• Title/Summary/Keyword: 항공기 형상

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A Study on Aircraft Flight Stability of T-50 Control Surface Reconfiguration Mode in PA Configuration (T-50 착륙외장 형상에서 조종면 형상 재구성 모드의 항공기 비행)

  • Kim, Jong-Seop
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.34 no.3
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    • pp.93-100
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    • 2006
  • Modern versions of supersonic jet fighter aircraft using a digital flight-by-wire flight control system design utilizes a control surface reconfiguration in order to guarantee the aircraft flight stability when a control surface is failed. The T-50 flight control laws are designed such that the surface reconfiguration mode controls the aircraft using non-failed control surfaces when one of the control surfaces is failed. In this paper, linear analysis and HQS(Handling Quality Simulator) pilot simulations are performed to analyze the flight stability and handling quality when the surface reconfiguration mode is engaged for aircraft landing configuration. It is found that the aircraft flight stability and handling quality is satisfied to level 1 requirements when the T-50 flight control law is changed to the surface reconfiguration mode.

Configuration Management System for Multi-Component Development (다품종부품 개발을 위한 형상관리 체계)

  • Kim, Sung-Chan;Oh, Hae-Soon;Lee, Sang-Wook
    • Proceedings of the KAIS Fall Conference
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    • 2011.12b
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    • pp.499-502
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    • 2011
  • 중형급 회전익 항공기는 약 5,000여종의 주요기능 부품이 사용된다. 이들 주요 기능부품은 항공기에 장착되기 위해 최적화설계로 목표중량을 달성하고, 요구성능을 상회하여야 한다. 따라서 항공기 기능부품은 개발비를 제외하고도, 동종의 자동차 부품에 비해 약 100배 이상의 양산 단가 구조과 막대한 개발비가 소요된다. 이와 같은 구성품 개발에 있어 개발비를 절감하는 기술관리 수단중 하나가 형상관리이며, 형상관리 체계의 수립은 사업의 성패에 중요요인으로 작용하고, 군사규격에 의거 항공분야 개발사업의 형상관리체계 수립이 요구된다. 본 연구에서는 다양한 민군겸용 구성품 국산화 개발에 적합한 형상관리 체계를 제안하고, 제안된 형상관리 체제를 구축 운용하여, 성공적인 민군겸용 구성품 형상관리가 수행되었음을 확인하였다.

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Aircraft configuration selection method using the airworthiness certification and the decision making process (항공안전 규정 및 의사결정모델을 이용한 항공기 형상선정기법 연구)

  • Yoon, Jung-Won;Bae, Bo-Young;Lee, Jae-Woo;Byun, Yung-Hwan
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.38 no.5
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    • pp.467-476
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    • 2010
  • For the very light jet aircraft design, the design baseline configuration has been selected using the logical decision making process, and the design optimization problem is formulated by considering the airworthiness regulations as design constraints. Airworthiness regulations are the minimum requirements for the safe aircraft flight and must be considered from the conceptual design stage. After carefully selecting the airworthiness constraints and the user specified requirements, a series of design making models including the affinity diagram, nested column diagram, quality function deployment (QFD), Pugh concept selection matrix, are used to find and evaluate alternative configuration baselines. From the feasible design space searching process, the best altenative design, which satisfies the airworthiness constraints while excluding the user subjective decisions as much as possible, has been successfully derived.

An Experimental Study of Fuselage Drag and Stability Characteristics of a Helicopter Configuration (회전익 항공기 형상의 기체공력 특성에 관한 실험적 연구)

  • Oh, Se-Yoon;Park, Keum-Yong;Lee, Jong-Geon;Ahn, Seung-Ki
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.33 no.9
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    • pp.9-15
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    • 2005
  • This paper describes the test carried out on an experimental study of fuselage drag and stability characteristics of a helicopter configuration and the test techniques developed for the testing and the lessons learned in the Agency for Defense Development Low Speed Wind Tunnel(ADD-LSWT). The main objective of this test is to determine the drag and stability characteristics of helicopter configurations according to the various configuration changes. The fuselage model with a highly modular structure is a representation of 1:8 scale of the external contour of the conceptual design helicopter configuration with rotating main rotor hub including blade stubs capable of rotating up to 500 rpm. The test results are compared with the available similar data and fair to good agreement is obtained.

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.

전진익 소형기의 전산유동해석

  • Choi, Seong-Wook;Kim, Eung-Tai
    • Aerospace Engineering and Technology
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    • v.1 no.2
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    • pp.1-10
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    • 2002
  • Flow computations around forward sweep wing small aircraft have been conducted in this study. The main-wing of the forward-wing small aircraft is composed of two planforms: the inboard wing section with backward sweep angle which is known as strake and the outboard wing section with forward sweep angle. The geometrical discontinuity or kink generated by the combination of these two different planforms requires detailed flow analysis around wing. Four different solvers were used to calculate aerodynamic data and the accuracy of each method is examined. For the convenience of grid generation over the aircraft geometry, the overset grid method was applied. Through this calculation, the basic aerodynamic data of the forward-wing aircraft were provided and the aerodynamic characteristics of the wing is expounded.

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A Study on the Cause and Improvement of Crack in the Installing Structure of the Bulkhead of Aircraft (항공기 Bulkhead 체결구조의 균열 원인 및 개선에 관한 연구)

  • Choi, Hyoung Jun;Park, Sung Jae
    • Journal of the Korea Academia-Industrial cooperation Society
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    • v.21 no.6
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    • pp.448-454
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    • 2020
  • This study aims to determine the cause of structural defects occurring during aircraft operations and to verify the structural integrity of the improved features. The fracture plane was analyzed to verify the characteristics of the cracks and the fatigue failure leading to the final fracture was determined by the progress of the cracks by the repeated load. During aircraft operations, the comparative analysis of the load measurement data at the cracks with the aircraft design load determined that the measured load was not at the level of 30% of the design to be capable of being damaged. A gap analysis resulted in a significant stress of approximately 32 ksi at the crack site. Pre-Load testing also confirmed that the M.S. was reduced by more than 50% from +0.71 to +0.43, resulting in a sharp increase in aircraft load and the possibility of cracking when combined. Thus, structural reinforcement and the removal of the gap for aircraft cracking sites improved the defect. Based on the structural strength analysis of the improvement features, the bulkhead has a margin of about +0.88 and the fitting feature is about +0.48 versus allowable stress. In addition, the life analysis results revealed an improvement of approximately 84000 hours.

A Study on Aerodynamic Characteristics of Airfoil for Human Powered Aircraft (인간동력 항공기용 에어포일의 공력특성 연구)

  • Park, Jun-Yong;Im, Je-Yeon;Yeo, Seong-Yun;Yu, Gi-Wan
    • Proceeding of EDISON Challenge
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    • 2013.04a
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    • pp.331-336
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    • 2013
  • 본 연구에서는 인간동력 항공기의 주익에 적용할 에어포일 형상에 대한 공력 특성을 파악하였다. 인간동력 항공기 날개에 적용하기에 적절한 에어포일을 조사하였으며, DAE11, DAE21, DAE31, SG6043 익형에 대하여 전산유체해석 프로그램인 EDISON_CFD를 통하여 비교하였다. 인간동력 항공기의 낮은 비행속도를 감안하여 $6{\times}10^5$의 저 레이놀즈수에서 받음각에 따른 양력계수, 항력계수, 양항비 등을 얻어내어 상호 비교 분석하였다. 본 연구를 통해 인간동력 항공기 주익에 적용할 저 레이놀즈 에어포일 형상을 최종적으로 선택할 수 있는 근거 자료를 확보하였다.

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Aeroelastic Response Analysis for Wing-Body Configuration Considering Shockwave and Flow Viscous Effects (충격파 및 유동점성 효과를 고려한 항공기 날개-동체 형상에 대한 공탄성 응답)

  • Kim, Dong-Hyun;Kim, Yu-Sung;Hwang, Mi-Hyun;Kim, Su-Hyun
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.37 no.10
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    • pp.984-991
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    • 2009
  • In this study, transonic aeroelastic response analyses have been conducted for the DLR-F4(wing-body) aircraft configuration considering shockwave and flow separation effects. The developed fluid-structure coupled analysis system is applied for aeroelastic computations combining computational structural dynamics(CSD), finite element method(FEM) and computational fluid dynamics(CFD) in the time domain. It can give very accurate and useful engineering data on the structural dynamic design of advanced flight vehicles. For the nonlinear unsteady aerodynamics in high transonic flow region, Navier-Stokes equations using the structured grid system have been applied to wing-body configurations. In transonic flight region, the characteristics of static and dynamic aeroelastic responses have been investigated for a typical wing-body configuration model. Also, it is typically shown that the current computation approach can yield realistic and practical results for aircraft design and test engineers.

A Comparison of Control Methods for Small UAV Considering Ice Accumulation and Uncertainty (결빙 현상과 불확실성을 고려한 소형 무인항공기 제어기법 비교 연구)

  • Hyodeuk An;Jungho Moon
    • Journal of Aerospace System Engineering
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    • v.17 no.5
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    • pp.34-41
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    • 2023
  • This paper applies the icing effect and wing rock uncertainty to small unmanned aerial vehicles (UAVs), which have recently attracted attention. Attitude control simulations were performed using various control methods. First, the selected platform, the Skywalker X8 UAV with blended wing-body (BWB) configuration, was linearized for both its baseline form, and a form with applied icing effects. Subsequently, using MATLAB SimulinkⓇ, simulations were conducted for roll and pitch attitude control of the baseline configuration and the configuration with icing effects, employing disturbance observer-based PID control, model reference adaptive control, and model predictive control. Furthermore, the study introduced wing rock uncertainty simultaneously with icing effects on the configured model-a combination not previously explored in existing research-and conducted simulations. The performance of each control Method was compared and analyzed.