• 항공우주시스템공학회지
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• 제11권4호
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• pp.1-7
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• 2017

복합재 무인기의 설계 허용치를 개발은 산업계에 가장 중요한 관심사이다. 전통적인 유인항공기 구조물의 인증방법을 시제기나 기술 시현기에 적용하는 것은 과도하게 긴 개발 시간과 비용을 발생시킨다. 본 논문에서는 경량 복합재 무인기의 구조중량의 줄이기 위한 설계 허용치 설정 방법을 제안하였다. 본 논문에서는 B-basis 복합재 재료물성의 설계허용치 적용 가능성을 검토하였다. 또한 여러 가지 민항기와 무인기의 목표 파손확률을 검토하여 제시하였다. 결과로부터, 경량 복합재료 무인기의 설계 허용치 요구조건은 유인 복합재료 항공기에 비하여 완화되어야 하는 것을 알 수 있다.

• 한국항공운항학회지
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• 제19권3호
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• pp.1-9
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• 2011

In this paper, a conceptual design process for Very Light Jet aircraft has been proposed incorporating aircraft safety certification. During the proposed design process, satisfaction of the airworthiness certification for an intermediate resulting aircraft configuration is evaluated and then redesigns are carried out if necessary and until the designed aircraft configuration satisfies the airworthiness requirements. Certification database has been developed using FAR 23, AC 23, KAS 23, and CS 23 as the airworthiness certification. Based on the developed certification database Design Certifcation Related Table has been produced to use the airworthiness requirements as design constraints in the propsed design process. Using Quality Function Deployment the design variables for a redesign are carefully selected and a design optimization is performed. To demonstrate the feasibility and effectiveness of rapid aircraft conceptual design using the proposed approach, a Very Light Jet design optimization including a redesign of wing flap has been performed and the design results have been presented.

• 한국항공운항학회지
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• 제17권2호
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• pp.18-22
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• 2009

In this study, we surveyed the operating status of the Light Sport Aircraft(LSA) in Korea, and reviewed the minimum requirements of the airpark for LSA in other countries. Based on the information, we presented the airpark standards to ensure the safe take-off, landing, and operation of LSA in Korea.

• 한국자동차공학회논문집
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• 제3권1호
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• pp.108-117
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• 1995

The primary purpose of this extensive test effort was to observe real-time operational performance characteristics associated with automotive grade fuel utilized by piston engine powered light aviation aircraft. In fulfillment of this effort, baseline engine operations were established with 100LL aviation grade fuel followed by four blends of automotive grade fuel. A comprehensive sea-level-static test cell/flight test data collection and evaluation effort were conducted to review operational characteristics of a carbureted light aircraft piston engine as related to fuel volatility, fuel temperature, and fuel system pressure. Presented herein are results, data, and conclusions drawn from test cell engine operation as well as flight test operation on 100LL aviation grade and four blends of automotive grade fuel.

• 한국항공운항학회지
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• 제18권2호
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• pp.35-40
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• 2010

In this study, we surveyed the operating status of the Light Sport Aircraft(LSA) in Korea, and reconstructed the flight route for Light Sport Aircraft in Yecheon TMA. Amended flight routes are LS095(Danyang Airpark $\Leftrightarrow$ Yeongju Airpark), LS096(Andong Airpark $\Leftrightarrow$ Yeongju Airpark), LS098(Yeongdeok Airpark $\Leftrightarrow$ Yeongju Airpark) and LS099(Yeongdeok Airpark $\Leftrightarrow$ Andong Airpark).

• 한국항공운항학회지
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• 제28권1호
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• pp.45-58
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• 2020

According to the Ministry of Land, Infrastructure and Transport press release ('18.12.21.) The amendment of the Aviation Business Act will reduce the capital requirements for aviation leisure operators and make it easier to enter aviation leisure businesses by improving regulations on small air transportation business. In addition, as the scale of the UAV(Unmanned Aerial Vehicle) sector is expected to increase globally, the dramatic increase in low altitude operating aircraft, including this, must be taken into account. The low altitude aircraft category is divided into small airplanes, helicopters, light aircrafts and ultra-light aircrafts, and instructors include school instructor pilots and student pilots, military and national helicopter pilots, and aviation leisure operators. In case of low altitude aircraft, there are cases of canceling operations due to low visibility and low clouds, and aircraft accidents due to excessive operation and sudden weather phenomenon. Therefore, in order to prevent low-altitude aircraft accidents, a safe flight plan based on weather conditions and weather forecasts and more accurate and local weather forecasts and weather forecast data are needed to prepare for the rapidly changing weather conditions.

• 한국항행학회논문지
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• 제27권2호
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• pp.173-181
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• 2023

항공모함은 군용함정이 항공기를 통하여 전투를 수행하기 위하여 항공기의 질서정연한 흐름유지가 필요하다. 항공기 흐름유지는 함정과 항공안전을 강화하기 위한 중요한 요소이다. 항공기 흐름유지를 위해서는 현재 운용 중인 레이더 기반의 감시정보와 CNS 통합 기술에 기반을 둔 감시 장비들에 의한 감시정보를 동시에 수용하여 보다 양질의 관제정보를 제공하는 최첨단 항공관제시스템을 개발이 필수적이다. 이를 위하여 본 연구는 이러한 점에 착안하여 해외 사례를 기초로 우리나라에서 경항공모함을 운영하기 위해 요구되는 항공지원시스템(Aviation Support System)과 항공관제장비(Air Traffic Control System)의 운영에 대해 구체적인 관제 장비의 기능 및 운영 방법 관하여 기술 한다.

• International Journal of Aerospace System Engineering
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• 제5권1호
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• pp.9-18
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• 2018

The longitudinal flight parameters of a light airplane are estimated from flight test data by use of the output error method. The reliability of the flight test measurement is examined in engineering judgment, scatter and Cramer-Rao bound, which turns out to be satisfactory with minor defects. Estimated parameter values are validated by comparing the simulated responses with the ones from actual flight tests. The FTD(Flight Training Device) of a light airplane turns out to satisfy the qualification of FAA Level 5 FTD in longitudinal motion. All the necessary practices for generation of high-fidelity data in longitudinal motion of a light aircraft are successfully performed in this study.

• 시스템엔지니어링학술지
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• 제9권2호
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• pp.83-90
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• 2013

Integrated aircraft synthesis process for rapid analysis and design is described in this paper. Data flow between different analysis fields is described in details. All the data are divided into several groups according to importance and source of the data. Analysis of design requirements and certification regulations is carried out to determine baseline configuration of an aircraft. Overall design process can be divided into initial sizing, conceptual and preliminary design phases. Basic data for conceptual design are obtained from initial sizing, CAD and geometry analysis. Basic data are required input for weight, aerodynamics and propulsion analyses. Results of this analysis are used for stability and control, performance, mission, and load analysis. Feasibility of design is verified based on analysis results of each discipline. Design optimization that involves integrated process for aircraft analysis is performed to determine optimum configuration of an aircraft on a conceptual design stage. The process presented in this paper was verified to be used for light aircraft design.

• 항공우주기술
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• 제7권2호
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• pp.1-10
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• 2008

일반적으로 조류충돌 안전성 입증에 대한 규정은 고정익 항공기 중 FAR Part 23급 커뮤터 및 FAR Part 25급 민간항공기 부류의 항공기에 국한되어 적용되고 있다. 이는 상대적으로 낮은 비행속력과 주로 개인용 항공기로의 활용 등의 이유로 조류 충돌에 대한 위험성이 낮게 평가되었기 때문이다. 하지만 최근의 지점 간 운송을 목적으로 하는 Air-Taxi 등의 수요 증가로 인한 소형항공기 운항시간 증가 예측과 급격한 수요의 VLJ(Very Light Jet)등은 FAR Part 23급 Normal, Utility급 항공기의 조류 충돌 안전성에 대한 규정 적용 및 안전성 향상에 대한 필요성을 증가시키고 있다. 본 연구에서는 외연적 유한요소 해석을 이용한 소형항공기 주익에 대한 조류 충돌 안전성 평가와 Crushable Foam을 적용한 안전성 향상방안을 제시하고 있다.