Publications

2025

1. Multi-objective Optimal Sizing Method for a Cruise Missile with Multi-phase Missions

   Seongjoong Park, Ki-Jun Byeon, Yeon-Ju Choi, Kwon-Su Jeon, Maxim Tyan, Seok-Min Choi, and Jae-Woo Lee

   International Journal of Aeronautical and Space Sciences, Apr 2025

   Abs DOI

   This paper presents a multi-objective optimal sizing method for a cruise missile with a multi-phase mission involving a boost phase and an air-breathing phase. Proposed method includes a mission profile analysis which simplifies the compound mission profile of the cruise missile to enable the missile to be sized in the conceptual design phase. Since a boost phase is usually included in the mission of a cruise missile to enable fast acceleration immediately after launch, a booster sizing method is also presented. After the booster phase, there is an air-breathing phase that includes climb and acceleration, cruise, etc. For this phase, we first present a hybrid method for predicting drag, which is difficult to estimate in the existing sizing process. In addition, tail sizing is included, based on the reverse application of longitudinal stability processes. We also present a mission analysis method for estimating fuel consumption in the sizing step. Proposed sizing method is implemented using a Python-based sizing tool, and includes all the processes associated with the sizing method presented in this paper. Finally, we perform a sizing that includes multi-objective optimization, with the aim of minimizing the total launch weight and maximizing the total range.

2. Possibility-based Sizing Method for Hybrid Electric Aircraft

   Zin Win Thu, Maxim Tyan, Yong-Hyeon Choi, Mohammad Irfan Alam, and Jae-Woo Lee

   IEEE Access, Apr 2025

   Abs DOI

   At the early stage of aircraft design, the sizing process plays a critical role in determining key parameters such as mass, geometry, and propulsion system characteristics based on design requirements. However, existing sizing methods, relying on historical data, assumptions, and low-fidelity models, often fail to address uncertainties, leading to costly design modifications, particularly for electric aircraft, where technological uncertainties pose significant challenges. It is crucial to account for uncertainties at the sizing stage to ensure reliable outcomes, highlighting the need for a method that efficiently integrates uncertainty into the process. We propose a possibility-based sizing approach, which accounts for design uncertainties into sizing process, yields possible feasible design outcomes and identifies critical parameters for refinement in later stages. We verified our approach with two case studies meeting CS23 certification. The results demonstrate design feasibility through trade-offs between conservative and optimistic designs, with possibility indices from 0.75 to 1, identifying maximum and stall speeds as key limiting factors. Sensitivity analysis shows that aerodynamic design, airframe, and propulsion efficiencies significantly impact maximum takeoff mass. Propulsion system integration achieves a relative mass reduction of 0.05, outperforming hydrogen fuel cells (0.025) and battery systems (0.009). The study highlights that power density is more critical than battery energy density in high-power segments, providing valuable insights for sizing and key parameters in future hybrid electric aircraft development.

2024

1. Integrated Propulsion System Analysis Framework for Designing Advanced Air Mobility Aircraft

   Mohammad Irfan Alam, Zin Win Thu, Nghia Nguyen, Maxim Tyan, and Jae-Woo Lee

   IEEE Transactions on Transportation Electrification, Dec 2024

   Abs DOI

   Electric aircraft emerge as a promising solution to mitigate the environmental impact of the aviation sector. The integration of electric propulsion components in such aircraft differs significantly from that of conventional aircraft. In the latter case, initial sizing frameworks typically employ mathematical models that operate solely with high-level propulsion parameters, such as power, thrust, and efficiency. However, in the case of advanced air mobility (AAM) aircraft, the propulsion system integration at the sizing stage is critical to exploring more comprehensive configurations and avoiding infeasible solutions. We introduce a framework for designing AAM aircraft, emphasizing the crucial integration of propulsion components from the initial phase. It combines top-level, low-fidelity methods, higher-fidelity components, and system-level propulsion analysis. This modular approach facilitates realistic aircraft configuration exploration by efficiently balancing high and low-fidelity studies. This integrated approach significantly reduces the risk of infeasible or impractical solutions and allows for adaptable coupling with various models of differing fidelity. We demonstrate the framework’s effectiveness by designing and analyzing a box-wing vertical takeoff and landing electric aircraft. Key results suggest setting the propeller pitch optimally at each mission segment increases the cruising range of aircraft by at least 10%. Similarly, varying the battery cell type with a fixed pack mass results in up to 10 km gain in cruising range for the optimal cruise speed. Propeller pitch, battery cell type, and other parameters are often omitted in the initial sizing stage. Our results emphasize the high sensitivity of aircraft performance to these parameters. The proposed framework illustrates its potential to advance electric aircraft design, contributing to a more sustainable future in aviation.

2. Extended Hierarchical Kriging Method for Aerodynamic Model Generation Incorporating Multiple Low-Fidelity Datasets

   Vinh Pham, Maxim Tyan, Tuan Anh Nguyen, and Jae-Woo Lee

   Aerospace, Jan 2024

   Abs DOI

   Multi-fidelity surrogate modeling (MFSM) methods are gaining recognition for their effectiveness in addressing simulation-based design challenges. Prior approaches have typically relied on recursive techniques, combining a limited number of high-fidelity (HF) samples with multiple low-fidelity (LF) datasets structured in hierarchical levels to generate a precise HF approximation model. However, challenges arise when dealing with non-level LF datasets, where the fidelity levels of LF models are indistinguishable across the design space. In such cases, conventional methods employing recursive frameworks may lead to inefficient LF dataset utilization and substantial computational costs. To address these challenges, this work proposes the extended hierarchical Kriging (EHK) method, designed to simultaneously incorporate multiple non-level LF datasets for improved HF model construction, regardless of minor differences in fidelity levels. This method leverages a unique Bayesian-based MFSM framework, simultaneously combining non-level LF models using scaling factors to construct a global trend model. During model processing, unknown scaling factors are implicitly estimated through hyperparameter optimization, resulting in minimal computational costs during model processing, regardless of the number of LF datasets integrated, while maintaining the necessary accuracy in the resulting HF model. The advantages of the proposed EHK method are validated against state-of-the-art MFSM methods through various analytical examples and an engineering case study involving the construction of an aerodynamic database for the KP-2 eVTOL aircraft under various flying conditions. The results demonstrated the superiority of the proposed method in terms of computational cost and accuracy when generating aerodynamic models from the given multi-fidelity datasets.

3. Enhanced Calibration and Performance Prediction Method for Entire Propulsion System of eVTOL UAV

   Jae Lyun Lee, Maxim Tyan, Do Youn Kwon, and Jae-Woo Lee

   IEEE Transactions on Transportation Electrification, Sep 2024

   Abs DOI

   The electric propulsion system (EPS) comprises various components, such as a battery, motor, controller, and propeller. Accurate analysis of these components requires many detailed parameters which can be challenging to obtain during the initial design phases. This article presents a method for constructing a calibration and global prediction model for a family of EPS components, to overcome analysis limitations during these design stages. A low-fidelity (LF) analysis method is developed to predict EPS performance with a given set of specifications, and wind tunnel tests are conducted to provide high-fidelity data. A linear calibration model is developed by modifying theoretical equations to include relative additive terms and coefficients. Subsequently, a global prediction model is generated using a radial basis function (RBF) network. The model predicts calibration coefficients for a set of target EPS combinations without corresponding high-fidelity data. By substituting these coefficients into the modified equations, EPS performance can be predicted with enhanced accuracy, without requiring additional high-fidelity analysis. Three examples of global prediction models are presented to demonstrate the feasibility and current limits of the method.

2023

1. Adaptive data fusion framework for modeling of non-uniform aerodynamic data

   Vinh Pham, Maxim Tyan, Tuan Anh NGUYEN, Chi-Ho Lee, LV Thang NGUYEN, and Jae-Woo Lee

   Chinese Journal of Aeronautics, Jul 2023

   Abs DOI

   Multi-fidelity Data Fusion (MDF) frameworks have emerged as a prominent approach to producing economical but accurate surrogate models for aerodynamic data modeling by integrating data with different fidelity levels. However, most existing MDF frameworks assume a uniform data structure between sampling data sources; thus, producing an accurate solution at the required level, for cases of non-uniform data structures is challenging. To address this challenge, an Adaptive Multi-fidelity Data Fusion (AMDF) framework is proposed to produce a composite surrogate model which can efficiently model multi-fidelity data featuring non-uniform structures. Firstly, the design space of the input data with non-uniform data structures is decomposed into subdomains containing simplified structures. Secondly, different MDF frameworks and a rule-based selection process are adopted to construct multiple local models for the subdomain data. On the other hand, the Enhanced Local Fidelity Modeling (ELFM) method is proposed to combine the generated local models into a unique and continuous global model. Finally, the resulting model inherits the features of local models and approximates a complete database for the whole design space. The validation of the proposed framework is performed to demonstrate its approximation capabilities in (A) four multi-dimensional analytical problems and (B) a practical engineering case study of constructing an F16C fighter aircraft’s aerodynamic database. Accuracy comparisons of the generated models using the proposed AMDF framework and conventional MDF approaches using a single global modeling algorithm are performed to reveal the adaptability of the proposed approach for fusing multi-fidelity data featuring non-uniform structures. Indeed, the results indicated that the proposed framework outperforms the state-of-the-art MDF approach in the cases of non-uniform data.

2022

1. Advanced Sizing Methodology for a Multi-Mode eVTOL UAV Powered by a Hydrogen Fuel Cell and Battery

   Jae-Hyun An, Do-Youn Kwon, Kwon-Su Jeon, Maxim Tyan, and Jae-Woo Lee

   Aerospace, Feb 2022

   DOI
2. Model-Driven Impact Quantification of Energy Resource Redundancy and Server Rejuvenation on the Dependability of Medical Sensor Networks in Smart Hospitals

   Francisco Airton Silva, Carlos Brito, Gabriel Araújo, Iure Fé, Maxim Tyan, Jae-Woo Lee, Tuan Anh Nguyen, and Paulo Romero Martin Maciel

   Sensors, Feb 2022

   Abs DOI

   The spread of the Coronavirus (COVID-19) pandemic across countries all over the world urges governments to revolutionize the traditional medical hospitals/centers to provide sustainable and trustworthy medical services to patients under the pressure of the huge overload on the computing systems of wireless sensor networks (WSNs) for medical monitoring as well as treatment services of medical professionals. Uncertain malfunctions in any part of the medical computing infrastructure, from its power system in a remote area to the local computing systems at a smart hospital, can cause critical failures in medical monitoring services, which could lead to a fatal loss of human life in the worst case. Therefore, early design in the medical computing infrastructure’s power and computing systems needs to carefully consider the dependability characteristics, including the reliability and availability of the WSNs in smart hospitals under an uncertain outage of any part of the energy resources or failures of computing servers, especially due to software aging. In that regard, we propose reliability and availability models adopting stochastic Petri net (SPN) to quantify the impact of energy resources and server rejuvenation on the dependability of medical sensor networks. Three different availability models (A, B, and C) are developed in accordance with various operational configurations of a smart hospital’s computing infrastructure to assimilate the impact of energy resource redundancy and server rejuvenation techniques for high availability. Moreover, a comprehensive sensitivity analysis is performed to investigate the components that impose the greatest impact on the system availability. The analysis results indicate different impacts of the considered configurations on the WSN’s operational availability in smart hospitals, particularly 99.40%, 99.53%, and 99.64% for the configurations A, B, and C, respectively. This result highlights the difference of 21 h of downtime per year when comparing the worst with the best case. This study can help leverage the early design of smart hospitals considering its wireless medical sensor networks’ dependability in quality of service to cope with overloading medical services in world-wide virus pandemics.

3. Rapid Airfoil Inverse Design Method with a Deep Neural Network and Hyperparameter Selection

   Maxim Tyan, Cheol Kyun Choi, Tuan Anh Nguyen, and Jae-Woo Lee

   International Journal of Aeronautical and Space Sciences, Sep 2022

   Abs DOI

   A deep-learning based rapid engineering design (DL-RED) algorithm is developed and presented for solving engineering inverse design problems. The algorithm generates an inverse design deep neural network (IDNN) by performing a two-stage hyperparameter selection and iteratively enhancing training database. The initial hyperparameter selection defines the configuration of IDNN that increases the accuracy of inverse design and reduces the network training time. Then database enhancement loop refines the training database by iteratively adding new samples to initial database based on results of validation. After the training database is generated the final hyperparameter selection is performed. A construction of Airfoil inverse design neural network is demonstrated in this paper. The Airfoil-IDNN generates a NACA 4-series airfoil that corresponds to target aerodynamic parameters given as an input. During the database enhancement loop the validation mean squared error has reduced to 57.37%, and totally to 96.48% after the final hyperparameter selection. The accuracy of the Airfoil-IDNN was demonstrated using two case studies. The first case study shows how accurate the network can generate an airfoil with arbitrary input parameters. The second one shows whether the IDNN can generate existing airfoils by a set of target parameters.

2021

1. iADA*-RL: Anytime Graph-Based Path Planning with Deep Reinforcement Learning for an Autonomous UAV

   Aye Aye Maw, Maxim Tyan, Tuan Anh Nguyen, and Jae-Woo Lee

   Applied Sciences, Jan 2021

   Number: 9 Publisher: Multidisciplinary Digital Publishing Institute

   DOI
2. Enhancement of light aircraft 6 DOF simulation using flight test data in longitudinal motion

   Le Viet Thang Nguyen, Maxim Tyan, Jae-Woo Lee, and Sangho Kim

   The Aeronautical Journal, Aug 2021

   DOI

2020

1. iADA*: Improved Anytime Path Planning and Replanning Algorithm for Autonomous Vehicle

   Aye Aye Maw, Maxim Tyan, and Jae-Woo Lee

   Journal of Intelligent & Robotic Systems, Aug 2020

   Abs DOI

   Path planning of autonomous mobile robots in a real-world environment presents several challenges which are usually not raised in other areas. The real world is inherently complex, uncertain and dynamic. Therefore, accurate models of path planning are difficult to obtain and quickly become outdated. Anytime planners are ideal for this type of problem as they can find an initial solution very quickly and then improve it as time allows. This paper proposes a new anytime incremental search algorithm named improved Anytime Dynamic A*(iADA*). The algorithm is based on the currently popular anytime heuristic search algorithm, which is Anytime Dynamic A*(ADA*). The iADA* algorithm improves the calculation of the path lengths and decreases the calculating frequency of the path throughout the search, making it significantly faster. The algorithm is designed to provide an efficient solution to a complex, dynamic search environment when the locally changes affected. Our study shows that the two-dimensional path-planning iADA* experiments were between 2.0 to 3.7 times faster than ADA*, both in partially known and fully unknown dynamic environments. Additionally, in this paper shows the experiment results of the comparison with other four existing algorithms based on computing time and path lengths. iADA* was an average 2.57 times reduced on the computational time for the environment which locally changes effected. For the path length is little increase, but it is not the worst case. According to the experiments, the more the environmental problems and complexity increases, the more iADA* provides a rapid in-search time and total time to obtain the final solution.

2019

1. Efficient multi-response adaptive sampling algorithm for construction of variable-fidelity aerodynamic tables

   Maxim Tyan and Jae-Woo Lee

   Chinese Journal of Aeronautics, Jan 2019

   IF=2.095

   Abs DOI

   Adaptive sampling is an iterative process for the construction of a global approximation model. Most of engineering analysis tools computes multiple parameters in a single run. This research proposes a novel multi-response adaptive sampling algorithm for simultaneous construction of multiple surrogate models in a time-efficient and accurate manner. The new algorithm uses the Jackknife cross-validation variance and a minimum distance metric to construct a sampling criterion function. A weighted sum of the function is used to consider the characteristics of multiple surrogate models. The proposed algorithm demonstrates good performance on total 22 numerical problems in comparison with three existing adaptive sampling algorithms. The numerical problems include several two-dimensional and six-dimensional functions which are combined into single-response and multi-response systems. Application of the proposed algorithm for construction of aerodynamic tables for 2D airfoil is demonstrated. Scaling-based variable-fidelity modeling is implemented to enhance the accuracy of surrogate modeling. The algorithm succeeds in constructing a system of three highly nonlinear aerodynamic response surfaces within a reasonable amount of time while preserving high accuracy of approximation.

2. Design-airworthiness integration method for general aviation aircraft during early development stage

   Maxim Tyan, Jungwon Yoon, Nhu Van Nguyen, Jae-Woo Lee, and Sangho Kim

   Aircraft Engineering and Aerospace Technology, Aug 2019

   Abs DOI

   Purpose Major changes of an aircraft configuration are conducted during the early design stage. It is important to include the airworthiness regulations at this stage while there is extensive freedom for designing. The purpose of this paper is to introduce an efficient design framework that integrates airworthiness guidelines and documentation at the early design stage. Design/methodology/approach A new design and optimization process is proposed that logically includes the airworthiness regulations as design parameters and constraints by constructing a certification database. The design framework comprises requirements analysis, preliminary sizing, conceptual design synthesis and loads analysis. A design certification relation table (DCRT) describes the legal regulations in terms of parameters and values suitable for use in design optimization. Findings The developed framework has been validated and demonstrated for the design of a Federal Aviation Regulations (FAR) 23 four-seater small aircraft. The validation results show an acceptable level of accuracy to be applied during the early design stage. The total mass minimization problem has been successfully solved while satisfying all the design requirements and certification constraints specified in the DCRT. Moreover, successful compliance with FAR 23 subpart C is demonstrated. The proposed method is a useful tool for design optimization and compliance verifications during the early stages of aircraft development. Practical implications The new certification database proposed in this research makes it simpler for engineers to access a large amount of legal documentation related to airworthiness regulations and provides a link between the regulation text and actual design parameters and their bounds. Originality/value The proposed design optimization framework integrates the certification database that is built of several types of legal documents such as regulations, advisory circulars and standards. The Engineering Requirements and Guide summarizes all the documents and design requirements into a single document. The DCRT is created as a summary table that indicates the design parameters affected by a given regulation(s), the design stage at which the parameter can be evaluated and its value bounds. The introduction of the certification database into the design optimization framework significantly reduces the engineer’s load related for airworthiness regulations.

2018

1. Efficient approach to database integration for an aerospace vehicle design and certification framework

   Aye Aye Maw, Tun Lwin, Maxim Tyan, Jae-Woo Lee, and Sangho Kim

   Advances in Engineering Software, Apr 2018

   Abs DOI

   The integration of distributed data sources is one of the main problems of engineering software. The data integration process for a heterogeneous legacy system is a key aspect of the development of a computerized system and in the integration of a design framework. In this research, our approach to data integration focuses on developing system-building techniques for efficient data integration queries. Keyword-based data searching is investigated and applied within a database for a design framework. A database table connector (DTC) wrapper program is implemented based on the use of data integration processes and keyword-based searching. The DTC provides data integration for various data resources from legacy programs and database management systems using SQL querying. The DTC enables designers and developers to rapidly and efficiently develop integration frameworks for different data resources. This paper also describes the implementation and deployment of the Certification and Aircraft Design Integration System framework, which integrates various analysis and optimization codes, computer-aided design software and database management systems. Multiple data types are used within the framework, including databases, spreadsheets, flat files, XML files and personal data management. Several aircraft design and optimization problems are successfully solved using the developed framework.

2017

1. Comprehensive preliminary sizing/resizing method for a fixed wing-VTOL electric UAV

   Maxim Tyan, Nhu Van Nguyen, Sangho Kim, and Jae-Woo Lee

   Aerospace Science and Technology, Dec 2017

   SCI IF=2.057

   Abs DOI

   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.

2. Database Adaptive Fuzzy Membership Function Generation for Possibility-Based Aircraft Design Optimization

   Maxim Tyan, Nhu Van Nguyen, Sangho Kim, and Jae-Woo Lee

   Journal of Aircraft, Jan 2017

   Abs DOI

   Aircraft conceptual design traditionally uses simplified analysis and optimization methods to generate the basic configuration of the aircraft. Analysis methods cannot fully represent the real physical phenomena, and hence the optimum solution may fail to satisfy the constraints when more sophisticated analysis is applied. This research proposes the use of a database to estimate the prediction errors associated with a particular analysis method. Newly proposed adaptive piecewise-linear fuzzy membership functions accurately represent the intervals of prediction errors to compensate for the discrepancies caused by analysis. A possibility-based design optimization framework is developed to solve nonprobabilistic design problems with uncertainties represented by the adaptive piecewise-linear fuzzy membership intervals. A two-seater light aircraft design problem has been solved to demonstrate the proposed method. The adaptive piecewise-linear fuzzy membership fu}nctions for six major analysis modules of in-house software were constructed using information about 15 aircraft stored in the database. Estimated errors of the analysis stay within 10% range. The adaptive piecewise-linear fuzzy membership function for selected parameters stores 39% more samples on average than the triangular functions that are traditionally used for possibility-based design optimization. The results of the design problem show that the objective function is improved by 3.4% with uncertain intervals covering 100% of database samples and by 46.1% with 12.3% database coverage.

3. A Tailless UAV Multidisciplinary Design Optimization Using Global Variable Fidelity Modeling

   Maxim Tyan, Nhu Van Nguyen, and Jae-Woo Lee

   International Journal of Aeronautical and Space Sciences, Dec 2017

   Abs DOI

   This paper describes the multidisciplinary design optimization (MDO) process of a tailless unmanned combat aerial vehicle (UCAV) using global variable fidelity aerodynamic analysis. The developed tailless UAV design framework combines multiple disciplines that are based on low-fidelity and empirical analysis methods. An automated high-fidelity aerodynamic analysis is efficiently integrated into the MDO framework. Global variable fidelity modeling algorithm manages the use of the high-fidelity analysis to enhance the overall accuracy of the MDO by providing the initial sampling of the design space with iterative refinement of the approximation model in the neighborhood of the optimum solution. A design formulation was established considering a specific aerodynamic, stability and control design features of a tailless aircraft configuration with a UCAV specific mission profile. Design optimization problems with low-fidelity and variable fidelity analyses were successfully solved. The objective function improvement is 14.5% and 15.9% with low and variable fidelity optimization respectively. Results also indicate that low-fidelity analysis overestimates the value of lift-to-drag ratio by 3-5%, while the variable fidelity results are equal to the high-fidelity analysis results by algorithm definition.

2016

1. Adaptive Multifidelity Constraints Method for Efficient Multidisciplinary Missile Design Framework

   Nhu Van Nguyen, Maxim Tyan, Sunghyun Jin, and Jae-Woo Lee

   Journal of Spacecraft and Rockets, Jan 2016

   IF=0.716

   DOI
2. Investigations on stability and control characteristics of a CS-VLA certified aircraft using wind tunnel test data

   Nhu Van Nguyen, Maxim Tyan, Jae-Woo Lee, and Sangho Kim

   Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, Feb 2016

   Abs DOI

   The stability and control characteristics using a wind tunnel test data process are proposed and developed to investigate the stability and control characteristics of a CS-VLA certified aircraft and to comply with the CS-VLA subpart B at the preliminary design review (PDR) and critical design review (CDR) stage. The aerodynamic characteristics of a 20% scale model are provided and investigated with clean, rudder, aileron, elevator, and winglet effects. The Mach and Reynolds correction methods are proposed to correct the aerodynamics of the scale model for stability and control analysis to obtain more reliable and accurate results of the full-scale model. The aerodynamic inputs and moment of inertia (MOI) comparison between the PDR and CDR stage show good agreement in the trends of stability and control derivatives. The CDR analysis results with the corrected wind tunnel test data and accurate MOI are investigated with respect to the longitudinal and lateral stability, control, and handling qualities to comply with the CS-VLA 173, CS-VLA 177, and CS-VLA 181 for finalizing the configuration in the CDR stage.

3. Efficient stall compliance prediction method for trimmed very light aircraft with high-lift devices

   Nhu Van Nguyen, Daeyeon Lee, Maxim Tyan, Jae-Woo Lee, and Sangho Kim

   Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, May 2016

   SCI IF=0.653

   DOI
4. Enhanced multi-fidelity model for flight simulation using global exploration and the Kriging method

   Daeyeon Lee, Nhu Van Nguyen, Maxim Tyan, Heun Geun Chun, Sangho Kim, and Jae-Woo Lee

   Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, Apr 2016

   SCIE IF=0.653

   DOI

2015

1. A modified variable complexity modeling for efficient multidisciplinary aircraft conceptual design

   Nhu Van Nguyen, Maxim Tyan, and Jae-Woo Lee

   Optimization and Engineering, Jun 2015

   IF=0.9

   DOI
2. Improving variable-fidelity modelling by exploring global design space and radial basis function networks for aerofoil design

   Maxim Tyan, Nhu Van Nguyen, and Jae-Woo Lee

   Engineering Optimization, Jul 2015

   IF=1.38

   DOI
3. Possibility-based multidisciplinary optimisation for electric-powered unmanned aerial vehicle design

   Nhu Van Nguyen, Jae-Woo Lee, Maxim Tyan, and Daeyeon Lee

   The Aeronautical Journal, Nov 2015

   IF=0.537
4. Repetitively enhanced neural networks method for complex engineering design optimisation problems

   Nhu Van Nguyen, Jae-Woo Lee, Maxim Tyan, and Sangho Kim

   The Aeronautical Journal, Oct 2015

   IF=0.537

   DOI

2014

1. Investigations on Missile Configuration Aerodynamic Characteristics for Design Optimization

   Nhu-Van Nguyen, Maxim Tyan, Jae-Woo Lee, and Yung-Hwan Byun

   Transactions of the Japan Society for Aeronautical and Space Sciences, Oct 2014

   IF=0.338

2025

1. 하이브리드 전기 항공기 사이징에서의 전력-에너지 균형 요구 : 유상하중과 기술적 요소의 고려

   최용현, Zin Win Thu, Maxim Tyan, 정우석, and 이재우

   한국항공우주학회지, Apr 2025

   Publisher: 한국항공우주학회

   Abs

   최근 항공 산업에서 지속 가능성이 강조되는 가운데, 전기추진 항공기의 도입이 가속화되고 있으며, 이에 전기추진 시스템에 적합한 사이징 방법이 요구되고 있다. 본 연구에서는 항공기 임무 형상에 따라 배터리의 요구 전력과 동력을 균형적으로 분배함으로써, 기존의 단일 동력 분담률을 사용하는 방법들이 가졌던 과대 추정 문제를 해결하는 사이징 방법론을 제시하였다. 제시된 방법론들은 검증을 통해 약 10%의 오차율을 보이며 그 타당성을 입증하였다. 또한, 선행 연구로부터 도출된 Part 23급 수소연료전지 항공기와의 비교를 통해 하이브리드 시스템의 효용성을 확인하고자, 본 연구에서 제시한 사이징 방법론을 활용하여 미래 기술 수준에 따른 하이브리드 추진 시스템의 Case Study를 수행하였다. 나아가 인증 기준에서 제시하는 요구사항을 만족하기 위한 유상하중 Tradeoff를 수행한 결과, 동일 최대이륙중량 10,343kg에 대해 하이브리드 시스템에서는 약 255kg의 유상하중을 더 수용하며, 최대이륙중량 인증요건 8,618kg에 대해서는 115kg의 유상 하중 손실 감소를 확인하였다.

2. Comprehensive Modeling of Electric Propulsion System for High-fidelity eVTOL-AAM Flight Simulation

   LV Thang Nguyen, Donggyu Seong, Mohammad Irfan Alam, Maxim Tyan, and Jae-Woo Lee

   한국항공우주학회지, Mar 2025

   Publisher: 한국항공우주학회

   Abs

   최근 몇 년간, 미래 항공 모빌리티(Advanced Air Mobility, AAM)은 높은 인구 밀도의 도심 지녁을 위한 혁신적인 해결책으로 떠오르고 있으며, 일반적으로 전기 추진 수직 이착륙 (eVTOL) 항공기의 형태를 가진다. 이러한 eVTOL 항공기에 대한 수요가 증가함에 따라, 고정밀 비행 시뮬레이션의 필요성도 증가하고 있다. 이때, 전기 추진 시스템은 eVTOL 항공기의 비행 역학에서 핵심적인 요소 중 하나이다. 이에 본 연구에서는 eVTOL 항공기의 비행 시뮬레이션을 위한 전기 추진 시스템의 종합적인 모델을 개발하는 것을 목표로 한다. 이때, 이 모델은 전기 추진 시스템 구성 요소에 대한 상세한 수학적 표현과 항공기 비행 역학과의 상호작용을 포함한다. 전체 통합 시스템의 신뢰성은 축소형 프로토타입의 UAM 항공기를 대상으로 하여 지상 및 비행 시험 시나리오 사례 연구를 통행 평가된다. 시뮬레이션 결과와 실험 데이터 간의 일치도는 모델이 강건함을 입증하며, 향후 가상 비행 인증 기술 및 AAM 분야의 디지털 트윈 기술을 발전시키는데 크게 기여할 수 있다.

2021

1. Improved VFM Method for High Accuracy Flight Simulation

   Chiho Lee, Mukyeom Kim, Jae-Lyun Lee, Kwon-Su Jeon, Maxim Tyan, and Jae-Woo Lee

   Journal of the Korean Society for Aeronautical & Space Sciences, Sep 2021

   Abs DOI

   Recent progress in analysis and flight simulation methods enables wider use of a virtual certification and reduces number of certification flight tests. Aerodynamic database (AeroDB) is one of the most important components for the flight simulation. It is composed of aerodynamic coefficients at a range of flight conditions and control deflections. This paper proposes and efficient method for construction of AeroDB that combines Gaussian Process based Variable Fidelity Modeling with adaptive sampling algorithm. A case study of virtual certification of a F-16 fighter is presented. Four AeroDB were constructed using different number and distribution of high-fidelity data points. The constructed database is then used to simulate gliding, short pitch, and roll response. Compliance with certification regulations is then checked. The case study demonstrates that the proposed method can significantly reduce number of high-fidelity data points while maintaining high accuracy of the simulation.

2020

1. Flying-Wing Type UAV Design Optimization for Flight Stability Enhancement

   Dong Gyu Seong, Nadhie Juliawan, Maxim Tyan, Sangho Kim, and Jae-Woo Lee

   Journal of Korean Society of Aeronautical and Space Sciences, Sep 2020

   DOI

2019

1. Numerical Experience with Variable-fidelity Metamodeling for Aerodynamic Data Fusion Problems

   Vinh Pham, Mukyeom Kim, Maxim Tyan, and Jae-Woo Lee

   Journal of Defense Acquisition and Technology, Jun 2019

   DOI

2013

1. Flap Design Optimization for KLA-100 Aircraft in compliance with Airworthiness Certification

   Jinhwan Park, Maxim Tyan, Nhu Van Nguyen, Sangho Kim, and Jae-Woo Lee

   Journal of the Korean Society for Aeronautical & Space Sciences, Aug 2013

   Abs DOI

   High-lift devices have a major influence on takeoff, landing and stall performance of an aircraft. Therefore, a slotted flap design optimization process is proposed in this paper to obtain the most effective flap configuration from supported 2D flap configuration. Flap deflection, Gap and Overlap are considered as main contributors to flap lift increment. ANSYS Fluent 13.0.0® is used as aerodynamic analysis software that provides accurate solution at given flight conditions. Optimum configuration is obtained by Sequential Quadratic Programing (SQP) algorithm. Performance of the aircraft with optimized flap is estimated using Aircraft Design Synthesis Program (ADSP), the in-house performance analysis code. Obtained parameters such as takeoff, landing distance and stall speed met KAS-VLA airworthiness requirements.

2. UAV Performance Improvement using Integrated Analysis and Design Optimization Technology

   Jimin Kim, Nhu Van Nguyen, Jung-Il Shu, Maxim Tyan, and Jae-Woo Lee

   Journal of the Korean Society for Aviation and Aeronautics, Aug 2013

   DOI

2024

1. 다중 저정밀도 데이터셋을 통합한 다중 정밀도 공기역학 데이터 융합 장치 및 방법

   Jae-Woo Lee, Quang Vinh Pham, Tuan Nguyen, and Maxim Tyan

   Dec 2024

2022

1. 비행시험 데이터를 이용한 6 자유도 비행 시뮬레이션 정확도 향상 방법 및 장치

   LV Thang Nguyen, Maxim Tya, Jae-Woo Lee, and Kwonsu Jeon

   Jul 2022
2. Method and device for improving accuracy of six-degree-of-freedom flight simulation by using flight test data

   LV Thang Nguyen, Maxim Tyan, Jae-Woo Lee, and Kwon-Su Jeon

   Jul 2022

   Abs

   본 발명은 비행시험 데이터를 이용한 6 자유도 비행 시뮬레이션 정확도 향상 방법 및 장치에 관한 것으로, 6 자유도 비행 시뮬레이션 정확도 향상 방법은 비행 시뮬레이션 모델을 구축하는 단계, 종방향 기동 비행시험을 수행하여 비행시험 중에 수집되는 비행시험 데이터로 비행시험 데이터베이스를 구축하기 위한 비행시험 수행 단계, 상기 비행시험 데이터를 이용하여 상기 비행 시뮬레이션 모델의 정확도 향상을 위해 상기 시뮬레이션 모델의 매개변수를 조정하는 예비 모델 튜닝 단계, 공기역학 데이터베이스를 보정하는 공력 DB 보정 단계, 및 상기 비행시험 데이터를 이용한 시뮬레이션 검증을 수행하여 개선된 시뮬레이션 모델을 제공하는 비행시험 검증단계를 포함한다. 따라서, 항공기의 종방향 운동에서 비행 시뮬레이션 모델의 정확도를 향상시킬 수 있다.The present invention relates to a method and apparatus for improving the accuracy of 6-DOF flight simulation using flight test data. A flight test performing step for building a flight test database with the collected flight test data, a preliminary model tuning step of adjusting the parameters of the simulation model to improve the accuracy of the flight simulation model using the flight test data, aerodynamics Aerodynamic DB correction step of correcting the database, and a flight test verification step of providing an improved simulation model by performing simulation verification using the flight test data. Therefore, it is possible to improve the accuracy of the flight simulation model in the longitudinal motion of the aircraft.

3. 전기추진장치를 장착한 무인비행체의 고정밀 비행 시뮬레이션 장치 및 방법

   Maxim Tyan, LV Thang Nguyen, Aye Aye Maw, Gu Moon Jeong, Jae-Woo Lee, and Chiho Lee

   Nov 2022
4. 무인이동체를 위한 인공지능 기반의 경로 재계획 방법 및 장치

   Aye Aye Maw, Maxim Tyan, Jae-Woo Lee, and Kwonsu Jeon

   Aug 2022
5. 수소연료전지를 적용한 무인기 초기 설계를 위한 사이징 방법 및 장치

   Jae-Woo Lee, Jae-Hyun An, Maxim Tyan, Do Youn Kwon, and Kwonsu Jeon

   Jul 2022

2017

1. 강건 최적 설계 시스템, 방법 및 컴퓨터 판독 가능한 기록매체

   Jae-Woo Lee, Maxim Tyan, and Nhu Van Nguyen

   Oct 2017

2025

1. Transition Flight Trajectory Optimization for Tilt-Rotor Urban Air Mobility (UAM) Aircraft with a Box-Wing Configuration

   Ki-Jun Byeon, Zin Win Thu, LV Thang Nguyen, Maxim Tyan, and Jae-Woo Lee

   Jan 2025
2. Logical Development Framework for the Initial Concept of Eco-Friendly Advanced Air Mobility Aircraft

   Min Ji Kim, Maxim Tyan, and Jaewoo Lee

   In AIAA SCITECH 2025 Forum, Jan 2025

   DOI

2024

1. Enhancing Sizing Methodology for Hybrid Regional Air Mobility (RAM) with Distributed Electric Propulsion: Incorporating Uncertainties at the Early Design Stage

   Zin Win Thu, Mohammad Irfan Alam, Maxim Tyan, Jae-Woo Lee, and Keunseok Lee

   In , Jan 2024

2022

1. Enhanced Performance Prediction of Hydrogen Fuel Cell Powered eVTOL UAV

   Zin W. Thu, Jae-Hyun Ahn, Jae-Lyun Lee, Do-Youn Kwon, Yeon-Ju Choi, Woon-Jae Won, Maxim Tyan, and Jae-Woo Lee

   In AIAA AVIATION 2022 Forum, Jun 2022

   DOI
2. Development of Validation Strategy for High Precision Simulation Model of Multicopter UAV

   Thang L. Nguyen, Taeho Kwag, Chiho Lee, Maxim Tyan, and Jae-Woo Lee

   In AIAA AVIATION 2022 Forum, Jun 2022

   DOI
3. Development of Advanced Surrogated-based Data Fusion Approach for Aerodynamic Database Construction

   Vinh Pham, Chi-ho Lee, LV Thang Nguyen, Maxim Tyan, and Jae-Woo Lee

   In AIAA Aviation, Jun 2022
4. eVTOL 천이 비행을 위한 Tilt Corridor 도출 기법 연구

   Jeongseok Hyeon, Chiho Lee, Le Viet Thang Nguyen, Minseok Jang, Maxim Tyan, and Jae-Woo Lee

   In Proceedings of the Spring Conference of The Korean Society for Aeronautical and Space Sciences, Apr 2022
5. eVTOL 항공기의 착륙장치 지상하중해석 기법 연구

   Woon Jae Won, Wonkyong Kim, Maxim Tyan, and Jae-Woo Lee

   In Proceedings of the Spring Conference of The Korean Society for Aeronautical and Space Sciences, Apr 2022
6. SITL 인터페이스 기반 고정밀 eVTOL 가상 환경 구축

   Tae Ho Kwag, Le Viet Thang Nguyen, Maxim Tyan, and Jae-Woo Lee

   In Proceedings of the Spring Conference of The Korean Society for Aeronautical and Space Sciences, Apr 2022
7. eVTOL 성능향상을 위한 수소연료전지-배터리 하이브리드 추진 시스템 동력 분배 기법 연구

   Do Youn Kwon, Jae Lyun Lee, Zin Win Thu, Ahyun Choi, Maxim Tyan, and Jae-Woo Lee

   In Proceedings of the Spring Conference of The Korean Society for Aeronautical and Space Sciences, Apr 2022

2021

1. 25kg급 Lift+Thrust 수소연료전지 수직이착륙 무인기 사이징 기법 연구

   Jae Hyun An, Jae Lyun Lee, Maxim Tyan, and Jae-Woo Lee

   In , Jul 2021
2. Development of Image Processing Algorithms using GMM and Lucas-Kanade Method for Autonomous UAV obstacle detection

   Nan Lao Ywet, Dasom Kim, Aye Aye Maw, Maxim Tyan, and Jae-Woo Lee

   In , Jul 2021
3. 3D Optimal Trajectory Generation Based on iADA* Considering Aircraft Performance Constraints

   Zin Win Thu, Jae Hyun An, Jae Lyun Lee, Vinh Pham, Aye Aye Maw, Maxim Tyan, and Jae-Woo Lee

   In , Jul 2021
4. Multi-AI Agents for Real-time Mission Planning of Autonomous Unmanned Aerial Vehicle

   Aye Aye Maw, Zin Win Thu, Dasom Kim, Maxim Tyan, and Jae-Woo Lee

   In , Apr 2021

   Abs

   This paper contributes to the growing research of the autonomous unmanned aerial vehicle system concerned with real-time mission planning. With autonomous technologies getting advanced and improved every day, the vehicle’s high intelligence is getting lots of interest for many different applications. This paper addressed the real-time mission planning problem of generating an optimal path to maneuverability and obstacle avoidance constraints, and replanning the path when at risk of obstacles, especially in unknown and dynamic environments. Additionally, the system also including the monitoring agent to check and monitor the vehicle’s status in the real-time form. To achieve this task, a real-time mission planning system with a multi Artificial Intelligence agent-based approach is proposed. The proposed approach for real-time mission planner runs in the popular simulator, AirSim. Using this approach, the real-time mission planning system, including global path planning and replanning, system monitoring, and the local path planner while avoiding the real-time system’s obstacle is implemented and demonstrated.

5. 정확한 공력 데이터베이스를 위한 SpaceMapping과 VFM 기반 다정밀도 외삽 기법 연구

   Yeon-Ju Choi, Chi-Ho Lee, Vinh Pham Quang, Maxim Tyan, and Jae-Woo Lee

   In , Jun 2021
6. 풍동 시험을 통한 전기 추진시스템 해석 정확도 향상을 위한 성능 파라미터 예측 기법 연구

   Jae-Lyun Lee, Do-Youn Kwon, Maxim Tyan, and Jae-Woo Lee

   In , Jun 2021
7. Intelligent Mission Management for Urban Air Mobility using MDP and RL

   Aye Aye Maw, Hyeon Jun Lee, JunSeok Lee, Maxim Tyan, and Jae-Woo Lee

   In Asia-Pacific International Symposium on Aerospace Technology, Nov 2021
8. Robust Real-time Object Detection and Tracking Method using Camera Images for Autonomous UAV Mission

   Nan Lao Ywet, Dasom Kim, Aye Aye Maw, Maxim Tyan, and Jae-Woo Lee

   In Korean Society for Aeronautical and Space Sciences, Nov 2021
9. 저속 및 순항 모드를 고려한 공력특성 향상을 위한 eVTOL 항공기 형상 최적화 기법 개발

   Minji Kim, Jaehyun An, Maxim Tyan, and Jae-Woo Lee

   In Korean Society for Aeronautical and Space Sciences, Nov 2021
10. 감항 기준을 고려한 eVTOL 항공기의 비행 하중 해석 기법 연구

    Wonkyong Kim, Maxim Tyan, Woon Jae Won, and Jae-Woo Lee

    In Korean Society for Aeronautical and Space Sciences, Nov 2021
11. eVTOL UAV 성능 예측을 위한 수소연료전지 성능해석 기법 연구

    Do Youn Kwon, Zin Win Thu, Jae Lyun Lee, Maxim Tyan, Jae-Woo Lee, Sewan Park, and Jeon Dae Lee

    In Korean Society for Aeronautical and Space Sciences, Nov 2021

2020

1. Digital Twin System for Future Urban Air Mobility. Technology Overview.

   Maxim Tyan, Aye Aye Maw, Kwon-su Jeon, Mina Jang, and Jae-Woo Lee

   In Korean Society for Aeronautical and Space Sciences, Nov 2020
2. eVTOL 비행체 추진시스템 모델링 구축 및 검증을 위한 실험적 연구

   Le Viet Thang Nguyen, Tae Ho Kwag, Gumoon Jeong, Maxim Tyan, and Jae-Woo Lee

   In 한국항공우주학회 2020 추계학술대회 논문집, Nov 2020
3. Flight test maneuvers design for improvement and validation of multicopter 6DOF simulator

   LV Thang Nguyen, Gu Moon Jeong, Maxim Tyan, and Jae-Woo Lee

   In The Past, Present and Future of Flight Simulation - Technology, Training and Regulatory Challenges, Jun 2020
4. Experimental Setup for Construction and Validation of Propulsion System Modeling for eVTOL Vehicle

   LV Thang Nguyen, Tae Ho Kwag, Gu Moon Jeon, Maxim Tyan, and Jae-Woo Lee

   In 한국항공우주학회 2020 추계학술대회 논문집, Nov 2020
5. 전익기형 UAV의 Tilt-rotor 설계 및 비행시험을 통한 검증

   Chiho Lee, Maxim Tyan, and Jae-Woo Lee

   In 한국항공우주학회 2020 추계학술대회 논문집, Nov 2020
6. 감항인증기술기준 연구를 통한 전익기형 수직이착륙 무인기 비행하중해석

   Wonkyung Kim, Maxim Tyan, and Jae-Woo Lee

   In , Nov 2020
7. Human factor and pilot performance quantitative analysis for flight training effectiveness in VR simulation environment

   Gu Moon Jeong, Young Jae Lee, Tae Ho Kwag, Maxim Tyan, and Jae-Woo Lee

   In The Past, Present and Future of Flight Simulation - Technology, Training and Regulatory Challenges, Jun 2020
8. 수소연료전지 도심항공교통수단의 성능운용분석 연구 (Performance Operation Analysis Study on Hydrogen Fuel cell Urban Air Mobility)

   Jaehyun An, Zin Win Thu, Jae Lyun Lee, Youngjae Lee, Jae Seon Min, Maxim Tyan, Seung Hyeog Nah, and Jae-Woo Lee

   In 한국항공우주학회 2020 추계학술대회 논문집, Nov 2020
9. Multi-fidelity Metamodel Network Method for Complex Engineering Data Processing Problems in Support of Accurate Flight Simulation

   Vinh Pham, LV Thang Nguyen, Nadhie Juliawan, Maxim Tyan, Jae-Woo Lee, and Sangho Kim

   In 한국항공우주학회 2020 춘계학술대회 논문집, Apr 2020
10. Configuration Sizing and Optimization of a 25kg VTOL-UAV powered by a Hydrogen Fuel Cell

    Maxim Tyan, Seong Dong-Gyu, Jae Hyun Anh, Vinh Pham, and Jae-Woo Lee

    In Asian Congress of Structural and Multidisciplinary Optimization 2020 (ACSMO2020), Oct 2020
11. Performance Analysis Code Development for Preliminary Design of Hydrogen Powered Vertical Takeoff and Landing UAV

    Win Thu Zin, Jae Lyun Lee, Quang Vinh Pham, Dong Gyu Seong, Jae Hyun An, Maxim Tyan, and Jae-Woo Lee

    In Korean Society for Aeronautical and Space Sciences, Nov 2020
12. Repetitively Enhanced Multi-fidelity Modelling Network Method for Complex Engineering Data Processing Problems in Support of Accurate Flight Simulation

    Vinh Pham, LV Thang Nguyen, Nadhie Juliawan, Maxim Tyan, Jae-Woo Lee, and Sangho Kim

    In Proceedings of the Spring Conference of The Korean Society for Aeronautical and Space SciencesProceedings of the Spring Conference of The Korean Society for Aeronautical and Space Sciences, Apr 2020
13. Development of Advanced Data Fusion Techniques for Data Processing in Support of High-fidelity Flight Simulation

    Vinh Pham, Mukyeom Kim, Maxim Tyan, and Jae-Woo Lee

    In Proceedings of the Asian Congress of Structural and Multidisciplinary Optimization, May 2020

2019

1. Development of Flight Dynamics Model for Wearable Display Device Drone Flight Simulator

   Maxim Tyan, Aye Aye Maw, LV Thang Nguyen, Gumoon Jeong, and Jae-Woo Lee

   In 2019 19th International Conference on Control, Automation and Systems, Oct 2019
2. 전익기형 무인기의 안정성 확보를 위한 형상 최적화 (Design Optimization of a Flying Wing UAV to Secure Aicrat Stability)

   Dong-Gyu Seong, Maxim Tyan, and Jae-Woo Lee

   In KSAS 2019 Fall Conference, Nov 2019
3. Fighter Aircraft Virtual Flight Test and Certification using Multi-Fidelity Aerodynamic Databases

   LV Thang Nguyen, Maxim Tyan, Gumoon Jeong, and Jae-Woo Lee

   In KSAS 2019 Fall Conference, Nov 2019
4. Flying-Wing Type UAV Design Optimization By Incorporating Flight Stability Constraints

   Dong-Gyu Seong, Maxim Tyan, Sangho Kim, and Jae-Woo Lee

   In Asia Pacific International Symposium on Aerospace Technology, Dec 2019
5. Data Fusion Technique for Noisy and Multi-fidelity Data Processing in Support of Accurate Flight Simulation

   Vinh Pham, Mukyeom Kim, Nadhie Juliawan, Maxim Tyan, Jae-Woo Lee, and Sangho Kim

   In KSAS 2019 Fall Conference, Nov 2019
6. Improved Aerodynamic Data Fusion Techniques using Local Fidelity Method for Accurate Flight Simulation

   Vinh Pham, Mukyeom Kim, LV Thang Nguyen, Maxim Tyan, and Jae-Woo Lee

   In 2019 KSAS Spring Conference, Apr 2019
7. 축소모델의 비행시험을 통한 1인승 PAV 실기체 동안정성 예측 연구

   Jaehyun An, Jae-Woo Lee, Maxim Tyan, and Dong-Gyu Seong

   In , Apr 2019
8. Data Fusion Method for Constructing Fighter Aircraft Aerodynamic Database Using Variable Fidelity and Space Mapping Techniques

   Mukyeom Kim, Maxim Tyan, Nadhie Juliawan, Sangho Kim, Joon Chung, and Jae-Woo Lee

   In 8th European Conference for Aeronautics and Space Sciences, Jul 2019
9. Development of Flight Mission Planner using Intelligent Anytime Planning and Replanning Algorithm for UAV Operation

   Aye Aye Maw, Maxim Tyan, and Jae-Woo Lee

   In International Conference on Computer Applications, Feb 2019
10. Dynamic Obstacle Avoidance using Deep Reinforcement Learning Network for Autonomous UAV

    Aye Aye Maw, Maxim Tyan, and Jae-Woo Lee

    In KSAS 2019 Fall Conference, Feb 2019

2018

1. A Data Fusion Method using Combined Variable Fidelity Modeling and Space Mapping for Aerodynamic Database

   Mukyeom Kim, Maxim Tyan, Vinh Pham, Nadhie Juliawan, Sangho Kim, and Jae-Woo Lee

   In The Asia-Pacific International Symposium on Aerospace Technology, Oct 2018
2. A Deep Learning Based Airfoil Design Algorithm Imitate Trial and Error Method

   Cheol Kyun Choi, Aye Aye Maw, Mukyeom Kim, Maxim Tyan, and Jae-Woo Lee

   In The Asian Congress of Structural and Multidisciplinary Optimization, May 2018
3. Development of Advanced Aerodynamic Data Fusion Techniques for Flight Simulation Database Construction

   Maxim Tyan, Mukyeom Kim, Vinh Pham, Cheol Kyun Choi, Nguyen Le Viet Thang, and Jae-Woo Lee

   In AIAA AVIATION, Jun 2018
4. A Multi-level Kriging Approach for Variable Fidelity Aerodynamic Database Construction

   Vinh Pham, Mukyeom Kim, Maxim Tyan, and Jae-Woo Lee

   In 2018 KSAS Fall Conference, Nov 2018

2016

1. UAV Mapping Mission Design Based on Operation Specific Requirements

   Aye Aye Maw, Maxim Tyan, LV Thang Nguyen, and Jae-Woo Lee

   In Korean Society for Aeronautical and Space Sciences Spring Conference, Apr 2016
2. Development of Adaptive Sequential Sampling Algorithm for Efficient Generation of Aerodynamic Tables

   Maxim Tyan, Nhu Van Nguyen, and Jae-Woo Lee

   In Asian Congress of Structural and Multidisciplinary Optimization 2016, May 2016
3. Robust Optimization of Transonic Airfoil for Generic Fighter Aircraft using Global Variable Fidelity Modeling

   Maxim Tyan, Nhu Van Nguyen, and Jae-Woo Lee

   In 16th AIAA Aviation Technology, Integration, and Operations Conference, May 2016

   DOI
4. Efficient Framework for Missile Design and 6DoF Simulation using Multi-fidelity Analysis and Data Fusion

   Nhu Van Nguyen, Maxim Tyan, and Jae-Woo Lee

   In 17th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference, Jun 2016

   DOI

2015

1. A Flying Wing UCAV Design Optimization Using Global Variable Fidelity Modeling

   Maxim Tyan, Nhu Van Nguyen, and Jae-Woo Lee

   In 11th World Congress on Structural and Multidisciplinary Optimization, Jun 2015

2014

1. Flight Simulation of Guided Vehicle with Improved Aerodynamic Database Using Multifidelity Analysis

   Hyunggeun Chun, Seongjun Cho, Daeyeon Lee, Maxim Tyan, and Jaewoo Lee

   In The Tenth Asian Computational Fluid Dynamics Conference (ACFD10), Jun 2014
2. The Multidisciplinary Design Optimization Process and Design Framework Development for the Unmanned Gliding Vehicle

   Kwon-su Jeon, Maxim Tyan, Sung Hyun Jin, Seoung Jun Cho, and Jae-Woo Lee

   In 2014 Asia-Pacific International Symposium on Aerospace Technology, APISAT2014, Jun 2014
3. Enhanced Multi Fidelity Analysis Method Using Global Exploration and Kriging

   Daeyeon Lee, Hyunggeun Chun, Maxim Tyan, Seoung Jun Cho, Jae-Woo Lee, Hwajin Nah, and Jung-Jae Suh

   In 2014 KSAS Spring Conference, Jun 2014
4. Repetitively Enhanced Neural Networks Method for a Long Endurance UAV Airfoil Design Optimization

   Nhu Van Nguyen, Maxim Tyan, and Jae-Woo Lee

   In CFD conference, May 2014
5. Tailless UAV design using variable fidelity method with global design search and radial basis functions network

   Maxim Tyan, Nhu Van Nguyen, Jae-Woo Lee, Sangho Kim, and Seung Hyeog Nah

   In EngOpt2014, 4th international conference on engineering optimization, Lisboa, Portugal, May 2014
6. Unmanned flying wing aircraft design using variable fidelity modelling with global design space exploration

   Maxim Tyan, Nhu Van Nguyen, Jae-Woo Lee, Sangho Kim, Seung Hyeog Nah, and Jo-Won Chang

   In Innovation 2014 conference, Tashkent, Uzbekistan, May 2014
7. Improving Variable-Fidelity Modelling by Exploring Global Design Space and RBF Networks for Airfoil Design

   Maxim Tyan, Nhu Van Nguyen, and Jae-Woo Lee

   In 8th China-Japan-Korea Joint Symposium on Optimization of Structural and Mechanical Systems, Gyeongju, Korea, May 2014

2013

1. Possibility based small aircraft design optimization using database driven uncertainty approach

   Hsu Myat Naing, Daniel Neufeld, Nguyen Nhu Van, Maxim Tyan, Jae-Woo Lee, and Sangho Kim

   In 2013 KSAS Spring Conference, Gangwon-do, Rep. of Korea, May 2013
2. Possibility Based Multidisciplinary Optimization for Electric-Powered Unmanned Aerial Vehicle Design

   Nhu Van Nguyen, Jae-Woo Lee, Dae-Yeon Lee, Maxim Tyan, and Seung Hyeog Nah

   In ADEX Air show 2013, Kintex, Seoul, Korea, May 2013
3. A Multidisciplinary Robust Optimization Framework for UAV Conceptual Design

   Nhu Van Nguyen, Maxim Tyan, Hyeong-Uk Park, Sangho Kim, and Jae-Woo Lee

   In WCSMO-10 Conference, Orlando, Florida, May 2013
4. Flap Design optimization for KLA100 aircraft in compliance with airworthiness certification

   Jinhwan Park, Maxim Tyan, Nhu Van Nguyen, Sangho Kim, and Jae-Woo Lee

   In 2013 KSAS Spring Conference, Gangwon-do, Rep. of Korea, May 2013
5. Design Optimization of Subsonic Airfoil and Slotted Flap Shape Using Multi-Fidelity Aerodynamic Analysis

   Maxim Tyan, Jin-hwan Park, Sangho Kim, and Jaewoo Lee

   In 21st AIAA Computational Fluid Dynamics Conference, Jun 2013

   DOI
6. Multi-element airfoil design optimization process using multi-fidelity aerodynamic analysis

   Maxim Tyan, Jinhwan Park, Sangho Kim, and Jae-Woo Lee

   In Korean Society for Computational Fluid Engineering, Jun 2013
7. Integrated Analysis Program Development for Light Aircraft Preliminary Design Stage

   Maxim Tyan, Daniel Neufeld, Jae-Woo Lee, and Sangho Kim

   In 2013 KSAS Spring Conference, Gangwon-do, Rep. of Korea, Jun 2013
8. Flap Design Optimization for Very Light Aircraft in compliance with Airworthiness Certification

   Jin-hwan Park, Sangho Kim, Nhu Van Nguyen, Maxim Tyan, and Jaewoo Lee

   In 21st AIAA Computational Fluid Dynamics Conference, Jun 2013

   DOI
9. Light aircraft high-lift device design optimization in compliance with certification regulations

   Jinhwan Park, Maxim Tyan, Nhu Van Nguyen, Sangho Kim, and Jae-Woo Lee

   In The 50th International Conference on Law and Policy in Air and Space Field, Jun 2013

2012

1. Integrated Design Certification System Development for Light Aircraft

   Im Kwon Kim, Tun Lwin, Eung Young Kim, Nhu Van Nguyen, Maxim Tyan, Jung Il Shu, and Jae-Woo Lee

   In KSAA 2012 Conference, Jun 2012
2. Performance Enhancement of Unmanned Aerial Vehicle Using an Electric Propulsion

   Jimin Kim, Nhu Van Nguyen, Maxim Tyan, Jae-Woo Lee, Sangho Kim, Yung-Hwan Byun, and Seung-Hyeog Nah

   In Asian Joint Conference on Propulsion and Power, Xian, China, Jun 2012
3. Flap Design Optimization for VLA by Incorporating Airworthiness Constraints

   Jinhwan Park, Sangho Kim, Jungwon Yoon, Nhu Van Nguyen, Maxim Tyan, and Jae-Woo Lee

   In 7th China-Japan-Korea Joint Symposium on Optimization of Structural and Mechanical Systems, Huangshan, China, Jun 2012
4. Development of Design-Certification-Analysis Integration Software for Small Aircraft (CADIS-SA)

   Jae-Woo Lee, Nhu Van Nguyen, Tun Lwin, Maxim Tyan, Seungbin Park, Sangho Kim, and Im Kwon Kim

   In KSAS 2012 Fall Conference, Jun 2012
5. Subsonic Airfoil and Flap Hybrid Optimization Using Multi-Fidelity Aerodynamic Analysis

   Maxim Tyan, Jin-hwan Park, Sangho Kim, and Jaewoo Lee

   In 12th AIAA Aviation Technology, Integration, and Operations (ATIO) Conference and 14th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference, Jun 2012

   DOI
6. Aircraft Airfoil and Flap Optimization Using Multi-Fidelity Aerodynamic Analysis

   Maxim Tyan, Jinhwan Park, Nhu-Van Nguyen, Daniel Neufeld, Sangho Kim, and Jae-Woo Lee

   In 12th AIAA ATIO Conference, Indianapolis, Indiana, Jun 2012

2011

1. Light Aircraft Parametric Configuration Design

   Maxim Tyan, Abdulaziz Azamatov, Jae-Woo Lee, Sangho Kim, and Yung-Hwan Byun

   In Innovation 2011 conference, Jun 2011
2. Light Aircraft Configuration Development Using Advanced Design Methods

   Maxim Tyan, Sangho Kim, Jae-Woo Lee, Soo-Hyung Park, and Young-Il Jang

   In 2011 KSAS Fall Conference, Jejudo, Rep. of Korea, Jun 2011
3. Parametric Configuration Model for Light Aircraft

   Maxim Tyan, Abdulaziz Azamatov, Jae-Woo Lee, Sangho Kim, and Yung-Hwan Byun

   In 2011 KSAF Spring Conference, Jun 2011

2010

1. Multidisciplinary Regional Jet Aircraft Design Optimization Using Advanced Variable Complexity Techniques

   Nhu Van Nguyen, Maxim Tyan, Seok-Min Choi, Jong-Mu Sur, Jae-Woo Lee, Sangho Kim, and Yung-Hwan Byun

   In 13th AIAA/ISSMO Multidisciplinary Analysis Optimization Conference, Jun 2010

   DOI