Revista Vortex-Vortex Music Journal最新文献_第5页

SIMULASI KESTABILAN PROTOTYPE UAV-SPRAYER BERBASIS QUADCOPTER TERHADAP PENAMBAHAN SEKAT PADA PENAMPUNG CAIRAN 基于四轴飞行器的基于四轴飞行器的比例模型，对液体容器中的支架进行增强

Revista Vortex-Vortex Music Journal Pub Date : 2022-07-01 DOI: 10.28989/vortex.v3i2.1229

Krisnadhi Hariyanto, Bangga Dirgantara

{"title":"SIMULASI KESTABILAN PROTOTYPE UAV-SPRAYER BERBASIS QUADCOPTER TERHADAP PENAMBAHAN SEKAT PADA PENAMPUNG CAIRAN","authors":"Krisnadhi Hariyanto, Bangga Dirgantara","doi":"10.28989/vortex.v3i2.1229","DOIUrl":"https://doi.org/10.28989/vortex.v3i2.1229","url":null,"abstract":"The use of UAVs has begun to penetrate the world of agriculture. One of the functions of UAVs in agriculture is to spray pesticides. The pesticides used are liquid so that when the UAV is airborne and maneuvering, the fluid experiences fluid motion or sloshing. Sloshing that occurs can cause the balance of the UAV to be disturbed. To overcome this, a bulkhead or baffle is needed in the reservoir in order to reduce fluid movement. In the case of the research studied, the simulation of sloshing in the reservoir with the presence of baffles and without the presence of baffles. This research uses different reservoir variations and different water levels, namely 55 mm, 35 mm and 15 mm. Simulations are carried out during cruising and maneuvering flights at a speed of 2 m/s. The container modeling uses the Catia V5R20 software and the simulation uses the Ansys 14.5 software. The simulation results show that the effect of baffle placement is more visible if the baffle is placed in the xy plane, while for the baffle placement in the yz plane, the force caused by sloshing is greater. In spraying the UAV-Sprayer will more often fly forward (cruise), while for maneuvers (right or left) it is only done occasionally/not too often. So that giving baffles is more effective in the xy plane because it can reduce sloshing better than the baffles in the yz plane.","PeriodicalId":40576,"journal":{"name":"Revista Vortex-Vortex Music Journal","volume":"104 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2022-07-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"83427153","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

EXPERIMENTAL STUDY OF PORTABLE STOVE PERFORMANCE USE SOLAR ENERGY 利用太阳能的便携式灶具性能实验研究

Revista Vortex-Vortex Music Journal Pub Date : 2022-07-01 DOI: 10.28989/vortex.v3i2.1251

Rizky Sultan Adryansyah, Lathifa Putri Afisna, Fransiskus Adimas

引用次数: 0

EXPERIMENTAL STUDY OF COOLING SPRAY METHOD ONTO INCLINED HEATED SURFACES 倾斜受热面冷却喷雾法的实验研究

Revista Vortex-Vortex Music Journal Pub Date : 2022-01-15 DOI: 10.28989/vortex.v3i1.1164

T. Wibowo, Dedet Hermawan, A. Prakoso

{"title":"EXPERIMENTAL STUDY OF COOLING SPRAY METHOD ONTO INCLINED HEATED SURFACES","authors":"T. Wibowo, Dedet Hermawan, A. Prakoso","doi":"10.28989/vortex.v3i1.1164","DOIUrl":"https://doi.org/10.28989/vortex.v3i1.1164","url":null,"abstract":"Single droplet impingement onto inclined heated surface is studied experimentally. Droplet in the form of aquades is dropped from a fixed height 70 mm to the metal surface with 45º impact angle. This experiment uses 3 types of metals; Stainless Steel AISI 304, Aluminum Alloy 2024, and Copper. All material surfaces are mirror polished and assumed to have the same surface treatment condition. Surface temperatures are 110 ºC, 150 ºC and 210 ºC to determine droplet behavior characteristics. The droplet has 3.0 mm diameter and 28.5 Weber Number (low impact category). In order to analyze droplet behavior in slow motion high velocity camera 4000 fps (frames per second) is used with image resolution 1024 x 768. Data obtained then processed using MATLAB image processing technique to analyze sequence of images visually and quantitatively to determine several parameters; spreading ratio, dimensionless height and contact time.The results showed droplets have different behavior characteristics even at the same surface temperature. Droplet contact time on the copper surface is shorter than aluminum and stainless steel. This is because droplets experienced bouncing due to film boiling regime takes place earlier. Maximum spreading ratio of stainless-steel surfaces is higher than copper because changes of boiling regime on stainless steel surfaces are slower and droplet is still experiencing spreading on the surface","PeriodicalId":40576,"journal":{"name":"Revista Vortex-Vortex Music Journal","volume":"12 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2022-01-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"91110128","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

RELIABILITY ANALYSIS OF MAIN ROTOR EC 155B1 ON PIN BLADE AND ATTACH BEAMS COMPONENTS USING MARKOV ANALYSIS 用马尔可夫分析方法对主转子ec155b1销叶和附梁构件进行可靠性分析

Revista Vortex-Vortex Music Journal Pub Date : 2022-01-15 DOI: 10.28989/vortex.v3i1.1026

Irvan Aditiya, L. R. Pinandhita, Bangga Dirgantara Adiputra

引用次数: 0

AERODYNAMIC ANALYSIS OF SPORT UTILITY VEHICLE (SUV) BY COMPUTATIONAL FLUID DYNAMICS (CFD) APROACH 基于计算流体动力学(cfd)方法的运动型多功能车(suv)气动分析

Revista Vortex-Vortex Music Journal Pub Date : 2022-01-15 DOI: 10.28989/vortex.v3i1.1161

B. Junaidin

{"title":"AERODYNAMIC ANALYSIS OF SPORT UTILITY VEHICLE (SUV) BY COMPUTATIONAL FLUID DYNAMICS (CFD) APROACH","authors":"B. Junaidin","doi":"10.28989/vortex.v3i1.1161","DOIUrl":"https://doi.org/10.28989/vortex.v3i1.1161","url":null,"abstract":"The main purpose of aerodynamics analysis of a vehicle is optimizing it’s form to increase aerodynamics efficiency. More streamline of aerodynamic design of a vehicle not just effecting to lower fuel consumption which is cause by lower drag due to wind at highspeed, but also increasing stability dan control of the vehicle itself. The vehicles are existed with many variations of form so they have difference aerodynamic characteristics. For a personal vehicle like cars, have many variants such as sedan, sport utility vehicle (SUV), multipurposes utility vehicle (MPV), ect. It becomes a motivation to do research about aerodynamic analysis of a SUV car which is a car variant with huge utilize in Indonesia. In this research, aerodynamic characteristics of SUV car are evaluated by computational simulation with computational fluid dynamics (CFD) approach. CFD simulation yields aerodynamic characteristics data and flow behaviors around car model. Simulation results show that critical drag coefficient (CDcrit) of SUV car is 0.36 with lift coefficient is 0.25. the CDcrit of the car is lower than typical value for a modern car. So that, optimalization of SUV car form which analyzed is needed. Contours of pressure at car surfaces show that high pressure area are located at front of grill and windshield, and low-pressure area are located at nose and leading-trailing roof due to the form nose and leading-trailing roof are streamlines. At back surface of the car, low pressure area are formed by flow separation which creates wake.","PeriodicalId":40576,"journal":{"name":"Revista Vortex-Vortex Music Journal","volume":"43 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2022-01-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"84736676","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

ANALISIS TENSILE STRENGTH KOMPOSIT SERAT DAUN AGEL BERORIENTASI ARAH 0 DERAJAT DENGAN VARIASI MATRIKS 基于基质变化的面向AGEL叶子的纤维复合强度分析

Revista Vortex-Vortex Music Journal Pub Date : 2022-01-15 DOI: 10.28989/vortex.v3i1.1177

Lazuardy Rahendra Pinandhita

引用次数: 0

STRENGTH ANALYSIS OF CARGO-X UAV WING STRUCTURE USING SANDWICH COMPOSITE MATERIALS 基于夹层复合材料的cargo-x无人机机翼结构强度分析

Revista Vortex-Vortex Music Journal Pub Date : 2022-01-15 DOI: 10.28989/vortex.v3i1.1153

D. Hartini, B. Junaidin, Habibi Habibi

引用次数: 0

GLIDER MODEL FLYING DYNAMICS SIMULATION EAGE-X ON LONGITUDINAL MATRA 纵向矩阵上滑翔机模型飞行动力学仿真age - x

Revista Vortex-Vortex Music Journal Pub Date : 2022-01-15 DOI: 10.28989/vortex.v3i1.1165

N. Retnowati, B. Junaidin, Engelbertus Rande

{"title":"GLIDER MODEL FLYING DYNAMICS SIMULATION EAGE-X ON LONGITUDINAL MATRA","authors":"N. Retnowati, B. Junaidin, Engelbertus Rande","doi":"10.28989/vortex.v3i1.1165","DOIUrl":"https://doi.org/10.28989/vortex.v3i1.1165","url":null,"abstract":"The Glider Eagle-X aircraft is an unmanned aircraft which is expected to fly with a height of 7 meters above the ground in Yogyakarta (120 m above sea level) with a flying speed of 10 m/s. In order for the Eagle-X glider to fly stably, it is necessary to analyze the flight stability of the Eagle-X glider model. Therefore, in this study, the analysis phase of static stability and dynamic response of disturbances in the longitudinal dimension was carried out. This can be useful for students so that they can better understand the analysis of static stability and dynamic response of disturbances in the longitudinal dimension. The results of the analysis show that the flight dynamics is a value of CM-α < 0 indicating the plane is statically longitudinal and the initial response of the graph is getting smaller which indicates the plane's motion is dynamically stable. The output of the stability analysis of the flying dynamics of the Eagle-X glider model is in the form of a graph. The simulation of the flying dynamics of the Eagle-X glider in the expected longitudinal dimension is shown by the aircraft movement following the graph from the results of the stability analysis which is used as the path of the Eagle-X glider model.","PeriodicalId":40576,"journal":{"name":"Revista Vortex-Vortex Music Journal","volume":"81 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2022-01-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"87154766","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

CASE ANALYSIS ON FLIGHT CONTROL SYSTEM SIKORSKY S76 C++ FAILURE FROM YAW CONTROL ASPECT 从偏航控制角度分析西科斯基s76c++飞行控制系统故障

Revista Vortex-Vortex Music Journal Pub Date : 2022-01-15 DOI: 10.28989/vortex.v3i1.1155

F. Rahmawati, Indro Lukito, M. I. Baihaqi

{"title":"CASE ANALYSIS ON FLIGHT CONTROL SYSTEM SIKORSKY S76 C++ FAILURE FROM YAW CONTROL ASPECT","authors":"F. Rahmawati, Indro Lukito, M. I. Baihaqi","doi":"10.28989/vortex.v3i1.1155","DOIUrl":"https://doi.org/10.28989/vortex.v3i1.1155","url":null,"abstract":"Flight Control is a system that functions as a helicopter control center. Failure that occurs in flight control would certainly result inconvenience of the pilot in operating the helicopter, even the movement of the helicopter can out of control causing incident or accident. The continuity of the helicopter operation is affected by the maintenance system applied. One of mode moving system helicopter is yaw control, that could control the nose helicopter to move right and left. Fault Tree Diagram could described analytical technique, whereby an undesired state of the system is specified (usually a state that is critical from a safety or reliability standpoint). The system then analyzed in the context of its environment and operation to find the solution. Based on the analysis results of failures that occurred in the Sikorsky S76 C ++ helicopter flight control from yaw control aspect in the period of January 2015 to May 2018 with an average use of helicopter’s 2092.05 flight hours, there were 46 failures which caused by yaw control. Based on diagram, there were 4 basic events which caused unschedule maintenance on Sikorsky S76 C ++ helicopter flight control system because of yaw fail control, so that a replacement or repair was needed for the components that affected to the system failure.","PeriodicalId":40576,"journal":{"name":"Revista Vortex-Vortex Music Journal","volume":"68 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2022-01-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"80669821","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 1

PRELIMINARY DESIGN OF UNMANNED AIRLAND (PUNA) 无人机地面(puna)初步设计

Revista Vortex-Vortex Music Journal Pub Date : 2022-01-15 DOI: 10.28989/vortex.v3i1.1186

Istyawan Priyahapsara, Sri Mulyani

引用次数: 0