• 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 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 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.33 no.4
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• pp.85-90
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• 2005

• 한국관개배수회지
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• no.17
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• pp.19-21
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• 1997

'At HR Wallingford we pursue excellence in scientific and technological research, consultancy and training in civil engineering and environmental hydraulics and problems related to water management. Our success is due to the competence and skills of our p

• 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 Korean Society of Coastal and Ocean Engineers
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• v.22 no.6
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• pp.397-404
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• 2010

Laboratory tests of wave overtopping rates for a rubble mound breakwaters armoured Tetrapod were carried out, with varying design waves, crest berm widths and crest freeboards. The objective of this study is to investigate overtopping performance and to examine the characteristics of the widely used overtopping prediction models through the results of laboratory tests. Laboratory tests show that structure slope and wave periods have a considerable influence on overtopping rates, but the difference of overtopping rates related to crest berm widths is slight. Owen(1980)'s prediction considerably overestimates compared to the measured valued. Prediction of Van der Meer et al.(1998) underestimates only for steep slope($cot{\alpha}$=1.5). Besley(1999)'s and Pedersen(1996)'s predictions have a relatively good agreement with the measured results for slopes with a broader crest berm width. In general, best agreement between measured and predicted overtopping rates is observed using modified Pedersen(1996)'s formula for all test conditions.

• Journal of Korean Society of Coastal and Ocean Engineers
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• v.32 no.3
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• pp.161-169
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• 2020

Physical experiments have been performed in a wave basin to investigate change of the wave loading on the crown wall under obliquely incident wave conditions. The measurement was carried out with wave incidence angle of 0, 15, 30 and 45°. The pressure transducers were placed on the front and bottom face of the crown wall to obtain horizontal and uplift force as well. It was found that both the horizontal and vertical force decreases with the incidence angle. Based on the analysis of the experimental data, a formula was suggested to estimate the reduction rate of horizontal and vertical forces under obliquely incident waves.

• Journal of the Korean Geotechnical Society
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• v.29 no.4
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• pp.23-32
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• 2013

In order to evaluate the bearing capacity behaviour of a monopod suction bucket foundation for an offshore wind tower at the western sea of Korea, a centrifuge load test and numerical analyses were performed. The monopod bucket foundation was designed to be installed in a silty sand layer. The model soil was prepared to simulate a target site by using soil samples having similar properties and controlling relative density. In-flight miniature cone penetration test and bender element array were used to confirm that the model soil had represented the target site conditions. The load - rotation curve of the centrifuge load test was analysed. A series of numerical analyses were performed to validate the experimental conditions. Self-weight of the model, distance to the boundary and elastic modulus of the soil layer were varied to study their effects on the load - rotation curves.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.4
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• pp.91-99
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• 2005

Flight compatibility certification is performed to substantiate the compatibility between ALQ-X ECM pod and KF-16D/RF-4C aircraft. A certification plan for the ALQ-X flight compatibility is established. Similarity analysis, mass/inertia analysis, structural analysis/test, and ground vibration test/flutter analysis are made to support the safety of MIL-HDBK-1763 Test 250 (Captive compatibility flight profile). Aircraft flew along flight envelope boundary with representative ALQ-X configurations. Handling qualities are evaluated by comparing flight characteristics of the aircraft with and without ALQ-X. Structural integrity and endurance is evaluated using measured flight test data. Results of these flight tests showed that ALQ-X is compatible with KF-16D/RF-4C without altering the flight envelope which has originally been certified for ALQ-88 and ALQ-119 ECM pods. ALQ-X certification program made following technical achievements: Type III certification for foreign designed fighter, flutter analysis program development using GVT results, and utilization of MIL-STD-1553B data bus in flight test.