turbine for Mini Turbojet Engine I Syarafina; P Adnan; F Hartono
AVIA Vol 2, No 1: (June, 2020)
Publisher : Institut Teknologi Bandung

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.47355/avia.v2i1.16

Abstract

This paper explains about aerodynamic design of a single stage gas generator turbine for a small turbojet engine. The design requirement is that the turbine must be able to deliver power output of 150 kW at 0.814 kg/s gas mass flow, with turbine inlet temperature of 1200 K, and turbine inlet pressure of 267508 Pa. The design phase consists of 4 steps, which is thermodynamic property analysis using parametric cycle analysis, determination of velocity triangle in 2D plane and 2D blade design using CASCADE software, 3D geometry modeling, and 3D flow analysis at design point using Computational Fluid Dynamics method. In parametric cycle analysis, design points are applied to get the unknown thermodynamics property. The determination of velocity triangles, two conditions are applied: zero inlet swirl and constant nozzle angle design. The design continues with the 2D approach in CASCADE to determine the airfoil type at the hub, mean, and the tip of the blade based on the inlet and outlet flow conditions. The 3D approach flow analysis is done by simulating the 3D geometry that has been made using CAD in full configuration to evaluate the overall performance of the turbine, especially the power generated by the turbine. The observed parameters are clearance, stagger angle, and cambered flat plate substitution in NGV affects the turbine’s output power. The analysis results show that all of those parameters above affect the turbine’s output power in a different way from one to each other. The bigger the clearance, the power output and the efficiency that is generated by the turbine also become bigger. Same as clearance, the stagger angle of turbine’s NGV also affects the turbine power and efficiency. The bigger the stagger angle, the bigger the power, but the efficiency drops.
A Study in Aerodynamic Optimization of UAV Helicopter Rotor- Blades Planform in Vertical Motion M F Afthon; M A Moelyadi
AVIA Vol 2, No 1: (June, 2020)
Publisher : Institut Teknologi Bandung

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.47355/avia.v2i1.12

Abstract

According to the objectivity of UAV helicopter, endurance is a valuable performance. To increase the endurance, we need to decrease the helicopter required power. Within the research scope in vertical movement only, 5 parameters of blades planform design were considered as design variables. They are root chord of the blades, taper location, taper ratio, pitch angle, and tip twist angle. Optimization was done using own developed genetic algorithm codes with built-in blade element momentum theory (BEMT) as a performance calculator. It was chosen due to its ability to estimate rotor performance quickly. Several CFD simulation were done to reduce the error of blade element momentum theory calculation. Using constant adjustment methods, BEMT can predict thrust and power with a difference with respect to CFD of 3.8% and 8.2% respectively. The optimization result gives the optimum blades design with improving almost 11% in efficiency which came out from 9.4% reduction in power required which is good for helicopter performance.

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