• Journal of Aerospace System Engineering
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• v.17 no.1
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• pp.97-105
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• 2023

For aviation sensor pod, structural integrity should be verified through static structural tests for flight loads induced in various maneuvering conditions of the aircraft. For this, it is necessary to develop a test system for full-scale static load test of sensor pod. Based on test requirements, this paper introduced a test system configuration of the static test and the development of test structure frame, restraints equipment, loading equipment, control, and measurement equipment. In addition, methods and procedures for verifying the developed test system were explained. In conclusion, the static load test and data acquisition were successfully performed. Reliability of the test equipment was also verified in the process.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.40 no.6
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• pp.536-541
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• 2012

An instrumented pod has been developed to measure the aeroacoustic environment as well as the conventional data such as load, vibration, and aerodynamic heating of fighters during flight tests, confirming to the recently developed external pod design for fighters. This study presents the development of the measurement system in detail, being the first indigenous effort in its kind. The pod was designed to meet the requirements of the MIL-HDBK-1763 and MIL-STD-810 Method 515, which are the base to determine the locations and range of sensors. The Endevco 8510B-2 was selected as the sensor to withstand the harsh environment during the flight tests. In order to assess the integrity of the fabricated pod design, a ground run-up test of a KF-16 has been conducted with the pod installed at Station 5. The test results show that the system works well but the sound level exceeds the predetermined sensor range. The sensor range has been readjusted for flight test performed later.

• Journal of Aerospace System Engineering
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• v.13 no.3
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• pp.32-39
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• 2019

Sensor pods mounted on the exterior of the aircraft used for tactical missions should have a fatigue life based on the expected load spectrum during operation. For mission equipment such as the sensor pod, the frequency fatigue life prediction method which applies the dynamic vibration environment condition is preferred due to the efficiency of the analysis. In this paper, a fatigue life prediction method in the frequency domain where stress due to static and dynamic loads is synthesized based on the actual flight load spectrum is proposed. After comparison with the existing analysis method, the fatigue life of the proposed analysis method was predicted conservatively. The proposed sensor pods satisfy the requirements of the fatigue life.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.8
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• pp.105-110
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• 2005

Analysis technique of flight compatibility test results using instrumented pod for external store is studied. Raw data of sensors and MIL-STD-1553B acquired from instrumented pod are analyzed separately. Besides, tuning and synchronization of sensor data enable the analysis of those two type of data simultaneously. Evaluation of analysis result shows that the analyzed data represent maneuvers of the aircraft successfully and agree the values of the real flight tests.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.9
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• pp.907-913
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• 2010

In this paper, we have described a development of the external instrumentation system of a fighter aircraft for flight test. The external instrumentation system consists of the instrumentation pod and the image pod. The instrumentation pod measures a flight data(attitude, velocity, altitude, etc) of the fighter aircraft by using GPS/AHRS sensor. The image pod takes high-speed images for the separation trajectory of a smart bomb with 2 high-speed cameras and video signal for it with one general camera. We have verified the performance of the external instrumentation system through the ground test, the environment test and the flight test.

• Journal of Internet Computing and Services
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• v.11 no.4
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• pp.33-39
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• 2010

In this paper, a data dissemination protocol that transmits data collected for Wireless Sensor Networks (WSNs) is newly proposed, and the proposed proactive protocol takes into account energy consumption minimized and delay time disseminated. The well-known SPMS (Shortest Path Mined SPIN) forms the shortest path-based routing table obtained by Bellman Ford Algorithm (BFA) and disseminates data using a multi-hop path in order to minimize energy consumption. The mentioned properties of SPMS cause memory burden to create and maintain the routing tables. In addition, whenever BFA is executed, it is necessary to suffer from the energy consumption and traffic occurred. In order to overcome this problem, a proactive dissemination protocol using Residual Energy and Signal Strength, called RESS, is proposed in this paper. Simulation results show that RESS outperforms SPMS up to 84% in terms of the number of traffic messages and the transmitted delay time of RESS is similar to that of SPMS using the shortest path.

• Journal of the Korea Institute of Military Science and Technology
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• v.26 no.1
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• pp.1-9
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• 2023

The skin structure of sensor pod mounted on the exterior of aircraft can be exposed to the acoustic dynamic load and static load such as aerodynamic pressure and inertial load during flight. Fatigue life prediction of structural model under acoustic load should be performed and also differential stiffness of model modified by static load should be considered. The acoustic noise test spectrum of MIL-STD-810G was applied to the structural model and the stress response power spectral density (PSD) was calculated. The frequency response analysis was performed with or without prestress induced by inplane static load, and the response spectrum was compared. Time series data was generated using the calculated PSD, and the time and frequency domain fatigue life were predicted and compared. The variation of stress response spectrum due to static load and predicted fatigue life according to the different structural model considering mean stress were examined and decreasing fatigue life was observed in the model with prestress of compressive static load.

• Electronics and Telecommunications Trends
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• v.20 no.6 s.96
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• pp.166-177
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• 2005

차량 운전자의 안전을 보장하고 운전의 편의를 돕기 위한 기술로는 차량용 레이더, 타이어 공기압 감지 장치, 원격시동 장치, 지리정보시스템 등이 있다. 그중 타이어는 차량의 수많은 부품들 중 도로와 직접 접촉하는 부품으로 타이어의 상태는 운전자의 안전에 직접적인 관련이 있다. 과거 포드 자동차에서는 파이어스톤에서 납품한 타이어 전량을 리콜하는 대규모 교체사례가 있었다. 초기 타이어 공기압 감지 장치는 일부 고급차종에만 적용되었는데 최근 압력 및 온도 측정용 센서의 높은 신뢰성과 양산비용의절감 및 국가의 정책적 요소가 복합적으로 작용하여 일반 차량에도 보급화가 진행중이다. 본 논문에서는 오늘날 타이어 공기압 감지 장치를 양산하는 업체들의 기술 동향을 분석하여 타이어 공기압 감지 시스템의 도입 배경, 국내외 기술기준 현황, 타이어 공기압 감지 시스템을 형성하는 기본 구조, 높은 정밀도를 가지는 반도체 센서 및 관련 기술에 대해 살펴본다.

• Proceedings of the KSRS Conference
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• 2008.03a
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• pp.53-58
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• 2008

인공위성을 통해 취득된 데이터들은 지상국의 수신처리시스템을 거쳐 표준영상으로 생산되며, 생산된 영상으로부터 사용자에게 의미 있고, 가치 있는 정보를 이끌어 내는 판독의 단계를 수행하게 된다. 본 연구에서는 원격탐사의 전반적인 이해를 돕기 위한 교육적 모델로서 캔샛 프로그램을 도입하였다. 캔샛 프로그램은 스탠포드대 로버트 트윙 교수의 제안으로 학생들에게 한 학기의 짧은 시간에 실제 인공위성의 설계, 해석, 제작, 조립, 시험, 발사, 운용 등 전반적인 시스템의 이해를 도모하기 위한 1Kg 이하의 캔 크기의 초소형 위성을 개발하는 교육 프로그램이다. 본 연구는 한국과학영재학교 R&E 프로그램의 지원으로 시작하였으며, 실제 초소형 위성 캔샛('KSAsat'으로 명명)을 직접 설계, 제작, 조립하고 최종적으로 발사 운용 시험을 수행하였다. 주 탑재체로 일반 상용 디지털 카메라를 장착하였으며, GPS, 광센서, 3 축 가속도계, 온도센서, 압력센서를 탑재하였다. 비행시험을 통해 성공적으로 영상을 취득하고, 각종 센서로부터의 데이터를 지상국으로 전송 받았다. 지상국을 통해 처리 되어진 데이터로부터 의미 있는 정보를 추출하는 판단의 단계를 거쳐 원격탐사의 전반적인 교육을 성공적으로 수행할 수 있었다. 본 논문에서 캔샛 프로그램이 원격탐사 교육에도 충분히 활용될 수 있음을 보였다.

• Proceedings of the Korea Information Processing Society Conference
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• 2014.11a
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• pp.1203-1204
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• 2014

세탁기에서 등속 원운동(uniform circular motion)시 발생하는 힘으로 인해 생기는 소음 및 진동을 트라이포드 수평계(tripod water level)의 자동 수평맞춤 센서 장치, 방진고무(vibration proof rubber)를 장착한 최적의 진동흡수 평판 기구를 설계 하고자 한다. 본 연구의 결과는 세탁기 소음으로 인한 층간소음 문제 해결에 기여 할 것이다.