Yooyen, Soemsak

Preferred name

Yooyen, Soemsak

Alternative Name

Yooyen, S.

Main Affiliation

International Academy of Aviation Industry

soemsak.yo@kmitl.ac.th

Now showing 1 - 10 of 12

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Numerically thermal analysis of a turbine vane at high temperature
(2019-11-26)
Prapamonthon, P.
;
Yooyen, S.
;
Sleesongsom, S.
Using conjugate heat transfer, thermal analysis of a turbine vane coated with thermal barrier coating (TBC) at a high temperature is presented. Numerical results are carried out at two turbine inlet temperatures (T <inf>∞</inf>) i.e. 783 K (low) and 1566 K (high) under two turbulence intensities (Tus) i.e. 8.3% and 16.6%. The main findings of this research are that for both Tus, the metal surface temperature reduction at the high temperature is higher than that at the low temperature because of the lower heat-flux ratio at the higher temperature. Based on the metal temperature reduction, the increasing inlet temperature has a greater influence than the increasing turbulence intensity. The results also indicate that at T <inf>∞</inf> = 783 K, on the pressure side (PS) the metal surface temperature reduction at Tu = 8.3% is lower than that at Tu = 16.6%, while on the suction side (SS) no significant difference happens when Tu increases. Interestingly, an inverse phenomenon happens for both PS and SS, that is the metal surface temperature reduction at Tu = 8.3% increases above that at Tu = 16.6% when T <inf>∞</inf> increases. This discrepancy may suggest the instability of the surface heat-flux ratio due to complex heat convection at the different inlet temperatures.
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Predicting Fuel Burn with Neural Network to Adjust Contingency Fuel of Airplane
(2023-01-01)
Ounsrimoung, Pimolrat
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Nootyaskool, Supakit
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Atchariyachanvanich, Kanokwan
;
Yooyen, Soemsak
The amount of fuel in an airplane tank is very important for flying. however, flying a short distance by adding a fuel-full tank is not energy efficient because spending a lot of tons for holding fuel weight. The flight planners who consider the amount of fuel to add to the tank by using historical data, use fuel burn calculating and adjust contingency fuel. This research presents the neural networks to predict fuel burn, which learn from historical airplane data. The experiment applied to local and international flight data and used both Airbus and Boeing. The predicted model was swapped and tested on the outbound and inbound replacements for confirmation capable of the predicted mode.
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Aircraft trajectory recognition via statistical analysis clustering for Suvarnabhumi International Airport
(2020-02-01)
Kamsing, Patcharin
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Torteeka, Peerapong
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Yooyen, Soemsak
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Yenpiem, Siriporn
;
Delahaye, Daniel
Since Suvarnabhumi International Airport is considered to be the biggest airport in Thailand, a big travelling-hub of southeast Asia and plays a significant part to the economy of Thailand relying on the tourism industry, an aircraft trajectory recognition is essential to support the high traffic management system from around the world. The first and essential stage of airport capacity enhancement is descriptive-analytic in several sections of the airport, including flight trajectory behaviors in order to plan an improvement procedure in the future. This experiment deploys K-mean and Gaussian Mixture clustering to compare results by using available automatic dependent surveillance-broadcast (ADS-B) dataset provided by the bigdata system from various websites. The test varies the number of clustering from three to ten and measures how similar an object is to its cluster by using the Silhouette score. Gaussian Mixture clustering produces at least three unique flight trajectories when setting the number of clustering equal to four, giving the Silhouette score of 0.43. K-mean clustering with the number of clustering equal to ten gives the highest Silhouette score of 0.45. However, its routes are not clearly recognized when compared with the Gaussian Mixture clustering. Although the overall results are not clearly shown in the pattern, it is enough to describe the trajectory patterns of the aircrafts taking off or landing over Suvarnabhumi International Airport.
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A statistical model for estimating statistical contingency fuel
(2022-01-01)
Atchariyachanvanich, Kanokwan
;
Kruaklai, Warune
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Chaipatchareekorn, Nattanan
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Sukteab, Nuttavadee
;
Yooyen, Soemsak
Contingency fuel is the amount of fuel used to compensate for unexpected events. This amount of fuel is equal to 5% of the trip fuel or 3% of the trip fuel when it has been determined to have an alternate airport on the route according to the rules of the Thai Civil Aviation Authority. Currently, contingency fuel planning determines the minimum and maximum values of contingency fuel based on aviation industry experience. As a result, the fuel supply may be either too much or too little on some flights. In this research, we aim to create a statistical model that can estimate the fuel required in the event of an emergency and measure the efficiency of contingency fuel with a loss function. The model uses statistical methods to calculate the contingency fuel in the form of Statistical Contingency Fuel (SCF) and monitors the fuel deviation for the planned and actual trip. We used fuel preparation data from 2018 and 2019 that was sourced from Thai Airlines data for six routes with a total of 4,184 flights. The results show that the SCF of flight A was at confidence of level 95, while that of other flights was at a confidence level of 99. The results obtained from the model can be used to assist flight planners to make better decisions concerning the determination of contingency fuel.
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The Development of an Automated Technology for Unmanned Aircraft CNS/UTM in Compliance with Safety and Security Measures of the State
(2025-01-01)
Yenpiem, Siriporn
;
Yooyen, Soemsak
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Banchong-Aksorn, Sasicha
;
Yoneyama, Keito R.
;
Jansri, Anurak
This research project supports the Senate's study and represents the government committee on promoting and developing the use of unmanned aircraft in low-altitude flights, with safety measures in accordance with the International Civil Aviation Organization's and Civil Aviation Authority of Thailand's minimum requirements. The main objective of this study is to create an innovative approach to enhance the country's competitiveness, which must also be accepted at the national and international level. This is based on the reasons for building infrastructure and networks for communications, navigation, and surveillance analysis to prevent aircraft from colliding and assessing the aircraft's behaviors in both segregated and current manned air traffic-controlled airspace. The study supports the utilization of air traffic management for the Unmanned Aircraft System Traffic Management (UTM) Platform, which is a necessary tool in facilitating the policy of using unmanned aircraft for commercial use. It can be extended for practical uses and further development in areas where there is an integration between manned and unmanned aircraft, both small and large for sustainable future development. It consists of basic theoretical analysis, system requirements for flight operations, and applications for low-altitude operations (within 500 feet and weighing less than 150 kilograms). The study methodology for constructing a quantitative and qualitative method includes: 1.Creating a system for requesting risk assessment levels for flight operation and program development 2.Creating systems for managing aviation mapping and geo-awareness information 3.Creating a system for requesting activities, flight and flight plan authorization, examining flight areas, and communication network identifications. Which will be used with tracking, advising, helping, recording, and monitoring aircraft behaviors. 4.Creating a system for examining other aircraft, airspace traffic information, obstacles during flight operations, and deconflicts. This research lays the foundation for future studies in the aviation sector, including the development of unmanned aircraft system traffic management and urban air mobility systems, and the integration of unmanned with manned aircraft, regardless of aircraft type. However, continuous national and international research will remain critical.
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Effect of polycrystalline structure on helium plasma irradiation of tungsten materials
(2018-01-01)
Saito, Seiki
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Nakamura, Hiroaki
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Yooyen, Soemsak
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Ashikawa, Naoko
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Katayama, Kazunari
Binary-collision-approximation-based (BCA-based) simulation is performed for the investigation of the effect of a polycrystalline structure on the penetration depth, absorption rate, and sputtering yield of tungsten materials irradiated by helium plasma. To clarify the possibility of suppressing the generation of helium bubbles in tungsten materials by designing the properties of the polycrystalline structure, such as grain size, the effect of the polycrystalline structure on helium bubble formation is also investigated.
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Vision-based attitude estimation for spacecraft docking operation through deep learning algorithm
(2020-02-01)
Phisannupawong, Thaweerath
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Kamsing, Patcharin
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Tortceka, Peerapong
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Yooyen, Soemsak
On-orbital services, especially in docking operation and other space object interaction. The missions need accurate, reliable, and robust detection to be an accurate in joining any interaction concerned. Two spacecrafts with an unknown mathematical model to predict the position and orientation, a computer vision-based attitude estimation system to detect the poses of spacecraft via camera is the key option of the mission. In astronautics control, the position coordinates are normally represented as the cartesian coordinate system and used a quaternions coordinate system for orientation representation because quaternions can represent the orientation of spacecraft better than physical angle and can overcome the problem of singularity. This paper aims to construct a model for both position and orientation estimation with public data. The input images are the dataset of Soyuz in the resolution of 1280x960, which is simulated by Unreal Engine 4. The implementation of this paper use GoogLeNet for a convolutional neural network model with the mathematical model of loss subject to direct regression. The result shows that a position estimation is significantly accurate with having distance error smaller than 1 meter and trand to reduce when setting a proper scaling factor for loss function. The result demonstrates a high error for orientation estimation. However, the experiment expresses that both position and orientation estimation can be improved in case of selecting a suitable scaling factor of loss function.
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Parametric study on wing-lambda-shock formation
(2021-01-01)
Chainok, Sirikorn
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Rungroch, Thanapol
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Chairach, Pattarasuda
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Prapamonthon, Prasert
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Yooyen, Soemsak
It is well-known that a wing is one of the most important parts of an aircraft as it is used to generate lift force. According to a wing moving at sufficiently high subsonic speeds, the flow speed on the wing's upper surface can be supersonic due to acceleration through the curvature-created suction, thereby forming a shock wave in a lambda shape. Additionally, the lambda shock can interact with the boundary layer flow. These phenomena relate to disturbances in the flow field, including flow separation, thus causing undesirable effects on lift production. Hence, a better understanding of the phenomenon of wing-lambda-shock formation and its nature is essential. This study presents a numerical investigation of the lambda-shock formation on an ONERA M6 wing, which is known as a swept, semi-span wing with no twist, under parametric effects of angleof-attack, and free-stream Mach number, which is increased up to the supersonic regime. The pressure coefficients obtained by simulations are validated by open data. Then, numerical results in terms of the local pressure coefficient, local Mach number, averaged lift and drag coefficients, and?-shape characteristics based on Mach number and pressure coefficients are discussed under an investigated range of the parameters. Results show that the angle-of-attack and free-stream Mach number can affect the lambda shock formation on the wing upper surface physically. Specifically, an iso-sonic surface with lambda shock waves is disturbed when the angle-of-attack and free-stream Mach number vary in an investigated range. This also affects lift and drag coefficients of the wing.
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The Development of a Web-Based Questionnaire for Automatic Risk Assessment Analysis of Unmanned Aircraft
(2025-01-01)
Yenpiem, Siriporn
;
Yoneyama, Keito R.
;
Yooyen, Soemsak
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Banchong-Aksorn, Sasicha
;
Jansri, Anuruk
One of the Civil Aviation Authority of Thailand's goals is to enhance the country's economic competitiveness through innovation. This has led to an increase in the number of commercial unmanned aircraft being used in urban areas, which presents both challenges and opportunities. One challenge is the absence of an effective air traffic management system to accommodate this growth, leading to airspace congestion and potentially hazardous situations. This study develops a risk assessment model, based on the minimum requirements of international standards, in the form of a questionnaire designed to swiftly calculate risk levels associated with unmanned aircraft operations. The methodology includes extensive secondary and primary research, as well as the analysis of key components before converting the findings into a web application. The resulting web-based tool helps categorize aircraft operations into three levels: low (open category), medium (specific category), and high (certified category), which aligns with the airspace guidelines. This tool aids in evaluating and analyzing flight activities, facilitating the safe integration of unmanned aircraft into the airspace and reducing the risk of accidents.
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Reliability-based Design Optimization of Classical Wing Aeroelasticity
(2020-07-27)
Sleesongsom, S.
;
Yooyen, S.
;
Prapamonthon, P.
;
Bureerat, S.
Flutter speed of aircraft is very important and needs to be firstly specified before a certification applied for a new aircraft by airworthiness regulator to make sure that the aircraft is free from flutter in its flight envelope. By assuming geometrical and physical parameters known, the speed is usually estimated from deterministic analyses in a design stage. In practice, some parameters are finitely measured by observing, especially for the geometrical parameters, material properties and so on due to the random in nature, which causes uncertainty of information often called uncertainties. The purpose of this paper is to combine reliability analysis and optimum design of aeroelastic aircraft wing. The classical two-dimensional wing with a typical airfoil section is used as an example in this study. To quantify uncertainty in the design of flutter speed, the discrete-time aero-elastic model and worst-case scenario are applied. Furthermore, the comparison between optimum design with/without reliability is provided in this study. The results show the proposed technique leads to the flutter speed being more conservative and realizable compared with the traditional technique.

Yooyen, Soemsak

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