• Title/Summary/Keyword: aircraft conceptual design

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A Tailless UAV Multidisciplinary Design Optimization Using Global Variable Fidelity Modeling

  • Tyan, Maxim;Nguyen, Nhu Van;Lee, Jae-Woo
    • International Journal of Aeronautical and Space Sciences
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    • v.18 no.4
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    • pp.662-674
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    • 2017
  • 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.

Shear Flow Analysis of Aircraft Composite Wing Structure (항공기 복합재 날개구조 전단흐름 해석)

  • Choi Ik-Hyeon;Kim Seong-Chan;Kim Seong-Jun
    • Proceedings of the Korean Society For Composite Materials Conference
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    • 2004.04a
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    • pp.75-78
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    • 2004
  • Traditionally aluminum alloy have been used in manufacturing of aircraft structures, and semi-monocoque structural concept have been mainly applied in structural design of fuselage and wing. However, recently monocoque structural concept is applied in many small-size aircraft structures manufactured with composite materials. In such case appling monocoque structural concept, in initial conceptual design stage on wing, it is not easy to analyze shear flow using classical shear flow analytical method because composite skin structure can support span-wise tension/compression stress as well as sectional shear stress. In this study, an extended shear-flow analytical method to apply to composite monocoque structural concept was developed through extending the classical shear-flow analytical method.

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SNU Human Powered Aircraft Design and Manufacturing (서울대학교 인간동력항공기의 설계 및 제작)

  • Eun, Won-Jong;Kim, Jung-Heon;Park, Seong-Woo;Kang, Jung-Pyo;Kim, Tae-Hwan;Park, Jae-Hyun;Han, Yoo-Ri;Lee, Da-Woon;Hong, Jong-Hwa;Lee, Yoon-Hyuk;Choi, Han-Seul;Park, Ji-Eun;Park, Joong-Hyun;Lee, Woo-Hee;Jang, Bum-Chan;Shin, Sang-Joon
    • Aerospace Engineering and Technology
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    • v.12 no.2
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    • pp.230-240
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    • 2013
  • Human powered aircraft: the aim is to fly only by human power, features many challenging issues. Contrary to the general aircraft operated by an engine, human powered aircraft, that manoeuvres by lower power, requires additional consideration about weight, material, aerodynamical and structural analysis. Since this aircraft flies at a low speed, low Reynolds number flight will need to be taken into account. In this paper, SNU (Seoul National University) Human Powered Aircraft was designed by comparing it with the existing human power aircrafts, as well as by using theoretical analysis that obtains the design parameters. Also, this paper discuss about the manufacturing process using composite material for real human powered aircraft.

The Overview of the Design and Development Process of the Indigenous Korean Utility Helicopter (KUH) (한국형기동헬기(KUH) 설계개발과정 개관)

  • Yoon, Heekweon;Oh, Sangchul;Jeong, Sangwon;Yang, Junho
    • Journal of Aerospace System Engineering
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    • v.2 no.3
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    • pp.29-32
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    • 2008
  • The overview of KUH design and development process is presented according to Buede's systems and development "vee" model. The system decomposition and integration activities exemplify KUH specification tree, design maturity and analysis according to design stage(conceptual, preliminary, and detail design), scheduled work breakdown structure, qualification test, ground test, and flight test. This process can be applied to the development of a new aircraft.

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Conceptual design of hybrid electric vertical take-off and landing (eVTOL) aircraft with a liquid hydrogen fuel tank

  • Kim, Jinwook;Kwon, Dohoon;Jeong, Sangkwon
    • Progress in Superconductivity and Cryogenics
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    • v.24 no.2
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    • pp.27-38
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    • 2022
  • Urban air mobility (UAM) has recently attracted lots of attention as a solution to urban centralization and global warming. Electric vertical take-off and landing (eVTOL) is a concept that emerges as one of the promising and clean technologies for UAM. There are two difficult challenges for eVTOL aircraft to solve. One is how to improve the weight efficiency of aircraft, and the other is how to complete long-range missions for UAM's flight scenarios. To approach these challenges, we propose a consolidated concept design of battery-fuel cell hybrid tiltrotor aircraft with a liquid hydrogen (LH2) fuel tank. The efficiency of a battery-fuel cell hybrid powertrain system on the designed eVTOL aircraft is compared to that of a battery-only powertrain system. This paper shows how much payload can increase and the flight scenario can be improved by hybridizing the battery and fuel cell and presenting a detailed concept of a cryogenic storage tank for LH2.

Probabilistic Load Analysis for Tailplane Considering Uncertainties in Design Variables (설계변수의 불확실성을 고려한 미익 하중의 확률론적 해석)

  • Choi, Yong-Joon;Kim, In-Gul;Lee, Seok-Je
    • Journal of the Korea Institute of Military Science and Technology
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    • v.13 no.6
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    • pp.1043-1050
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    • 2010
  • This paper examined the probabilistic load analysis for the tailplane during pitching maneuvering in the conceptual aircraft design phase. The flight load analysis based on the probabilistic distribution of design variables are compared with the results of the deterministic analysis. Two forms of variable distribution are used in this paper. One is standard normal distribution, the other distribution is calculated from the results of short-period longitudinal equation of aircraft motion. The influence of the distribution parameter on the probabilistic load analysis was investigated and the significant design variables that have an impact on the mean and variance of probabilistic load were identified. The comparison indicates that probabilistic load analysis provides more reliable probabilistic load distribution for the structural design than the traditional deterministic analysis.

Initial Sizing of General Aviation Aircraft Propelled by Electric Propulsion system (전기로 추진되는 일반 프로펠러 항공기의 초기 사이징)

  • Han, Hye-Sun;Shin, Kyo-Sic;Park, Hong-Ju;Hwang, Ho-Yon;Nam, Taewoo
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.41 no.5
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    • pp.391-403
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    • 2013
  • Propeller aircraft propelled by an electric propulsion system is gaining a renewed interest because of ever-increasing environmental concern on harmful emissions emitted from conventional jet engines and national energy security. Traditional aircraft sizing methods are not readily applicable to electric propulsion aircraft that utilize a variety of alternative energy sources and power generation systems. This study showcases an electric propulsion aircraft sizing exercise based on a generalized, power based sizing method. A general aviation aircraft is propelled by an electric propulsion system that comprises of a propeller, a high temperature super conducting motor, a Proton Exchange Membrance(PEM) fuel cell system fuelled with hydrogen, and power conditioning equipment. In order to assess the impact of technology progression, aircraft sizing was conducted for two different sets of technology assumptions for electric components, and the results were compared with conventional baseline aircraft.

A Study on Short-Take-Off and Vertical Landing (STOVL) Performance Evaluation of a Light Aircraft Carrier and a Consistent Analysis of Safe Operating Envelope (SOE) (경항공모함 이·착함 성능평가 및 안전임무 수행범주 일관 해석 연구)

  • Sa Young Hong;Dong-Min Park;Jae Hwan Jung;Min-Guk Seo;Seok-Kyu Cho
    • Journal of the Society of Naval Architects of Korea
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    • v.61 no.2
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    • pp.125-134
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    • 2024
  • The Safe Operating Envelope (SOE) combined with Short-Take-Off and Vertical Landing (STOVL) performance is an essential consideration of a light aircraft carrier for design of hull shape with excellent seakeeping performance in terms of naval air operations as well as traditional naval ship missions such as Transit and Patrol (TAP), and Replenishment at Sea (RAS) and so on. A variety of procedures are systematically combined to determine SOE considering rather complicated missions associated with operation of aircraft onboard. The evaluation of take-off and landing safety missions onboard should consider wind effect on deck and severer seakeeping indices and standards compared with conventional naval ships. In order to support take-off and landing missions, various support activities of the crews are required. So, additional evaluation is needed for indicators such as MSI(Motion sickness Index) and MII(Motion Induced Interruptions), which are quantitative indicators of work ability that appear as a result of motion response. In this study, a standard procedure is developed including the seaworthiness performance indicators, standards, and evaluation procedures that should be considered during design of STOVL aircraft carrier. Analysis results are discussed in terns of air-wake on deck as well as seakeeping indices associated with design parameter changes in view of conceptual design of a light aircraft carrier.

An Experimental Study on High Angle of Attack Static Stability Analysis For the Aerodynamic Design of Canard Type High Maneuver Aircraft (카나드 형상 고시동 항공기 공력설계를 우한 높은 받음각 정적 안정성 분석 실험 연구)

  • Chung, In-Jae
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.35 no.7
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    • pp.575-580
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    • 2007
  • During the conceptual design phase of a canard type high maneuverable aircraft, the low speed small scale wind tunnel test was conducted to investigate the high angle-of-attack static stability of the aircraft. In this study, 1/50th scale generic canard-body-wing model was used for the small scale wind tunnel test. For the analysis of static stability including high angle-of-attack nonlinear characteristics, the vertical tail effects were studied due to canard deflections. In addition, the nose chine effects were studied at high angle-of-attack. Based on the results obtained from the experimental study, the configuration change effects for canard type aircraft on high angle-of-attack static stability have been able to analyze.

Conceptual design and sensitivity analysis of a tilt + stopped rotor type eVTOL using motor weight estimation formula and iterative design (모터중량 추정식과 반복 설계를 통한 틸트+정지로터형 eVTOL 개념설계 및 민감도 분석)

  • Ju-heon Lee;Taejong Kim;Seo-yoon Jang;Hui-su Jo;Ho-Yon Hwang
    • Journal of Advanced Navigation Technology
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    • v.27 no.1
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    • pp.77-95
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    • 2023
  • In this study, the conceptual design of a tilt + stopped rotor type electric vertical take-off and landing (eVTOL) aircraft was performed using design iteration. Based on Hyundai Motor's S-A1, the mission profile was defined using the concept of urban air mobility (UAM), and configuration design and aerodynamic analysis were performed using OpenVSP and XFLR5 software. After estimating the required power for the designed eVTOL, the required performance of the battery and the maximum take-off weight (MTOW) were calculated. . It was iteratively calculated using Microsoft Excel and Visual Basic Application, and a new electric motor weight estimation formula was derived. Also, the sensitivity analyses of each design variables of an eVTOL was performed using the automated program.