• Journal of the Korea Institute of Military Science and Technology
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• v.17 no.4
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• pp.430-435
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• 2014

This paper presents the case study of the airworthiness certification for the flight control system of tactical UAV. Airworthiness regulations for flight characteristics and design and construction based on the STANAG 4671 are selected, and safety assessment is performed. Stall protection on wing level and turning flight criteria, and flap interconnection system failures were analyzed and applied to the flight control system design. The Hardware-in-the-loop simulation including math model, integrated system verification and validation test and failure mode and effects test were also performed and they are used to validate the means of compliance of the proposed airworthiness.

• Journal of Advanced Navigation Technology
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• v.21 no.1
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• pp.1-12
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• 2017

As the current ground transportation system becomes saturated, there is a need to develop a roadable personal air vehicle (PAV). Therefore, researches for PAV development and operation system development are being actively carried out in various countries around the world. PAV, the next generation transportation system, is a new concept of personal transportation that combines ground transportation, air traffic, and IT industry. Also, the development of PAV can solve the saturation of traffic congestion and shorten the travel time dramatically. In this study, we analyzed the certification criteria of FAR Part 23, which is going to be revised, and analyzed the patents and folding mechanism of Terrafugia Transition and Aeromobil 3.0, which are the most advanced of roadable PAV. Also, we used $OpenVSP^{(R)}$ for the reverse configuration design of the existing Terafugia transition and Aeromobile 3.0. Aerodynamic analyses were performed for the reverse configuration design using the $XFR5^{(R)}$ program.

• Current Industrial and Technological Trends in Aerospace
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• v.5 no.1
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• pp.75-92
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• 2007

2002년 프론티어사업의 일환으로서, 10년간 1200억의 예산으로 미래형 신개념비행체 기술개발사업을 시작한 스마트무인기사업은, $2002{\sim}2003$년 수행한 개념연구를 통해 미래형 신개념 고속 수직이착륙 항공기 개념으로서 틸트로터 개념을 선정하고 이의 개발에 매진하고 있다. 사업단에서는 우선, 항공 선진국에서 지난 반세기 동안 시행한 다양한 비행체 개념연구결과에 대해 자체적인 비교 분석 및 국제공동 연구를 근간으로하여, 당시 틸트로터에 필적하는 가능성을 보였던 스탑트로터(보잉사), 복합자이로콥터(카터콥터사) 개념이 아닌, 틸트로터 비행체의 기술개발을 결정하게 되었다. 각각의 비행체 개념이 갖는 위험성과 도전성, 그리고 소요기술, 설계특성, 개발 위험도 등에 대한 면밀한 분석을 기초로 한 사업단의 체계적 의사결정은 주효했다. 스탑트로터개념은 비행시험의 잇단 실패와 지연/잠정 중단사태가 이어졌고, 복합자이로콥터 또한 잇단 비행사고로 2002년 기록한 148kts를 능가하는 고속성능 시현에 지금까지 실패함으로써, 실용화 가능한 고속수직이착륙기로서의 검증을 위해서는 해결해야할 기술적 과제가 많이 남아있음을 보여주고 있다. 반면, 틸트로터 개념의 경우 V-22의 설계 수정형에 대한 성공적인 비행시험완료 및 인증획득으로 전면양산승인이 2005년 결정되어 458대가 (미해병대(360), 해군(48), 공군(50)) 납품될 예정이고, 2010년 인증획득을 목표로 민수용으로 개발중인 BA609의 순조로운 비행시험진행, 무인기로 개발된 Eagle Eye 기술시현기의 비행 시험성공과 2003년 미 해양경찰청으로부터 Deep Water 프로그램의 장거리 순찰임무 주력기종 선정과 같이 군용, 상용, 무인용 고속 수직이착륙 시장의 전 방위적 진입이 현실화되고 있다. 이에 따라 항공업계의 반응은 2가지 방향으로 나뉘고 있다. 하나는 유럽의 ERICA 프로그램과 같이 틸트로터 기술 개발을 서두르자고 주장하는 방향이고, 다른 하나는 시콜스키의 X2 프로그램과 같이 틸트로터와는 차별화된 독자적인 고속 수 직이착륙 비행체 개념 개발을 시도하는 것이다. 이러한 배경으로 국내 독자적인 기술력으로 지난해까지 일구어낸 성공적인 스마트무인기 상세설계 종료 및 축소형 비행체 전환비행성공은 그 의의가 매우 크다고 할 수 있다. 본 논문은 틸트로터 개발사를 통해, 신개념 비행체 개발의 어려움과 교훈을 알아보고, 세계에서 2번째로 틸트로터 기술을 개발하고 있는 스마트무인기 사업의 현황과 기술적 특징 및 의의의 정리, 그리고 틸트로터의 대안으로 진행중인 새로운 고속 VTOL 비행체 연구현황에 대한 소개 와 간단한 기술적 평가를 포함시켰다.

• Journal of Aerospace System Engineering
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• v.11 no.4
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• pp.1-7
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• 2017

The development of effective design allowable values for unmanned composite aircraft is an issue of paramount concern for the industry. The application of conventional manned aircraft structural certification methods to unmanned aircraft such as prototype and technology demonstrators, can lead to excessively long development time and costs. In this paper, the determining method of composite structure design allowable values for light composite unmanned aircraft is presented to reduce to the structural weight. This paper seeks to show the applicability of composite B-basis material values as a design allowable of light composite unmanned aircraft structures. A review of different civil and UAV targets failure probability is given. From the results, the researchers can know that the requirements of light composite unmanned aircraft design allowable should be alleviated, compared to manned composite aircrafts.

• Journal of Aerospace System Engineering
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• v.12 no.6
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• pp.17-22
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• 2018

The amount of fuel, which affects aircraft endurance, needs to be measured accurately. This paper deals with the implementation of a fuel quantity measurement system that consists of capacitive fuel sensor, DAQ board, and Labview software. The main circuit of the implemented system for measuring fuel quantity is simulated with Pspice to identify parameters, which are related to the change of fuel quantity. After simulation, we established that Vrms changes with the variation of fuel amount. The Vrms, which is the output of fuel sensor, is transmitted to the Labview software via the DAQ board of the implemented fuel quantity measurement system. The fuel quantity is also calculated using this software. The present simulation results indicated that the accuracy of the implemented fuel quantity measurement system improved with the filter application.

• Journal of Advanced Navigation Technology
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• v.27 no.6
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• pp.821-827
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• 2023

In this study, the aircraft technical standards of the Korea and the United States were analyzed to derive the dynamometer test procedure required to prove the compatibility for flight test certification of the metal brake pad for transport aircraft. Since the design modification of the brake systems is classified as a major change, the STC(Supplemental Type Certificate) and the PMA(Parts Manufacturer Approval) are required. In accordance with the TSO-C135a, the technical standard order for brake system in the United States, the design landing-stop test, accelerate-stop test, and most severe landing stop test were selected among the test items for flight test. The conditions for the dynamometer test are determined according to the specifications provided by aircraft manufacturer, and the brake pad condition, deceleration, and the number of test are defined according to the TSO-C135a.

• The Korean Journal of Air & Space Law and Policy
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• v.35 no.3
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• pp.95-126
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• 2020

In 2017, the world's first WIG ship (WIG: Wing In-Ground) pilot's license written test was conducted in Korea. The WIG ship is a ship that combines the characteristics of ships and airplanes. Therefore, the pilot of the WIG ship was allowed to apply only for those who had the aircraft pilot's license and the 6th class marine nautical license. The WIG ship pilot's license system was first introduced by Korea, so there are no international standards for the license system, and the introduction of a domestic qualification system also requires institutional arrangements due to various restrictions such as pilot training. However, in order to become a valuable industry as a future growth engine for the ocean, several urgent problems need to be solved, and that is the training of manpower for WIG ships. Therefore, I reviewed the institutional issues related to pilot training as this subject. Since 2001, various countries around the world have been discussing this issue, centering on IMO, and Korea has continued to participate and cooperate in IMO meetings. And the national qualification test for surface flying ships was conducted in Korea from 2011. However, there are still problems to be solved, and I pointed out the advancement of the manpower training system, the education and training system, and the designated national educational institution system. As a solution to this, it was suggested through the improvement of the license system and the operation of designated educational institutions. Among these solutions, I believe that the best way is to entrust the operation of designated national educational institutions to private educational institutions. However, I propose a plan that the government entrusts to private educational institutions, but the government is responsible for licensing and supervision. WIG ship will be a new market for the aviation industry and aviation workers.

• Journal of Advanced Navigation Technology
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• v.27 no.4
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• pp.382-390
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• 2023

The Korea market for LUAV (Light Unmanned Aerial Vehicle) weighing less than 150 kg is growing rapidly. As a result, the market for manufacturing and operating LUAV is expanding, and domestic development of parts and finished products is actively taking place. However, the flight control system and onboard software, which are key components of domestic LUAV, are largely dependent on overseas products due to the excessive cost and period required for development. This paper presented a domestic software development and certification procedure using DO-178C, a guideline for aircraft software development, and the Model-based Development method, and conducted a survey of those involved in the development, manufacturing, and certification of LUAV and analyzed the results. In addition, a case study was conducted to apply the software development plan to the helicopter FCC (Flight Control Computer).

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.12
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• pp.1035-1042
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• 2016

By using commercial flight simulation game engine, X-Plane, we have studied QTG(Qualification Test Guide) generation that can satisfy FTD level 5. Flight model is SR-20 of Cirrus. In list of QTG, There are some items to measure control forces. therefore, we have installed CLS(Control Loading System) to flight control devices in order to make it possible to measure control forces. We made Autopilot function externally to make flight model in trim conditions because X-Plane don't provide internal trim routine function. In addition to develop an algorithm, it can automatically perform the test. To avoid the inconvenience to control as it was to be carried out in same conditions. In case of FTD level 5, it is possible to use alternative data sources not only real flight data. By using these alternative data sources, all test results satisfy a scope given by CFR Part 60.

• Journal of the Korean Society of Propulsion Engineers
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• v.22 no.3
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• pp.128-133
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• 2018

Korean civil airworthiness requirements of powerplant system are regulated by KAS(Korean Airworthiness Standard) Part 23 and Part 33. These are equivalent to FAR Part 23, Part 33 of FAA, and CS-23 and CS-E of EASA. FAA and EASA rewrite the airworthiness requirements for small airplane. They changed current 'prescriptive regulation' to a 'performance-based regulation' which makes safety performance the objective. Powerplant requirements have also been changed extensively by this concept revolution. In accordance with this reorganization, we studied the new powerplant system requirements of FAR Part 23 and proposed ideal directions to rewrite the Korean Airworthiness Standard.