• 한국항공우주학회지
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• 제37권10호
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• pp.1010-1016
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• 2009

본 본문에서는 항공기 탑재비행시험을 통한 무기체계 개발시험에 대하여 기술하였다. 국방과학연구소에서는 항공기를 운용하며, 각종 항공/유도 무기체계의 핵심 탑재장비와 센서 개발을 위하여 항공기 탑재비행시험을 수행하고 있다. 탑재비행시험 플랫폼으로는 KTX-1/XKO-1 항공기를 사용하며, 외부연료탱크 형상의 탑재시험체를 제작하여 시스템 연동을 위해 항공기를 수정하였다. 항공기 탑재비행시험을 통하여 각종 탐색기와 항법시스템 그리고 유도무기 핵심 탑재장비에 대한 개발시험을 수행하였다.

• 한국군사과학기술학회지
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• 제24권2호
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• pp.204-210
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• 2021

In this paper, we studied a method of wirelessly checking up the POD for captive flight tests which is performed during the development of guided weapons systems. The wireless power transfer module, the power distribution device, and the battery pack were designed to wirelessly power the captive flight test POD, and the communication device was designed to enable wireless communication between the POD and the check-up device. The communication device was designed to enable WiFi, IR communication, and laser diode communication, so that various communication methods could be tested. Through the performance test, it was confirmed that power was stably supplied to the captive flight test POD, and the wireless communication performance was verified by measuring the delay time and error rate. As a result, by using our system the POD check-up for the captive flight test was performed wirelessly and the data of the captive equipment could be obtained effectively.

• 한국항공우주학회지
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• 제35권1호
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• pp.73-78
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• 2007

국내 개발에 성공한 기본훈련기(KTX-1) 시제기 및 외부연료탱크를 활용하여 유도무기에 적용되는 핵심 부품의 비행환경 성능을 검증할 수 있는 탑재비행시험(Captive Flight Test) 절차 및 결과를 소개한다. 2001년부터 2006년까지 총 150 쏘티 이상의 탑재비행시험을 통하여 국내 개발된 탐색기, 항법장치/기법, 관성센서, 전파고도계 등을 비행환경에서 시험평가하여 유도무기체계 연구개발 단계에서 일정단축 및 비용절감에 기여하였다.

• International Journal of Aerospace System Engineering
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• 제4권2호
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• pp.5-9
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• 2017

In a pressurized fuel supply system of aircraft, a flow passage opening device is required to keep fuel continuously transferred from one tank to the other. The device utilizes balancing weights in order to follow up an acceleration at special conditions such as negative g. It is very difficult to test the device in a real high-speed and high-altitude test since severe test conditions and expensive supports are needed. Therefore, this paper deals with performance analysis of a flow passage opening device through low speed aircraft captive flight tests (CFT) including roll and negative-g maneuvers. It is shown that balancing weights in the device can open the passage in accordance with fuel position.

• 한국군사과학기술학회지
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• 제16권6호
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• pp.779-788
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• 2013

The load requirements should be known to design mechanical structure. This paper proposes a generation method of load requirements using U.S. military specification to design the external mounting structure of the helicopters of which the flight environments such as aerodynamic forces and inertia forces are unknown. In this study, the load requirements which were applied at the design of the pod structure for helicopter captive flight test could be computed by using this method. The validation of proposed method was confirmed from the test flight using developed pod system.

• 한국시뮬레이션학회논문지
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• 제27권1호
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• pp.111-117
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• 2018

영상탐색기가 적용된 유도무기체계의 경우 영상 추적 성능이 체계 성능에 큰 영향을 미치기 때문에 유도탄 비행 중 강인한 영상 추적 성능을 확보하는 것이 필수적이다. 유도탄의 실사격 비행시험이 실제 영상 추적 성능을 확인하기 위한 가장 확실한 방법이나, 실사격 시험만으로 영상 추적기법을 실험 및 수정/보완할 경우 매우 큰 비용 손실이 발생하게 된다. 따라서 영상탐색기를 유도탄 비행 궤적을 모의할 수 있는 비행체에 탑재 후 추적 성능을 시험하는 탑재비행시험(CFT; Captive Flight Test)을 수행하게 된다. 하지만 탐색기를 탑재하는 항공기가 유도탄의 완벽한 거동을 모의하는 것은 불가능하기 때문에 탑재 비행시험만으로 체계 성능을 확인할 수는 없다. 본 논문에서는 기존 영상추적기법 단독 성능 확인에만 한정되어 있던 탑재비행시험 영상을 통합비행 시뮬레이션에 적용하여 체계 성능 확인이 가능하도록 한 기법 연구 결과에 대하여 기술하였다. 이 연구는 탑재비행시험 영상의 활용도를 증대시킬 뿐만 아니라, 기존 합성영상 기반의 통합비행 시뮬레이션 기법의 사실성을 보완할 수 있어 다양한 측면에서 체계 성능 검증을 가능하게 하였다.

• 한국군사과학기술학회지
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• 제9권2호
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• pp.87-95
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• 2006

The performance of a microwave missile seeker and radar operating in an air-to-air look-down mode is strongly influenced by the presence of ground clutter In order to correctly account for the effects of ground clutter, it is required to develop a model capable of representing clutter characteristics as a function of range and/or frequency. In this paper, a program to estimate the clutter reflectivity for various ground conditions is developed, using the actually measured data and the data available from open literatures. In addition, clutter characteristics measured for various ground conditions such as sea, agricultural area, urban city and industrial area through the captive flight tests are presented.

• 한국군사과학기술학회지
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• 제22권4호
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• pp.501-508
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• 2019

In this paper, a study on a wireless check-up method of test equipment for captive flight test(CFT) was conducted. For CFT, test equipment is mounted on a POD, and check-up is carried on the test equipment's. For check-up the POD wirelessly, battery, power distribution unit, wireless communication devices were designed within the POD, and a check-up device is designed outside of the POD. Once the external check-up device sends a 'start signal' to the POD, it performs the overall check-up procedures and transmits the 'end signal' to the external check-up device. Detailed check-up results are stored in an internal storage device, and are possible to read from external check-up device if necessary, thereby improving the reliability of the wireless check-up. By implementing and applying these wireless check-up system, the reliability of the check-up was enhanced by dynamical and movable check-up, and safety is guaranteed as the check-up was carried without access to the aircraft.

• 한국콘텐츠학회논문지
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• 제19권7호
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• pp.436-443
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• 2019

본 논문의 목적은 탑재비행시험 간 무인헬기 연료 소모량에 영향을 미치는 인자들의 영향정도와 상관관계를 분석하여 예측모형을 수립하는 것이다. 본 연구에서는 실험계획법을 활용하여 4인자 2수준 완전요인실험을 설계하여 실험을 수행하였고, 결과 값을 분석하여 인자들의 주 효과와 교호작용을 도출하고 회귀분석을 통해 예측모형을 수립하였다. 본 연구에서 도출한 결과를 활용하여 효율적인 탑재비행시험 및 전자시험장 시험 능력 향상에 기여할 것으로 기대된다.

• 한국군사과학기술학회지
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• 제19권5호
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• pp.606-612
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• 2016

A Captive Flight Test(CFT) is used to verify the performance of missile component such as seeker and guiding algorithm of missile. Recently most of surface to air missile adapts multi-mode guidance method which include command guidance and active/passive guidance. A CFT system for missile system adapting multi-mode guidance method consists of pod equipment, command transmitting system and measuring system. In this paper, we proposed CFT system and testing method for missile which adapt multi-mode guidance, and system integration procedure by using distributed missile system integration method and procedure. The proposed CFT system and system integration method was applied to CFT of surface to air missile, and brought successful result.