Latest articles in this journal
Vortex, Volume 2, pp 20-29; doi:10.28989/vortex.v2i1.931
The wing is part of an aircraft or UAV which has a function as a major component of producing lift, therefore if a problem occurs such as a vortex at the end of the wing it will affect its performance capability. This study aims to determine the condition of the airflow, the value of induced drag, and the selection of the design of the wingtip devices on the wing profile of the UAV LSU-05. The method used is numerical or computational methods with CFD-based software to predict the aerodynamic characteristics and phenomenon of airflow around the wing with wingtip devices and without it. The model used in this study is a half-wing LSU-05 with NACA 4415 made with CATIA V5R20 software and the simulation uses ANSYS CFX 17.1. Based on the previous simulation results, it was found that the application of the canted winglet geometry to the wing profile of the UAV LSU-05 affects the coefficient lift (CL)/coefficient drag (CD) value and induced drag. Whereas the coefficient lift (CL)/coefficient drag (CD) value before using the canted winglet was 18.904 after application, increased to 21.616, this causes the induced drag value to change inversely with the coefficient lift (CL)/coefficient drag (CD) value where the value before the application was 30.4181 N to 29.0566 N.Keywords: Canted Winglet, CFD, Wing
Vortex, Volume 2, pp 39-50; doi:10.28989/vortex.v2i1.933
Designing a system to identify damage based on damage symptom data, so as to get repair handling in accordance with the procedure using a forward chaining expert system, where the expert system is one of the computer systems that aims to solve problems by imitating the human mindset as an expert applied to one of them. Aircraft components that are frequently maintained and damaged are found, namely the landing gear of the Cessna Grand Caravan C208-B aircraft. In the process of making the damage identification system in this final project, the UML (Unified Modeling Language) modeling paradigm and the PHP programming language are used. From the research results, the landing gear damage identification system of the Cessna Grand Caravan C208-B aircraft using a forward chaining expert system can facilitate the search for damage and handling for users or technicians in dealing with a symptom that occurs in the landing gear of the Cessna Grand Caravan C208-B aircraft
Vortex, Volume 2, pp 58-69; doi:10.28989/vortex.v2i1.935
As an one of engine manufacturers, CFM produces CFM56-7B with some thrust rating versions to fulfill market demand. In this case, operator has some considerations in choosing engine which is appropriate with the demand. The engine performance is very important to be considered, especially the engine capabilities when it is being maximally operated in takeoff phase.This research discusses about the CFM56-7B engine takeoff performance comparison between 26300 lbs and 24200 lbs thrust rating configuration. By processing Test Cell Result data using formula in Engine Shop Manual - 003, author did a performance calculation to know how much the difference that happened to both of those thrust rating configuration.
Vortex, Volume 2, pp 78-84; doi:10.28989/vortex.v2i1.937
Aircraft is a type of transportation that can reach a certain area in a short time compared to other types of transportation. Every aircraft used will experience a decrease in performance along with the use of flight hours, to maintain and restore the aircraft condition to its original condition, maintenance effectiveness is needed. Aircraft maintenance carried out to keep the aircraft systems or components working properly, one of the components that need maintenance is the Air Separation Module. The purpose of this study to determine the reliability, failure rate, type of failure, and effectiveness of maintenance of the Air Separation Module.
Vortex, Volume 2, pp 1-9; doi:10.28989/vortex.v2i1.896
Bending testing is carried out in the lab. Nurtanio Adisutjipto College of Technology Yogyakarta uses the Gotech Testing Machine INC (Universal Testing Machine) UTM testing machine where the results obtained in the test are in the form of a graphic in which the maximum load value, elastic modulus, area, yield point and span have been obtained. From the results of these tests, we can compare the average value of the maximum load and the modulus of elasticity received in each specimen with variations in carbon fiber and WR fiberglass.
Vortex, Volume 2, pp 30-38; doi:10.28989/vortex.v2i1.932
In the aircraft manufacturing industry, the strength and weight of the material is one of the important considerations in structural design. Composite material is a material composed of two or more forming materials, each of which has different mechanical properties. Aircraft structure in this era are 50 - 80% composed of glass or carbon fiber composite materials as reinforcement. Unfortunately, these fibers when recycled produce harmful CO gas, difficult to degrade naturally and cause itching when in contact with human skin. For this reason, environmentally friendly and strong fibers are needed to replace the role of glass or carbon fibers. Is a bamboo plant, which is abundant in Indonesia which is considered suitable as a substitute material. In this study, a mechanical test and descriptive analysis were carried out on the strength of the composite material with variations in the types of bamboo fibers apus, wulung, tutul and petung. These fibers are arranged with epoxy resin and hardener as a binding material (matrix). And each fiber will be arranged in 0 ° pattern to the matrix. Then each material with a different fiber type will be tested for tensile and bending to obtain the value of stress and strain that occurs at its maximum loading. And the result is the average tensile stress value (Mpa) composite material of apus bamboo is 75.95, wulung bamboo 49.92, petung bamboo 112.73, tutul bamboo 83.85. Then the average bending stress (Mpa) composite material of apus bamboo was 239.073, wulung bamboo 214.236, petung bamboo 249.67, tutul bamboo 272.79. With this result, bamboo fiber composites are considered to be able to replace the role of carbon or glass fibers, as an alternative composite material in some parts of the interior fuselage of aircraft panels. Keyword: Composites material, Matrix, Bamboo Fibers, Carbon and Glass Fibers, Stress and Strain.
Vortex, Volume 2, pp 51-57; doi:10.28989/vortex.v2i1.934
This study aims to determine the results of the analysis of the causes a failure that occurred in the Electric Motor-Driven Pump system on an aircraft. Boeing 737-800. The data used is in the form of a Pilot Report from the Batik airline.Water in the period 2013 to 2020.The method used in this research is Failure Mode and Effect Criticality Analysis (FMECA). FMECA is a method used to analyze the causes of damage to a system / component,along with the effects if there is damage to the system / component. The first step in this research is to find case data happened to the hydraulic system (ATA 29) on the airline Batik Air, then perform data processing. From the results of the analysis, the results of the RPN value on Electric Motor-Driven.The highest pump is because EMDP cannot supply pressure to the system. Based on the RPN calculation, the RPN value was obtained at 12. This value obtained from the matrix in the safety standard manual from Batik Air.
Vortex, Volume 2, pp 70-77; doi:10.28989/vortex.v2i1.936
Until now, Gading Airfield cannot be used for commercial flights. However, in the future, along with the increasing number of commercial and training flights, Gading Airfield will continue to be developed to help smooth flights in DI Yogyakarta. Thus some flight guidelines for civil aviation must be made. Several analysis and calculation methods are carried out starting from general analysis of the airfield, counting and design of the takeoff guide patron starting from two sides of the runway, namely from RWY 10 and 28. The calculation consists of MTOW calculation which is limited by PCN, calculation of takeoff path, calculation Takeoff distance requirement, calculation of climb segment up to 1.500 feet, calculation of flight turn 1.500 feet, to design patron takeoff path guidance.
Vortex, Volume 2, pp 10-19; doi:10.28989/vortex.v2i1.921
Soekarno Hatta International Airport and Halim Perdana Kusuma Airport are located in the Jabodetabek metropolitan area which is the largest area for air transportation users in Indonesia. Along with the increasing number of users of air transportation modes, a multi-airport system is needed to reduce the burden on one airport. The method used is a qualitative analysis method by comparing existing data with data obtained from research to determine a multi-airport criteria. From the results of data processing, it is concluded that the development of a multi-airport system in the Jabodetabek metropolitan area has several criteria, namely airport distance, accessibility, airport management, airport route services, passenger demand as well as government regulations and policies governing the multi-airport systems.
Vortex, Volume 2, pp 85-92; doi:10.28989/vortex.v2i1.938
Air transportation is increasingly in demand.. Airports as a gathering place for passengers must be prepared to face this increase in the number of aircraft passengers.This increase in airplane passengers certainly affects and is influenced by various socio-economic factors, including: population, number of hotels, number of tourists, GRDP (Gross Regional Domestic Product), and number of train passengers. Halim Perdana Kusuma Airport could be considered as new airports in Indonesia because it has only been used for commercial flights for 7 years starting from opening for public flights in 2014. This airport has visually increased the number of passengers each year so it is suitable as an object of research. Calculation of the estimated increase in airplane passengers at the airport can be done using a multiple linear regression method, while to find out how much influence the size of the increase in airplane passengers and socio-economic factors can use the correlation coefficient search