• Title/Summary/Keyword: 소형 민수 헬기

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Comparative Study of Engine Type Certification Criteria (항공기 엔진 민수 인증 기준의 비교 분석 연구)

  • Kim, Jae-Hwan;Jung, Yong Wun;Moon, Gyeong Chan;Park, Sooyoul;Kim, Myeonghyo
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2017.05a
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    • pp.201-204
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    • 2017
  • An comparative analysis between two engine type certification specifications which are FAR Part 33 and EASA CS-E has been performed to provide fundamental information for validity assessment of civil certified engine when it is installed to a military rotorcraft. The analysis result has been used to build a traceability information between CS-E and MIL-HDBK-516C by which the substantiation data for engine type certification can be used as parts of aircraft propulsion system airworthiness substantiation.

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Comparisons of Rotor Performance and Noise between Candidate Light Civil Helicopters (민수헬기 대상기종 로터 공력성능 및 소음 비교)

  • Chung, Kihoon;Kang, Hee Jung;Kim, Do-Hyung;Yun, Chul Yong;Kim, Seungho;Park, Kuhwan;Lee, Sang-Gi
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.41 no.9
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    • pp.726-733
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    • 2013
  • The rotor blade of helicopter is the core component determining helicopter performance and requiring low noise and low vibration because the blade becomes the major source of noise during flight. The performance analysis of candidates rotor blades is very critical because LCH(Light Civil Helicopter) will be developed parallel with LAH(Light Armed Helicopter) as an international upgrade program based on the existing platform of foreign civil helicopter. This research was aimed to recognize the performance of the candidates rotor blades compared with the newly developed foreign rotor blades and to investigate the feasibility about developing korea unique shape rotor blades by analysis the rotor performance and noise. The result of this research can be used for the target performance index during negotiation with foreign helicopter company and developing korea unique shape rotor blades.

Development and Verification of Active Vibration Control System for Helicopter (소형민수헬기 능동진동제어시스템 개발)

  • Kim, Nam-Jo;Kwak, Dong-Il;Kang, Woo-Ram;Hwang, Yoo-Sang;Kim, Do-Hyung;Kim, Chan-Dong;Lee, Ki-Jin;So, Hee-Soup
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.50 no.3
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    • pp.181-192
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    • 2022
  • Active vibration control system(AVCS) for helicopter enables to control the vibration generated from the main rotor and has the superb vibration reduction performance with low weight compared passive vibration reduction device. In this paper, FxLMS algorithm-based vibration control software of the light civil helicopter tansmits the control command calculated using the signals of the tachometer and accelerometers to the circular force generator(CFG) is developed and verified. According to the RTCA DO-178C/DO-331, the vibration control software is developed through the model based design technique, and real-time operation performance is evaluated in PILS(processor in-the loop simulation) and HILS(hardware in-the loop simulation) environments. In particular, the reliability of the software is improved through the LDRA-based verification coverage in the PIL environments. In order to AVCS to light civil helicopter(LCH), the dynamic response characteristic model is obtained through the ground/flight tests. AVCS configuration which exhibits the optimal performance is determined using system optimization analysis and flight test and obtain STC certification.

Brand Marketing Strategy for Light Civil Helicopter (LCH) with Brand Asset Valuator (BAV) Model (BAV 모델을 적용한 소형 민수 헬기(LCH) 브랜드 커뮤니케이션 전략)

  • Ji Ho Park;Haeun Lee;Sanghak Lee
    • Journal of the Korean Society for Aviation and Aeronautics
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    • v.32 no.2
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    • pp.48-64
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    • 2024
  • This study established a marketing strategy for the KAI Light Civil Helicopter (LCH) market by applying a Brand Asset Valuator (BAV) model to the LCH project currently underway by Korea Aerospace industries (KAI). Through literature reviews, the global scale of LCH projects and the development status of KAI LCH were identified. Subsequently, four sub-items from the BAV model were applied, and an expert survey was conducted. The primary data underwent an analysis process following the completion of the validity and reliability verification stage. The analysis revealed that the highest value was in the knowledge indicator, while the lowest value was in differentiation. The analysis confirmed KAI LCH's position on the BAV Power gird, indication that brand vitality, particularly differentiation, was lower than brand knowledge. Accordingly, this study finally presents a new marketing strategy to enhance the brand vitality of KAI LCH.

Design of Mach-Scale Blade for LCH Main Rotor Wind Tunnel Test (소형민수헬기 주로터 풍동시험을 위한 마하 스케일 블레이드 설계)

  • Kee, YoungJung;Park, JoongYong
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.46 no.2
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    • pp.159-166
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    • 2018
  • In this study, the internal structural design, dynamic characteristics and load analyses of the small scaled rotor blade required for LCH(Light Civil Helicopter) main rotor wind tunnel test were carried out. The test is performed to evaluate the aerodynamic performance and noise characteristics of the LCH main rotor system. Therefore, the Mach-scale technique was appled to design the small scaled blade to simulate the equivalent aerodynamic characteristics as the full scale rotor system. It is necessary to increase the rotor speed to maintain the same blade tip speed as the full scale blade. In addition, the blade weight, section stiffness, and natural frequency were scaled according to the Mach-type scaling factor(${\lambda}$). For the design of skin, spar, torsion box, which are the main components of the blade, carbon and glass fiber composite materials were adopted, and composite materials are prepreg types that can be supplied domestically. The KSec2D program was used to evaluate the section stiffness of the blade. Also, structural loads and dynamic characteristics of the Mach scale blade were investigated through the comprehensive rotorcraft analysis program CAMRADII.

Airloads and Structural Loads Analysis of LCH Rotor Using a Loose CFD/CSD Coupling (유체-구조 연계해석을 통한 소형민수헬기(LCH) 공력 및 구조하중 해석)

  • Lee, Da-Woon;Kim, Kiro;Yee, Kwan-Jung;Jung, Sung-Nam
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.47 no.7
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    • pp.489-498
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    • 2019
  • The airloads and structural loads of Light Civil Helicopter (LCH) rotor are investigated using a loose CFD/CSD coupling. The structural dynamics model for LCH 5-bladed rotor cwith elastomeric bearing and inter-bladed damper is constructed using CAMRAD-II. Either isolated rotor or rotor-fuselage model is used to identify the effect of the fuselage on the aeromechanics behavior at a cruise speed of 0.28. The fuselage effect is shown to be marginal on the aeromechanics predictions of LCH rotor, though the effect can be non-negligible for the tail structure due to the prevailing root vortices strengthened by the fuselage upwash. A lifting-line based comprehensive analysis is also conducted to verify the CFD/CSD coupled analysis. The comparison study shows that the comprehensive analysis predictions are generally in good agreements with CFD/CSD coupled results. However, the predicted comprehensive analysis results underestimate peak-to-peak values of blade section airloads and elastic motions due to the limitation of unsteady aerodynamic predictions. Particularly, significant discrepancies appear in the structural loads with apparent phase differences.

Establishing Engine Accelerated Mission Test Cycles complying with the CS-E of European Aviation Safety Agency (유럽항공안전청 형식증명 감항기준에 부합하는 엔진가속시험 사이클 수립)

  • Park, Sooyoul;Moon, Gyeongchan;Koo, Hyuncheol
    • Journal of Aerospace System Engineering
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    • v.14 no.1
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    • pp.62-67
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    • 2020
  • The European Aviation Safety Agency (EASA) legislates the CS-E (Certification Specification-Engine) for type certification of aircraft engines. According to the CS-E, engine manufacturers (type certificate holders) the need to show compliance of continued airworthiness of an engine during the overhaul, and the Accelerated Mission Test (AMT) is usually accepted as means of compliance. As a part of the Korean Civil Helicopter program, the engine has been developed with foreign manufacturers to achieve the EASA engine type certificate. In this study, the AMT procedure is planned for the engine to be certified by the EASA, and AMT cycles are also established to meet airworthiness requirements of the CS-E in consideration of the engine design and operation characteristics.

A Design of Handling Quality Assessment Environment Based on FLIGHTLAB Model Using Legacy Simulator (레거시 시뮬레이터를 활용한 FLIGHTLAB 모델 기반의 조종성 평가 환경 설계 연구)

  • Yang, Chang Deok;Lee, Seung Deok;Cho, Hwan Heui;Jung, Dong Woo
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.44 no.6
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    • pp.530-536
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    • 2016
  • The handling quality simulator including high fidelity flight mechanics model is indispensable component to design and verify the flight control system. Korea Aerospace Industries, LTD. (KAI) has been performing LCH (Light Civil Helicopter) core technology development program regarding automatic flight control system (AFCS) software development. And KAI has been developing flight mechanics model using FLIGHTLAB to design and evaluate the AFCS flight control law. This paper presents the handling quality assessment environment development results through the combining FLIGHTLAB with a legacy simulator. And this paper details the FLIGHTLAB model, application development process and FLIGHTLAB interface design. The developed handling quality assessment environment has been demonstrated with the ADS-33E hover and pirouette MTE (Mission Task Element) maneuver simulation.