• Proceedings of the KIPE Conference
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• 2016.07a
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• pp.143-144
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• 2016

본 논문에서는 유도무기 및 항공기 탑재장비용 30W급 군사용 DC-DC 컨버터를 설계하며, 군사용 전원장치 규격과 기존 군사용 DC-DC 컨버터 제품의 성능을 분석하여 개발제품의 요구사양을 정립한다. 기존 산업용 컨버터와 군사용 컨버터의 설계 방식 차이점을 분석한 뒤 MIL 규격과 정량적 요구사양 만족 여부를 실험 및 공인인증기관 시험을 통해 검증한다.

• The Journal of the Institute of Internet, Broadcasting and Communication
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• v.18 no.5
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• pp.89-95
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• 2018

In this paper, we analyze the antenna performance changes caused by the aircraft structure, diffraction and reflection, when the direction finding antenna used in the aircraft is mounted on the aircraft. Direction finding antenna is an antenna that receives radar threat signal in the direction finding device of aircraft electronic warfare system. Recently, because various antenna are mounted on an aircraft, various analyzes such as antenna performance and interference analysis are required. Therefore, the electromagnetic analysis was carried out by installing a broadband direction finding antenna with 50% bandwidth on simulated aircraft, and the direction finding performance was analyzed by comparing the single antenna performance with the performance mounted on the aircraft. The analyzed direction finding accuracy was $6.47^{\circ}$ RMS and predicted to be suitable as an antenna for aircraft direction finding antenna.

• The Journal of the Institute of Internet, Broadcasting and Communication
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• v.23 no.2
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• pp.51-59
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• 2023

The tracking radar system is installed and operated on the ground, ships, and aircraft, and requires a design to withstand electromagnetic interference with nearby electronic devices. In this case, radiation and immunity standards for cable connection must be satisfied to prevent malfunction of other equipment due to electromagnetic wave interference caused by cables connected to the tracking radar. The radiation standard must also be satisfied so that the electromagnetic wave noise generated and radiated from the tracking radar does not affect the peripheral device, so that the immunity standard for the electromagnetic wave emitted from the peripheral device must be satisfied. In this paper, we propose a design to satisfy MIL-STD-461G including CE, CS, RE, and RS, and explain design satisfaction through tests.

• Journal of the Institute of Electronics Engineers of Korea SC
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• v.49 no.3
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• pp.12-18
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• 2012

This paper presents a computation method of LOS(Line Of Sight) angle using IMU(Inertial Measurement Unit) for an antenna on aerial vehicle to point to a stationary satellite. In the overall system, the antenna is located at the front of the vehicle, and an IMU is introduced to account for body flexure dynamic. And using the differences between the position and velocity of the IMU based navigation and those of GPS/INS at the vehicle center. Kalman filter is designed to suppress Strapdown INS drift errors.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.1
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• pp.71-78
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• 2017

The electrical power system of Korean Utility Helicopter(KUH) is designed as a dual control system to enhance the system safety of aircraft and each system is installed separately at left and right of the aircraft. The system is composed of 2 AC generators, 1 APU generator, 2 Transformer Rectifier Units(TRU), AC/DC Electrical Master Box(AC/DC EMB). The AC/DC EMB, consists of 2 AC EMB and 2 DC EMB, is essential equipment which supply and distribute electric power to the aviation electronics and electrical equipment of KUH. There were defects caused by internal short circuit in AC EMB during the first production phase of the KUH. This paper describes the analysis of the defects, troubleshooting process, root cause, and the solution by design change.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.5
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• pp.41-49
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• 2005

This paper discusses the test procedure, instrumentation, verification methodology and the results of the ground vibration test(GVT) performed on the KF-16D aircraft to estimate experimentally dynamic characteristics of the aircraft. The modal tests for 7 external store configurations were conducted to estimate effects of external stores on the aircraft vibration modes. To emulate free-free boundary conditions the test aircraft was mounted on its landing gear structure with deflated tires during the GVT. The airframe modal tests were done by burst random excitations with 6 to 8 shakers and about 200 accelerometers. Frequency response functions(FRFs) were measured for each test, and the FRFs were reduced and analyzed to identify the dynamic parameters interested. The analyses were carried out in two steps. To extract modal parameters such as, frequencies and damping ratios, the poly-reference least square complex exponential method was used in the time domain. The mode shape coefficients were estimated with the least squares frequency domain method to identify the vibration modes.

• Journal of the Institute of Electronics Engineers of Korea TC
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• v.46 no.2
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• pp.60-65
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• 2009

A highly reliable Video Transmission System (VTS) was developed in order to obtain both video and digital data simultaneously in the real time flight test situation of a flying vehicle. The VTS integrates GPS date digital telemetry data and video signals into a compact digital data package which is compressed and processed by an MPEG-2 Encoder and a modulator respectively. The modulator is composed of a specially devised Forward Error Correction processor and base band QPSK modulator. The designed VTS was verified and proved for its required functioning and performance through separate flight tests using an airplane and Rockets.

• Journal of Aerospace System Engineering
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• v.17 no.4
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• pp.87-94
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• 2023

This paper addresses the installation and modification design of airframe structures for new and modified equipment installations that are essential for aircraft performance improvement. Typical performance improvement equipment mounted on the exterior of the aircraft include antenna, radar, electro-optical/infrared (EO/IR), and self-protection system equipment, which require structural reinforcement, modification, and mounting design of the green aircraft for operation. In the interior of the aircraft, console and rack structures are modified or added according to user operation requirements. In addition, this is accompanied by the installation design of equipment to be replaced and added for performance improvement, and the according modification of environmental control system components for internal cooling. The engineering process and cases in which airworthiness was verified through the detailed design of airframe structures with structural integrity, operability, and maintainability of performance-improved aircraft are presented.

• Journal of the KSME
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• v.29 no.6
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• pp.594-600
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• 1989

항공기용 원동기는 항공기를 추진시키기 위한 동력장치이다. 항공기가 추진력을 얻기 위해서는 프로펠러를 회전시켜 대량의 공기를 뒤로 가속시켜 그 반작용을 이용하는 방법과, 단순히 배기 가스를 뒤로 고속분사시켜 그 반작용을 이용하는 방법이 있다. 피스톤 엔진은 전자를, 터보 제트 엔진은 후자를 대표하고 있는데 두 가지 방법을 절충하여 터빈으로 프로펠러를 회전시키는 터보 프롭엔진과, 헬리콥터의 로우터를 회전시키는 터보 샤프트 엔진도 있다. 또 터보 제트 엔진과 터보 프롭 엔진의 증간성능을 꾀한 터보 팬 엔진이 있는데 효율이 아주 좋기 때문에 급속히 발 전되어 항공기용 원동기의 대명사격으로 현재 군용이나 민간기용으로 널리 사용되고 있다. 최 근에는 터보팬 엔진과 터보 프롭 엔진을 절충한 새로운 터보 프롭 APT (advanced turbo prop) 엔진의 실용화가 추진되고 있다. 이상과 같은 종류의 엔진 이외에도 항공기용 원동기에는 극히 제한된 용도에 쓰이는 램 제트와 펄스 제트 엔진 그리고 로켓 엔진 등이 있다. 원동기는 그 용 도에 따라 개발, 활용되는 것이기 때문에 오랜 역사를 지닌 피스톤 엔진은 아직까지도 경항공 기용 원동기의 주류를 이루고 있고, 앞으로도 터보 프롭 엔진과 더불어 나름대로 계속 활용될 것으로 전망된다.

• The Proceeding of the Korean Institute of Electromagnetic Engineering and Science
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• v.2 no.2
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• pp.85-90
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• 1991

군사장비에 대한 EMI문제는 2차 세계대전 이후 전자장비에 대한 의존도가 높아짐에 따라 크게 변화하였다. 2차 세계대전 초기에는 주로 항공기의 엔진점화장치에서 발생되는 3~30MHz 대역의 무선주 파수간섭(RFI)이 통신장비에 문제가 되었으며 간섭현상도 그다지 심각하지 않았다. 그러나 전자공학의 급 속한 발전에 따라 고성능 통신장비 및 레이다가 등장하였으며 각종 전자장비도 고출력화, 고밀도화됨에 따 라 장비자체에서 방사되는 전자파잡음의 세기가 증가하게 되었다. 이에 반해 체계(System)탑재 전자장비 들이 점차 마이크로프로세서화 됨에 따라 제어신호의 수준은 더 낮아져서 전자파간섭에 더욱 취약하게 되 었다. 또한 현대의 전장(Battle Field)은 수많은 전기/전자장비가 동시에 운용됨에 따라 발생되는 전자파로 인해 더욱 복잡한 전자파환경이 형성된다.