• Title/Summary/Keyword: KC-100

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Flutter Analysis Model Tuning of KC-100 Aircraft with the Ground Vibration Test Results (지상진동시험결과를 이용한 KC-100 항공기의 플러터 해석모델 보정)

  • Paek, Seung-Kil;Choi, Yong-Joon
    • Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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    • 2011.10a
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    • pp.191-195
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    • 2011
  • The airframe ground vibration tests were conducted on the KC-100 aircraft according to the regulation requirement, KAS 23.629(a)(2) and the modal characteristics for the target modes were measured. To make FE model tuning, a design sensitivity approach with engineering judgment was implemented using MSC/Nastran and Attune, a genetic algorithm based parameter optimization software. Based on the comparison between initial prediction and test results, design variables such as beam cross-sectional properties and spring stiffnesses were devised. As the results, the correlation of the FE model to the GVT results was made appropriately, meeting the goal of matching the target frequencies within 5%.

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KC-100 Full-scale Static Test System (KC-100 전기체 정적 구조시험 장치)

  • Shim, Jae-Yeul;Lee, Sang-Geun;Ahn, Seok-Min
    • Aerospace Engineering and Technology
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    • v.11 no.1
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    • pp.7-18
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    • 2012
  • Full-scale static test was introduced for the KC-100 aircraft which is domestic civil aircraft to be certified for the first time. Test requirement, test frame, and important test stystems such as loading system, counterbalance system, restraint system and jacking system are explained in detail. Especially, the way to satisfy compliance for the installation of test article and loading system is introduced by using check sheets for the installations. 15 Full-scale and 7 local test conditions were successfully completed and the test data was obtained.

The Analysis of Mission Profile of the KC-100 UAV (KC-100 무인화 비행체 임무 형상 분석)

  • Lee, Jung-hoon
    • Journal of Aerospace System Engineering
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    • v.14 no.5
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    • pp.49-57
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    • 2020
  • The KC-100 has completed civil type certification with the Ministry of Land, Infrastructure, and Transport, and is currently under development as an unmanned aerial vehicle as part of the Ministry of Land, Infrastructure, and Transport. The Certification Technology of small Unmanned Airplane system (CTsUA system), which is an unmanned KC-100, is being developed to enable the installation of heavy-duty mission equipment and long-time flight missions. This study investigated the process and results of analyzing various parameters such as aircraft weight, airspeed, flight altitude, required horsepower, and fuel consumption at each stage to construct a mission profile based on the operational concept of the CTsUA system. To maintain a maximum take-off weight of 3,600 lbs (1,633 kg), the analysis determined that the weight of the application equipment for the unmanned system should be kept below 80 lbs (36 kg).

An Investigation of Icing Effects on the Aerodynamic Characteristics of KC-100 Aircraft (KC-100 항공기의 표면발생 Icing 형상 및 공력 영향성 연구)

  • Jung, Sung-Ki;Lee, Chang-Hoon;Shin, Sung-Min;Myong, Rho-Shin;Cho, Tae-Hwan;Jeong, Hoon-Hwa;Jung, Jae-Hong
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.38 no.6
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    • pp.530-536
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    • 2010
  • In-flight icing is a critical technical issue for aircraft safety and, in particular, ice accretions on aircraft surfaces can drastically impair aerodynamic performances and control authority. In order to investigate icing effects on the aerodynamic characteristics of KC-100 aircraft, a state-of-the-art CFD code, FENSAP-ICE, was used. A main wing section and full configuration of KC-100 aircraft were considered for the icing analysis. Also, shapes of iced area were calculated for the design of anti-/de-icing devices. The iced areas around leading edge of main wing and horizontal tail wing were observed maximum 7.07% and 11.2% of the chord length of wing section, respectively. In case of wind shield, 16.7% of its area turned out to be covered by ice. The lift of KC-100 aircraft were decreased to 64.3%, while the drag was increased to 55.2%.

A Study on the System Engineering Application to KC-100 Aircraft Development (민간항공기개발 시스템엔지니어링 적용 연구)

  • Choi, Nag-Sun;Kang, Min-Seong;Kim, Kwang-Hae;Koh, Dae-Woo
    • Journal of the Korean Society of Systems Engineering
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    • v.5 no.2
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    • pp.49-56
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    • 2009
  • KC-100(KAI Civil Aircraft, Small Series) aircraft is 4 seats general aviation aircraft with single piston engine which is developing under FAA part 23 category by Korea Aerospace Industries(KAI) and will be a shadow program for civil aircraft safety infrastructure improvement. This aircraft will be the first civil aircraft developed in Korea meeting the Korean regulatory KAS Part 23 requirements. Type certification for KC-100 aircraft was applied at the second half of this year. The type certificate is expected to be issued after 3 years of design, prototype manufacturing, ground and flight tests. In this paper the system engineering process for civil aircraft was first reviewed. Next, the differences and similarities in the system development between military and civil aircraft were systematically examined using experiences for KAI military aircraft development program.

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Study on The Propulsion System Flight Test of KC-100 Small Airplane (KC-100 소형항공기 추진계통 비행시험 사례연구)

  • Kim, Dae-wook;Kang, Sung-soo;Kim, Chan-jo;Wu, Bong-gil
    • Journal of Aerospace System Engineering
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    • v.7 no.2
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    • pp.15-22
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    • 2013
  • The conformity of propulsion system need to be evaluated thorough the flight test because it is an important part of the airplane to ensure the flight safety. In the small airplane development, the flight test according to KAS(Korean Airworthiness Standards) Part 23 is one of the ways to verify compliance in terms of satisfactory aircraft/engine/propeller integration. This thesis introduces means of verifying the compliance and test requirement of KAS Part 23 for the conformity of the propulsion system in small airplane. It also describes procedures and methods of propulsion system flight test through KC-100 airplane project.

Modigication of host cells and Expression of Recombinant E. coli trp plasmids for the increased Production of Tryptophan in Klebsiella pneumoniae (Klebsiella pneumoniae에서 트립토판 생산증대를 위한 숙주개발 및 재조합 trp plasmid의 발현)

  • 지연태;홍광원;박장현;이세영
    • Korean Journal of Microbiology
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    • v.25 no.1
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    • pp.46-51
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    • 1987
  • In order to increase the production of tryptophan by maximizing expression of recombinant trp plasmid, Klebsiella pneumoniae KC 105(pheA tyrA trpE trpR tyrR) was genetically modified. KC 107, inosine monophospate(IMP) auxotroph from KC 105 and KC 108, histidine(His) auxotroph from KC 107 were also derived respectively to increase phosphoribosylpyrophosphate(PRPP) production which is required for tryptophan biosynthesis. From KC 107 phosphoribosylpyrophosphate consumption which is required for tryptophan biosynthesis. From KC 107 and KC 108, KC 109 and KC 110, both arginine auxotrophs were derived respectively. To investigate the expression of recombinant trp plasmid in the selected K. pneumoniae mutants, the auxotrophic mutants were transformed with recombinant trp plasmids pSC 101-$trpE^{FBR}$, pSC 101-trpL(.DELTA.att) $trpE^{FBR}$ (pSC 101-trp-AF). Amount of tryptophan produced and activities of tryptophan synthase of $trpR^{-}$ mutant (KC 100) and $tyrR^{-}$ mutnat(KC 105) containing recombinant plasmid pSC 101-trp operon were increased by 30-40% as compared with KC 99(pheA tyrA trpE) containing recombinant plasmid pSC 101-trp operon. Activities of tryptophan synthase and production of tryptophan of KC 108 ($His^{-}$) and KC 109($Arg^{-}$) containing recombinant plasmid pSC 101-trp operon were increase by two-fold as compared with KC 107 containing pSC 101-trp operon.

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Development and Validation of Dynamic Model for KC-100 UAS (KC-100 항공기 무인화를 위한 운동모델 구축 및 검증)

  • Seong Hyeon Kim;Ji Bon Kim;Jung Hoon Lee;Eung Tai Kim;Byoung Soo Kim
    • Journal of Aerospace System Engineering
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    • v.17 no.1
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    • pp.79-87
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    • 2023
  • To design a control law of an aircraft, an accurate aircraft dynamic model is required. To obtain an aerodynamic database (DB) to build a dynamic model, a large number of wind tunnel tests are typically required. However, when flight test data of target aircraft exist such as in the process of unmanned conversion of a manned aircraft, an aircraft dynamic model can be obtained through a parameter estimation method and a DB tuning procedure. This paper describes a nonlinear model construction process and a verification method for KC-100 OPV aircraft. Flight data compatibility analysis was performed to determine suitability of the estimation method application. Linear model estimation was performed using the maximum likelihood estimation method. Results of aerodynamic DB tuning process and verification applying the FFS standard to the nonlinear model constructed are presented.

First report of three Filosporella species isolated from freshwater ecosystem in Korea (담수생태계로부터 분리된 Filosporella 3종의 국내 최초보고)

  • Mun, Hye Yeon;Oh, Yoosun;Goh, Jaeduk;Chung, Namil
    • The Korean Journal of Mycology
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    • v.47 no.2
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    • pp.165-172
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    • 2019
  • To investigate the diversity of aquatic fungi, we collected deposits of soil, plants, and plant litter from ponds and streams. NNIBRFG1552 was isolated from soil deposits and NNIBRFG3013 from plant deposits in Namsaengi-mot in Jeju, Korea in 2016; NNIBRFG5472 was isolated from plant litter in Bocheong-cheon, Boeun, Korea in 2018. Based on morphological characteristics and phylogenetic analysis using rDNA sequences of the internal transcribed spacer (ITS), NNIBRFG1552, NNIBRFG3013, and NNIBRFG5472 were identified as Filoporella exilis (100% similarity with KC834046), F. fistucella (99.8% with KC834047), and F. cf. annelidica (100% with KC834044), respectively. Furthermore, cultural and morphological characteristics were analyzed to confirm the molecular identification. No species of the genus Filosporella has yet been reported in Korea.

Spin-up, Spring-back Load Analysis of KC-100 Nose Landing Gear using Explicit Finite Element Method (외연적 유한요소법을 이용한 KC-100 전방착륙장치 Spin-up, Spring-back 하중 해석)

  • Park, Ill-Kyung;Kim, Sung-Jun;Ahn, Seok-Min
    • Journal of the Korean Society for Aviation and Aeronautics
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    • v.19 no.4
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    • pp.51-57
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    • 2011
  • The spin-up and the spring-back are most severe load cases in the aircraft landing gear design. These load cases are caused by reciprocal action of complex physical phenomenon such as the friction between a tire and ground, inertia of the rotation of a tire and the flexibility of a landing gear structure. Generally, the empirical formula or the theoretical formula is used to calculate the spin-up and spring-back load in the early stage of the development program of the aircraft landing gear. After the materialization of the design of a landing gear, spin-up and spring-back load are acquired by the free drop test. In this study, the spin-up and the spring-back load of the rubber shock absorber type KC-100 nose landing gear are calculated by the explicit finite element analysis. Through this analysis, more accurate and realistic spin-up and spring back loads could be applied to the early phase of the development of the aircraft landing gear.