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Maxim Tyan,Sangho Kim,Jae-Woo Lee,Soo-Hyung Park,Young-Il Jang 한국항공우주학회 2011 한국항공우주학회 학술발표회 논문집 Vol.2011 No.11
KLA-100 is a single engine, 2 seat general aviation aircraft which is being developed by Light Aircraft Development Center at Konkuk University for obtaining the certification of KAS-VLA for the first time in Korea. The progress in aircraft configuration design for the very light aircraft development is described in the present paper. In particular, an advanced configuration design methods which has been established during the conceptual and the preliminary design stages are presented. The advanced configuration design method is systematically and effectively composed of system engineering based requirement analysis and alternative configurations determination, initial sizing and conceptual design tool, parameter based configuration generation method, computational fluid dynamics, wind tunnel testing, and design-certification integration methods.
Integrated Analysis Program Development for Light Aircraft Preliminary Design Stage
Maxim Tyan,Daniel Neufeld,Jae-Woo Lee,Sangho Kim 한국항공우주학회 2013 한국항공우주학회 학술발표회 논문집 Vol.2013 No.4
A comprehensive program development using a multi-disciplinary approach for propeller driven aircraft analysis, design and optimization is presented in this paper. The program consists of a worksheet format database with a data processing module along with modules for aerodynamic, propulsion, mission, weight and geometry analysis, and 3D geometry display. The program was written using object oriented programming to enhance exibility and extensibility compared to functional programming approach. Additional analysis modules and design optimization extensions can be written and integrated easily. The developed program source code is being continuously optimized to reduce computational time and improve effciency. Most of the methods used in current program were used for conceptual and preliminary design of the KLA-100, a new VLA category aircraft. The accuracy of the analysis methods was validated using experimental and published data.
Comprehensive preliminary sizing/resizing method for a fixed wing – VTOL electric UAV
Tyan, Maxim,Nguyen, Nhu Van,Kim, Sangho,Lee, Jae-Woo Elsevier 2017 AEROSPACE SCIENCE AND TECHNOLOGY Vol.71 No.-
<P><B>Abstract</B></P> <P>A Fixed Wing (FW) aircraft with Vertical Takeoff and Landing (VTOL) is a new type of aircraft that inherits the hovering, VTOL, and maneuvering properties of multicopters and the power-efficient cruising of an FW aircraft. This paper presents a comprehensive method for FW-VTOL electric UAV sizing and resizing. The method uses newly developed integrated analysis that combines the VTOL propulsion sizing method with modified FW aircraft sizing theories. Performance requirements are specified as a set of functional relations. Several new empirical equations are derived using available data. The required battery capacity and total mass are determined from mission analysis that includes both VTOL and FW mission segments. The design is iteratively resized when the actual components of the propulsion system are selected. A case study of a 3.5-kg FW-VTOL electric UAV is presented in this research. The results of sizing and resizing are compared to parameters of the actual aircraft manufactured. Prediction of most parameters stays within a 10% error threshold.</P>
Integrated Analysis, Design and Optimization Program Development for Advanced Air Mobility Aircraft
Maxim Tyan(장막심),JaeLyun Lee(이재륜),MinJi Kim(김민지),Woon Jae Won(원운재),Yeonju Choi(최연주),Zin Win Thu,Ki Joon Byeon(변기준),Seong Joong Park(박성중),Jae-Woo Lee(이재우) 한국항공우주학회 2022 한국항공우주학회 학술발표회 논문집 Vol.2022 No.11
Flap Design Optimization for KLA-100 aircraft in compliance with Airworthiness Certification
박진환,Maxim Tyan,Nhu Van Nguyen,김상호,이재우 한국항공우주학회 2013 한국항공우주학회 학술발표회 논문집 Vol.2013 No.4
고양력장치는 항공기의 이착륙 및 실속성능에 큰 영향을 미친다. 그러므로, 이 논문에서는 가장 효과적인 플랩 형상을 얻는 방법에 대하여 슬롯티드 플랩 설계 최적화 프로세스을 제안하였다. 플랩 펼침각 및, overlap, gap 을 양력을 증가시키는 주요 변수로 생각하였고, 정확한 해석결과를 위해 공력해석 소프트웨어로 ANSYS Fluent 13.0.0<SUP>®</SUP>을 사용하였다. 최적화된 형상은 SQP(Sequential Quadratic Programming) 알고리즘을 통해 도출됐으며, 최적화된 플랩과 함께 ADSP(Aircraft Design Synthesis Program) in-house 성능해석 코드를 사용하여 항공기의 성능을 시험하였고, 이착륙 거리, 실속속도 등의 성능변수들이 KAS-VLA 인증규정을 만족하는 결과를 얻었다. High-lift devices have a major influence on takeoff, landing and stall performance of an aircraft. Therefore, slotted flap design optimization process is proposed in this paper to obtain the most effective flap configuration. Flap deflection, gap and overlap are considered as main contributors to flap lift increment. ANSYS Fluent 13.0.0<SUP>®</SUP> used as aerodynamic analysis software that provides accurate solution within given flight conditions. Optimum configuration is obtained by Sequential Quadratic Programing (SQP) algorithm. Performance of the aircraft with optimized flap is tested using Aircraft Design Synthesis Program (ADSP), in-house performance analysis code. Obtained parameters such as takeoff, landing distance and stall speed were checked to meet KAS-VLA airworthiness requirements.