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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 66 Documents
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An Experimental Analysis on the Effects of Stagger on the Aerodynamic Forces of Tandem Wings Y Parlindungan; S Tobing
AVIA Vol 2, No 2: (Dec, 2020)
Publisher : Institut Teknologi Bandung

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.47355/avia.v2i2.21

Abstract

This study is inspired by the flapping motion of natural flyers: insects. Many insects have two pairs of wings referred as tandem wings. Literature review indicates that the effects of tandem wing are influenced by parameters such as stagger (the stream-wise distance between the aerodynamic center of the front and the rear airfoil), angle-of-attack and flow velocity. As a first stage, this study focuses on the effects of stagger (St) on the aerodynamic performance of tandem wings. A recent numerical study of stagger on tandem airfoils in turbulent flow (Re = 6000000) concluded that a larger stagger resulted in a decrease in lift force, and an increase in drag force. However, for laminar flow (Re = 2000), increasing the stagger was not found to be detrimental for aerodynamic performance. Another work also revealed that the maximum lift coefficient for a tandem configuration decreased with increasing stagger. The focus of this study is to perform an experimental analysis of tandem two-dimensional (2D) NACA 0012 airfoils. The two airfoils are set at the same angle-of-attack of 0° to 15° with 5° interval and three variations of stagger: 1c, 1.5c and 2c. The experiments are conducted using an open-loop-subsonic wind tunnel at a Reynolds number of 170000. The effects of St on the aerodynamic forces (lift and drag) are analyzed
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.
Study Travel Time in the Movement of Passengers and Baggage at the Arrival Station of Sultan Hasanuddin International Airport Makassar F Sabur
AVIA Vol 2, No 2: (Dec, 2020)
Publisher : Institut Teknologi Bandung

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.47355/avia.v2i2.22

Abstract

Airport provides facilities for services to aircraft, passengers, and goods. One of the activities at the airport is handling your luggage. At some particular time, especially in crowded flight, a passenger still faces delays in receiving baggage at the arrival terminal. The purpose of the research is to know the travel time difference and the factors that influence the travel timedifferences in the movement of passengers and baggage at the arrival terminal of Sultan Hasanuddin International Airport of Makassar. The type of research is a correlation study, using primary data in the form of data direct field measurements as well as secondary data from the monthly reports-MATSC Support Operations Division Aeronautical Information Service in theform of fixed flight schedules and Side Air Operations Division in the form of data movement apron. Processing the data is by using SPSS version 18:00 The findings is: the smallest time difference between the passenger and baggage occurs when using the bus, followed a garbarata and the greatest difference in time when walking, so that it can be concluded that the use of buses more effective in reducing delays in receiving the baggage at the arrival terminal of International Airport Sultan Hasanuddin of Makassar
Analysis of 6-Pulse and 12-Pulse in Conversion of the 115VAC/400Hz to 270 VDC for Application on Fighter Dwi Rochma Agustiningsih, Edy Suwondo, Muhammad Kusni
AVIA Vol 1, No 1: (Dec, 2019)
Publisher : Institut Teknologi Bandung

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.47355/avia.v1i1.11

Abstract

The development of aircraft secondary power technology is moving from mechanical power, pneumatic power and hydraulic power to electric power. The trend toward electric power is known as More Electric Aircraft (MEA). Modern military aircraft are designed using 270VDC for electric power system. Today, some military aircraft still use 115VAC/400Hz for their electrical power system. If this type of aircraft need provides 270VDC electrical power, then they require Multi-Pulse Transformer Rectifier Unit (TRU). The development of this type TRU has not been aimed to comply with aircraft military standards. This research investigates the variation of the number of pulses (p) and firing angle (α) to the amplitude ripple voltage, output voltage, and distortion factor in order to comply with the MIL-STD-704F standards. The multi-pulse transformer rectifier unit being analyzed consists of 6-Pulse and 12-Pulse. The research shows that the amplitude ripple voltage and distortion factor of the 6-Pulse TRU do not comply MIL-STD-704F. The amplitude ripple voltage and distortion factor of 12-Pulse comply MIL-STD-704F with firing angle (α) ≤4°.Keywords: Transformer Rectifier Unit, thyristor, ripple voltage, distortion factor, firing angle
CFD Analysis on Aerodynamic Coefficients of Flying Saucer N Ruseno
AVIA Vol 3, No 1: (June, 2021)
Publisher : Institut Teknologi Bandung

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.47355/avia.v3i1.38

Abstract

With the growing of Unmanned Aerial Vehicle (UAV) usage, many new types of UAV are introduced. Flying Saucer is a new type of UAV which is not yet famous in the market. The aim of this study is to analysis the aerodynamic coefficients of a Flying Saucer. The research question arise is What the optimum angle of attack for Flying Saucer flight is. The study is conducted in Computational Fluid Dynamics (CFD) using COMSOL Multiphysics with Laminar Flow physics for several angles of attack. The analysis considers Lift and Drag coefficient in the form of ???????? and ???????? to angle of attack (α) plot, ratio of ????????/???????? to angle of attack (α) plot and drag polar plot. We conclude that a symmetric Flying Sauce has aerodynamic characteristic with the optimum operational angle of attack in the range of 8 to 16 deg. The ???????? and ???????? has a quadratic relationship with large ????????0 due to the geometric of Flying Saucer. It recommends that further study should explore in the area of zero and maximum angle of attack (α) and validation in wind tunnel experiment.
Flight Test Evaluation for Tilt Rotor Unmanned Aerial Vehicle Development A A Arif; R A Sasongko
AVIA Vol 3, No 1: (June, 2021)
Publisher : Institut Teknologi Bandung

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.47355/avia.v3i1.39

Abstract

Tiltrotor Unmanned Aerial Vehicle (UAV) is type of UAV that combine fixed wing (FW) and multirotor (VTOL) configuration in order to be able to perform instant transition from one configuration to another. Tiltrotor UAV has advantage to perform takeoff and landing from limited space such as plantation farm, forest, and residential area. Tiltrotor also can carry various mission since it has 2 configuration such as cargo drone, safer payload dropping, and mapping. In this research tiltrotor UAV designed with ruddervator (V-Tail) configuration with 3 motors in total, 2 motors placed on main wing with tilting capability and 1 motor placed at the end of fuselage as pitch controller in VTOL mode. Test flight will be conducted and evaluated to test UAV capability in hovering and transition from one mode to another
Comparison between Vortex-In-Cell and Vortex Particle Methods on Two-Dimensional Problem Canh, C X; Zuhal, L R; Muhammad, H
AVIA Vol 3, No 1: (June, 2021)
Publisher : Institut Teknologi Bandung

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.47355/avia.v3i1.40

Abstract

This research is concerned with the two-dimensional vortex method (VM) solvers. We develop and investigate the performance of the Vortex-In-Cell (VIC) and Vortex Particle Method (VPM) which are well known as the VM’s family members. The advantage of these both methods are that we can accelerate velocity computation procedure, an N-body problem in numerical methods, by using Fast Fourier Transform (FFT) and Fast Multipole Method (FMM), respectively. In addition, the viscous calculation process in VPM can be accelerated by using a scheme of Nearest Neighbor Particle Searching (NNPS) algorithms. Moreover, the no-through boundary condition treatment issue can be easily handled by using an immersed boundary condition for both methods. The accuracy and numerical cost of both numerical methods will be examined by simulating flow over an Impulsively Started Circular Cylinder and comparisons
Circular Airport Concept Analysis for Indonesian Archipelago A S Kusumalestari; F Franciscus
AVIA Vol 3, No 1: (June, 2021)
Publisher : Institut Teknologi Bandung

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.47355/avia.v3i1.36

Abstract

Circular Airport Concept, issued by Hessellink in 2014, divides the expert opinion, but the project is still running. The idea is how visible to engage this concept into Indonesian Archipelago. To build airport within limit area for several islands in Indonesia is a big challenge. Some pioneer routes which connecting remote areas with a small aircraft is still searching for some development. Another challenge is the environmental sustainability. This paper makes an analysis about application of the concept into Indonesian Archipelago, and how this concept might be a solution. The discussion will cover analysis of airport design, aircraft to operate, and area to be treated.
Development of Flight Multifunctional Indicator Based on A320 and B737 NG Flight Indicator A R Pandie; A V Kirillov
AVIA Vol 3, No 1: (June, 2021)
Publisher : Institut Teknologi Bandung

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.47355/avia.v3i1.37

Abstract

The objectives of this research are: to know the concept of modeling and simulation the cockpit display based on disadvantages and differences between A320 and B737NG; to offer the development and new technology to design the development (new) flight instruments of the display based on Airbus A320 and Boeing B737 NG flight instrument technology. Methodologies that have been used in this research are literature review, interview/discussion/questionnaire, and descriptive analysis. Questionnaire towards the users/pilots who flies airplane A320 or B737 NG. For the questionnaire, the Likert-scale method is utilized to collect data and information. This research result’s in finding that: 1. the technology of flight instrument system between A320 and B737 NG visually displays similarity with several differences such as ergonomic side, ECAM technology, and VSD technology. 2. Based on works of literature review and response from the users/pilots, the author finds and proposes several technologies or requirements to apply in the new type model of PFD and Multi-function Display, they are including: PFD and MFD merged into one display only with some additional menu buttons; ECAM + engine warning display, ECAM + systems display, and digital instruction to solve the problem merged into one display only with some additional buttons; display design is using the fully digital display, computerized system, LCD technology, VSD, and EHSI technology, and layout display is using configuration “basic T”; standby flight instrument merged into one display only with some additional menu buttons

Page 2 of 7 | Total Record : 66

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