• 제목/요약/키워드: Nonlinear Aerodynamic Characteristics

검색결과 55건 처리시간 0.026초

단발 터어보프롭 항공기의 파라메터 추정 및 비행시뮬레이션 (Parameter estimation and flight simulation of a single turbo-prop aircraft)

  • 이환;이상기
    • 제어로봇시스템학회:학술대회논문집
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    • 제어로봇시스템학회 1997년도 한국자동제어학술회의논문집; 한국전력공사 서울연수원; 17-18 Oct. 1997
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    • pp.1659-1662
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    • 1997
  • The objective of this paper is to estimate the aerodynamic derivatives of a single turbo-prop aircraft at a specified flight condition for the best deduction of the dynamic characteristics using modified maximum likelihood estimation method whcih is known to be unbiased, efficient, and consistent. The flight test data necessary to the estimation of aerodynamic derivatives is obtained by implementing the six degree of freedom nonlinear flight simulation to consider the effects of several control input types, control deflection amplitudes, and intensity of turbulence. The simulated data is added with the measurement noise, which is regarded as the actual flight test data.

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Three-dimensional Guidance Law for Formation Flight of UAV

  • Min, Byoung-Mun;Tahk, Min-Jea
    • 제어로봇시스템학회:학술대회논문집
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    • 제어로봇시스템학회 2005년도 ICCAS
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    • pp.463-467
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    • 2005
  • In this paper, the guidance law applicable to formation flight of UAV in three-dimensional space is proposed. The concept of miss distance, which is commonly used in the missile guidance laws, and Lyapunov stability theorem are effectively combined to obtain the guidance commands of the wingmen. The propose guidance law is easily integrated into the existing flight control system because the guidance commands are given in terms of velocity, flight path angle and heading angle to form the prescribed formation. In this guidance law, communication is required between the leader and the wingmen to achieve autonomous formation. The wingmen are only required the current position and velocity information of the leader vehicle. The performance of the proposed guidance law is evaluated using the complete nonlinear 6-DOF aircraft system. This system is integrated with nonlinear aerodynamic and engine characteristics, actuator servo limitations for control surfaces, various stability and control augmentation system, and autopilots. From the nonlinear simulation results, the new guidance law for formation flight shows that the vehicles involved in formation flight are perfectly formed the prescribed formation satisfying the several constraints such as final velocity, flight path angle, and heading angle.

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플랩을 갖는 복합재 평판 날개의 비선형 공력 탄성학 해석 (Nonlinear Aeroelastic Analyses of Composite Wing with Flap)

  • 신원호;배재성;이인
    • Composites Research
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    • 제20권1호
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    • pp.8-14
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    • 2007
  • 플랩을 갖는 복합재 평판날개에 대해서 유격 비선형성과 구동장치의 동적 강성을 고려하여 비선형 공탄성 해석을 수행하였다. DHM 방법을 사용하여 아음속 비정상 공기력을 계산하였으며 유격은 기술함수를 적용하여 이선형 스프링으로 가정하였다. 동적 강성을 기어시스템의 지배방정식으로부터 계산하고, 적층각과 재질에 따른 공탄성 특성을 살펴보았다. 선형 및 비선형 공탄성 해석 결과들은 플러터 특성이 유격과 동강성에 따라 크게 달라지는 것을 보여주었다. 다양한 형태의 제한주기거동이 선형플러터 속도 이전과 이후에서 관찰되었다.

스포일러 동적 작동에 따른 에어포일 공력특성 역전현상 연구 (Computational Investigations of Adverse Effects of Deploying Spoilers on Airfoil Aerodynamic Characteristics)

  • 정형석
    • 한국항공우주학회지
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    • 제48권5호
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    • pp.335-342
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    • 2020
  • 스텔스 성능을 향상시키기 위해 꼬리날개를 제거한 무미익 항공기는 러더(rudder)를 대체하여 스포일러(spoiler)를 활용하여 방향조종을 수행한다. 짧은 시간에 스포일러 작동을 반복하는 경우 비정상적(unsteady)이고 비선형적인 공력특성이 발생하여 항공기 비행성능에 역효과(adverse effect)를 초래할 수 있다. 본 연구에서는 dynamic mesh 기법을 적용한 전산해석을 통하여 스포일러 전개에 따른 에어포일의 비정상 공력 특성을 해석하였다. 스포일러 전개 속도, 장착 위치, 전개 스케줄(deployment scheduling) 변화에 따른 공력특성을 분석하여 스포일러의 동적 작동에 따른 역효과를 감소시킬 수 있는 방안을 검토하였다. 스포일러 장착위치 및 전개 방식의 적절한 선정을 통해 스포일러 동적 역효과를 감소시킬 수 있음을 확인하였으며, 에어포일 형상최적화를 통한 역효과 감소방안에 대한 추가적인 연구가 필요한 것으로 판단된다. 이러한 동적 공력 데이터는 향후 무미익 형태의 항공기 개발에 기초자료로 활용될 수 있을 것이다.

받음각 효과를 고려한 발사체 날개단면의 초음속극초음속 비선형 유체유발진동해석 (Nonlinear Flow-Induced Vibration Analysis of Typical Section in Supersonic and Hypersonic Flows with Angle-of-Attack Effect)

  • 김동현;김유성;윤명훈
    • 한국군사과학기술학회지
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    • 제10권4호
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    • pp.12-19
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    • 2007
  • In this study, nonlinear flow-induced vibration(flutter) analyses of a 2-DOF launch vehicle airfoil have been conducted in supersonic and hypersonic flow regimes. Advanced aeroelastic analysis system based on computational fluid dynamics and computational structural dynamics is successfully developed and applied to the present analyses. Nonlinear unsteady aerodynamic analyses considering strong shock wave motions are conducted using inviscid Euler equations. Aeroelastic governing equations for the 2-DOF airfoil system is solved by the coupled integration method with interactive CFD and CSD computation procedures. Typical wedge type airfoil shapes with initial angle-of-attacks are considered to investigate the nonlinear flutter characteristics in supersonic(15). Also, the comparison of detailed aeroelastic responses are practically presented as numerical results.

인공신경망 이론을 적용한 3단 축류압축기의 다분야 통합 최적설계 (Multidisciplinary Design Optimization of 3-Stage Axial Compressorusing Artificial Neural Net)

  • 홍상원;이세일;강형민;이동호;강영석;양수석
    • 한국유체기계학회 논문집
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    • 제13권6호
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    • pp.19-24
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    • 2010
  • The demands for small, high performance and high loaded aircraft compressor are increased in the world. But the design requirements become increasingly complex to design these high technical engines, the requirement of the design optimization become increased. The optimal design result of several disciplines show different tendencies and nonlinear characteristics of the compressor design, the multidisciplinary design optimization method must be considered in compressor design. Therefore, the artificial Neural Net method is adapted to make the approximation model of 3-stage axial compressor design optimization for considering the nonlinear characteristic. At last, the optimal result of this study is compared to that of previous study.

FUZZY CONTROL LAW OF HIGHLY MANEUVERABLE HIGH PERFORMANCE AIRCRAFT

  • Sul Cho;Park, Rai-Woong;Nam, Sae-Kyu;Lee, Man-Hyung
    • 제어로봇시스템학회:학술대회논문집
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    • 제어로봇시스템학회 1998년도 제13차 학술회의논문집
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    • pp.205-209
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    • 1998
  • A synthesis of fuzzy variable structure control is proposed to design a high-angle-of-attack flight system for a modification version of the F-18 aircraft. The knowledge of the proportional, integral, and derivative control is combined into the fuzzy control that addresses both the highly nonlinear aerodynamic characteristics of elevators and the control limit of thrust vectoring nozzles. A simple gain scheduling method with multi-layered fuzzy rules is adopted to obtain an appropriate blend of elevator and thrust vectoring commands in the wide operating range. Improving the computational efficiency, an accelerated kernel for on-line fuzzy reasoning is also proposed. The resulting control system achieves the good flying quantities during a high-angle-of- attack excursion. Thus the fuzzy logic can afford the control engineer a flexible means of deriving effective control laws in the nonlinear flight regime.

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Wind spectral characteristics on strength design of floating offshore wind turbines

  • Udoh, Ikpoto E.;Zou, Jun
    • Ocean Systems Engineering
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    • 제8권3호
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    • pp.281-312
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    • 2018
  • Characteristics of a turbulence wind model control the magnitude and frequency distribution of wind loading on floating offshore wind turbines (FOWTs), and an in-depth understanding of how wind spectral characteristics affect the responses, and ultimately the design cost of system components, is in shortage in the offshore wind industry. Wind spectrum models as well as turbulence intensity curves recommended by the International Electrotechnical Commission (IEC) have characteristics derived from land-based sites, and have been widely adopted in offshore wind projects (in the absence of site-specific offshore data) without sufficient assessment of design implications. In this paper, effects of wind spectra and turbulence intensities on the strength or extreme responses of a 5 MW floating offshore wind turbine are investigated. The impact of different wind spectral parameters on the extreme blade loads, nacelle accelerations, towertop motions, towerbase loads, platform motions and accelerations, and mooring line tensions are presented and discussed. Results highlight the need to consider the appropriateness of a wind spectral model implemented in the strength design of FOWT structures.

유도무기 날개 단면형상에 따른 초음속 및 극초음속 플러터 특성 (Supersonic and Hypersonic Flutter Characteristics for Various Typical Section Shapes of Missile Fin)

  • 김동현;김유성;김요한;오일권
    • 한국소음진동공학회논문집
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    • 제18권5호
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    • pp.496-502
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    • 2008
  • In this study, supersonic and hypersonic flutter characteristics have been analyzed for the various typical section shapes of missile fin configurations. Nonlinear flutter analyses are conducted considering the effect of moving shock waves. Computational fluid dynamic method is applied to accurately predict unsteady aerodynamic loads due to structural motions for the solution of aeroelastic governing equations. Commonly used typical section shapes of supersonic and hypersonic launch vehicles are considered in the present numerical study. Detailed flutter responses for four different typical section models are presented and the flutter characteristics are physically investigated.

동적실속 수동제어장치 최적설계 (Design Optimization of Passive Control Devices for Dynamic Stall Control)

  • 주완돈;이보성;이관중;이동호
    • 한국항공우주학회지
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    • 제33권1호
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    • pp.11-19
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    • 2005
  • 본 연구에서는 진동 운동하는 익형의 동적실속 특성을 향상시키기 위하여, 고정 앞전 Droop과 Gurney 플랩의 크기와 위치에 대한 최적설계를 수행하였다. 고정 앞전 Droop이 모멘트 특성의 개선에 효율적이나 양력특성의 저하를 유발 할 수 있다. 반면에 Gurney 플랩은 양력특성의 향상을 가져오지만, 모멘트특성을 악화시키는 특성이 있다. 고정앞전 Droop의 설계변수는 상호 보완적인 특성을 갖는 위치와 각도를 설정하였으며, Gurney 플랩은 그 길이를 설계변수로 설정하였다. 또한, 동적실속과 같이 비선형성이 강한 문제의 설계를 위해서 고차 다항식의 반응면 기법과 민감도 기반의 최적설계 기법을 사용하였다. 최적화는 양력과 모멘트 특성이 동시에 개선되도록 수행 하였다. 설계 결과 동적실속의 양력, 모멘트 및 항력특성의 향상을 가져올 수 있었으며, 가변 앞전 Droop과 Gurney 플랩을 결합한 능동제어장치에 버금가는 동적실속 제어 효과를 갖을 수 있음을 확인하였다.