• 제목/요약/키워드: Helicopter preliminary design

검색결과 17건 처리시간 0.027초

헬리콥터 연료탱크 기본설계 (Preliminary Design of Helicopter Fuel Tank)

  • 이정훈;김성찬;김현기
    • 항공우주시스템공학회지
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    • 제2권2호
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    • pp.14-19
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    • 2008
  • This paper presents the procedure and the results of the preliminary design of the fuel tank as a part of developing the helicopter. For the requirements of operational capability, MIL-DTL-27422D and Defence Standard 15-2/Issue 1 are considered to be applied in developing a helicopter fuel tank. The procedure of the fuel tank development is set up including interface plate design, tank design, former design, tank material lay-up, and tank installation assessment. The outer moulded line and fittings of fuel tank have being designed, and several test will be performed to get the qualification.

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회전익 항공기의 기본설계 및 가격예측 연구 (Preliminary design and cost estimation of helicopters)

  • 이충연;고광호;정성남;유영훈
    • 한국항공우주학회지
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    • 제38권4호
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    • pp.309-314
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    • 2010
  • 기본설계 단계에서 회전익 항공기의 가격을 보다 정확하게 예측하기 위해서 Harris & Scully에 의해 제시된 가격 예측 식을 최신의 추세식으로 수정하였다. 이를 위해 1997년 이후의 총 74개에 대한 회전익기 가격 및 제원 정보를 이용하여 가격 예측 식을 업데이트하였다. 업데이트 된 가격 예측식을 Tishchenko의 기본설계 기법과 통합하여 기본설계 단계에서 가격을 고려하도록 구성하였다. 본 기본설계 및 가격예측 프로그램을 현재 운용되고 있는 미국 Sikorsky사의 S-76C+를 비롯한 여러 기종의 헬리콥터에 적용하여 가격과 제원 결과를 도출하고 검증하여 본 연구의 유효성을 확인하였다.

다목적 쌍발 헬리콥터용 터보축 엔진의 성능해석 및 기본설계 (Performance Analysis and Preliminary Design for the Turbo-Shaft Engine of the Multi-Purpose Helicopter)

  • 서정원;윤건식
    • 대한기계학회논문집B
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    • 제26권1호
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    • pp.55-65
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    • 2002
  • In this study, the procedures for the preliminary design of the turbo-shaft engine for the light multi-purpose helicopter are established. The engine specifications are determined through the performance analysis on the on-design and off-design conditions by the use of simulation program. In addition, the effect of humidity on the engine performance is examined by considering the change of the gas properties and characteristic maps due to moisture contents. The calculation results show that the engine power is reduced by the existence of moisture in working fluid.

통계적 기법을 적용한 헬기 형상설계 연구 (A Study of Helicopter Initial Sizing using Statistical Methodology)

  • 김준모;오우섭
    • 한국군사과학기술학회지
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    • 제10권1호
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    • pp.22-32
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    • 2007
  • This paper describes a study of a helicopter database for the sizing stage of a preliminary design process. The database includes specifications and performance parameters for more than 150 conventional single rotor helicopters currently in market. Design parameters, including configuration and weight parameters, have been analyzed and trend curve equations(regression equations) are derived using the regression analysis method. Finally, the applicability of this research result was verified whether the method is reliable for being adopted as a useful design tool in the early stage of a helicopter design process.

후퇴각 날개끝이 있는 헬리콥터 로터깃의 회전주파수 해석 (Rotating Frequency Analysis of a Helicopter Rotor Blade with Swpt Tips)

  • 황호연;;정건교
    • 소음진동
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    • 제10권2호
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    • pp.229-239
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    • 2000
  • To reduce the drag rise on the advancing helicopter rotor blade tips, the tip of the blade is modified to have sweep, anhedral and pretwist. The equations of motion of rotor blade with these tip angles were derived using Hamilton principle, programmed using FORTRAN and named as ARMDAS(Advanced Rotorcraft Multidisplinary Design and Analysis System). Rotating frequency analysis of rotor blades with swept tipe was performed that is necessary in conceptual and preliminary design phases of the helicopter design. Vibration analysis of non-rotating blades was also accomplished and compared with MSC/NASTRAN resutls for the basis of comparison with the vibration test data. The rotating frequency analysis of blades with an actual rotor blade data was also performed to verify coded program and to check the possibility of a resonance of an actual rotor blade at the specific rotating speed.

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Power and Trim Estimation for Helicopter Sizing and Performance Analysis

  • Laxman, Vaitla;Lim, Jae-Hoon;Shin, Sang-Joon;Ko, Kwang-Ho;Jung, Sung-Nam
    • International Journal of Aeronautical and Space Sciences
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    • 제12권2호
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    • pp.156-162
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    • 2011
  • The preliminary design stage of helicopters consists of various operations and in each operation design several detailed analysis tasks are needed. The analysis tasks include performance and the required power estimation. In helicopter design, those are usually carried out by adopting the momentum theory. In this paper, an explicit form of computational analysis based on the blade element theory and uniform/non-uniform inflow model is developed. The other motivation of the present development is to obtain trim and required power estimation for various helicopter configurations. Sectional and hub loads, power, trim, and flapping equations are derived by using a symbolic tool. Iterative computations are carried out till convergence is achieved in the blade response, inflow, and trim. The predictions regarding the trim and power estimation turn out to be correlated well with the experimental results. The effect of inflow is further investigated. It is found that the present prediction for the lateral cyclic pitch angle is improved with the non-uniform inflow model as compared to that by the uniform inflow model. The presently improved trim and power estimation will be useful for future helicopter sizing and performance analysis.

무인 헬리콥터용 길이가변 로터 블레이드 개발을 위한 선행연구 (Preliminary Study on Development of Length-Variable Rotor Blade for Unmanned Helicopter)

  • 천주홍;변영섭;이병언;송우진;김정;강범수
    • 한국정밀공학회지
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    • 제27권3호
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    • pp.73-79
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    • 2010
  • A preliminary study on a length-variable rotor blade for a small unmanned helicopter has been conducted. After surveys on previous researches, and examining requirements for application to a small unmanned helicopter, a length-variable rotor blade was designed and manufactured to be driven by centrifugal force from rotor revolution with no mechanical actuator. The rotor blade was divided into a fixed inboard section and an outboard section sliding in span-wise direction. In order to determine the operating conditions of the length-variable rotor during revolution, and to derive the design variables of extension spring and rotor weight, a series of analyses from multi-body dynamics solution were conducted. The manufactured prototype was verified of its length-varying mechanism from a rotor stand, the results and required future improvements are discussed.

헬리콥터 로터 블레이드 예비설계를 위한 에어포일 공력 해석 (Airfoil Aerodynamic Analysis for the Helicopter Rotor Blade Preliminary Design)

  • 김상진
    • 한국항공우주학회지
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    • 제33권6호
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    • pp.21-30
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    • 2005
  • 헬리콥터 로터 블레이드 예비설계 단계에서 에어포일 선정과 분포의 기초 자료를 생성하기 위해 로터 에어포일 공력해석을 수행하였다.기존 헬리콥터의 에어포일 중 공력해석 대상으로 10개를 선정하고 블레이드 요소이론을 이용한 공력해석에 적합한 table 형태의 공력계수 자료를 생성하였다. 해석 비용을 고려, 풍동시험 대신 간단한 수학적 모델을 이용하여 모든 받음각 영역($-180^{o}\sim180^{o}$)에서 공력특성 곡선($C_{l},C_{m},C_{d}$)을 구성하였다. 공력특성곡선 구성에 필요한 각 에어포일의 필수 공력자료를 IBLM을 이용하여 구하였으며, 구성된 공력특성곡선은 실험결과와 정성적으로 일치하였다. 마지막으로, 에어포일 선정과 분포설계의 기준을 마련하기 위하여 각 에어포일의 양력계수, 모멘트계수를 상호 비교한 후 분류하였다.

헬리콥터용 2단 축류압축기의 재설계에 관한 연구 (A Study on the Redesign of the Two-Stage Axial Compressor for Helicopter Engines)

  • 김진한;최창호;김춘택;양수석;이대성
    • 한국유체기계학회 논문집
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    • 제4권1호
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    • pp.7-13
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    • 2001
  • In developing a multistage compressor, the stage matching is one of the critical design issues. The mismatching can be often observed even if each stage has been proven good and then used as part of a compression system. A good matching among the stages can be achieved by changing various design parameters (i.e., passage cross sectional areas, blades angles, stagger angles, curvature, solidity, etc.). Therefore, designers need to find out what parameters must be changed and how much. In this study, a method to search the design parameters for optimum stage matching has been used based on an 1-D mathematical model of a compressor, which uses the data obtained from the preliminary test to identify the design parameters. This methodology is applied with a two-stage axial compressor, which was originally designed for a helicopter gas turbine engine. After identifying design parameters using preliminary test data, an optimization process has been employed to achieve the best matching between the stages (i.e., maximum efficiency of the compressor at its operation modes within a given range of the rotor speed under given restrictions for required stall margins and mass flow). 3-D flow calculations have been performed to confirm the usefulness of the corrections based on the 1-D mathematical model. Calculational results agree well with the experimental data in view of the performance characteristics. Some promising results were produced through the methodology proposed in this paper in conjunction with flow calculations.

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가상 환경 상의 헬리콥터 조종실 설계를 위한 정량적인 인간공학적 평가 방법 개발 (Development of Quantitative Ergonomic Assessment Method for Helicopter Cockpit Design in a Digital Environment)

  • 정기효;박장운;이원섭;강병길;엄주호;박세권;유희천
    • 대한인간공학회지
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    • 제29권2호
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    • pp.203-210
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    • 2010
  • For the development of a better product which fits to the target user population, physical workloads such as reach and visibility are evaluated using digital human simulation in the early stage of product development; however, ergonomic workload assessment mainly relies on visual observation of reach envelopes and view cones generated in a 3D graphic environment. The present study developed a quantitative assessment method of physical workload in a digital environment and applied to the evaluation of a Korean utility helicopter (KUH) cockpit design. The proposed assessment method quantified physical workloads for the target user population by applying a 3-step process and identified design features requiring improvement based on the quantified workload evaluation. The scores of physical workloads were quantified in terms of posture, reach, visibility, and clearance, and 5-point scales were defined for the evaluation measures by referring to existing studies. The postures of digital humanoids for a given task were estimated to have the minimal score of postural workload by finding all feasible postures that satisfy task constraints such as a contact between the tip of the index finger and a target point. The proposed assessment method was applied to evaluate the KUH cockpit design in the preliminary design stage and identified design features requiring improvement. The proposed assessment method can be utilized to ergonomic evaluation of product designs using digital human simulation.