Structural Safety Evaluation of Test Fixture for Static Load Test of External Fuel Tank for Fixed-Wing Aircraft

Kim, Dong-Hyeop; Kim, Young‐Cheol; Kim, Sang Woo; Kim, Hyungi; Kim, Sung‐Chan

doi:10.1007/s42405-021-00411-w

Cited by 7 publications

(4 citation statements)

References 17 publications

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“…Figure11shows the actual test setup installed to perform the EFT structural test. The structural safety of the test fixture used in the structural test was confirmed in earlier research 12. Figures12(a) and (b) correspondingly show the test profiles for the test of the limit load (115% DLL) and that of the ultimate load (150% DLL) of LC-01.…”

supporting

confidence: 68%

“…The structural safety of the test fixture used in the structural test was confirmed in earlier research. 12 Figures 12(a) and (b) correspondingly show the test profiles for the test of the limit load (115% DLL) and that of the ultimate load (150% DLL) of LC-01. As shown in the test profiles, the structural test had the form of a 30% DLL preliminary test, followed by the limit load test or the ultimate load test.…”

Section: Test Setup and Test Profilementioning

confidence: 99%

“…The structural safety of the test fixture used in the structural test was confirmed in earlier research. 12

Figure 9.Test setup diagram for the structural test of the EFT.

Figure 10.Test specimen installed on the test fixture.

Figure 11.Actual test setup for the structural test of the EFT: (a) right side and (b) left side.…”

Section: Test Setup and Test Profilementioning

confidence: 99%

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Validation of the structural integrity of an aircraft external fuel tank through a structural test under flight-load conditions

Kim

An³

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part G:

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An external fuel tank, one of the main components of an aircraft, is a component that extends the range of the aircraft and that should be separable from the aircraft in emergency situations. During flight, if structural damage occurs in an external fuel tank, the survivability of the aircraft may be catastrophically affected. Therefore, the structural integrity of such external fuel tanks must be proven under flight-load conditions applied to the external fuel tank during flight. This study presents the results of a structural test conducted to verify the structural integrity of an external fuel tank for flight-load conditions. In the main text, the process of converting the six-component flight load into a test load is described, and a whiffle tree application plan is presented for efficient testing. Then, the reliability of the test load was confirmed by comparing it with the required flight load. As a result of the structural test, the test loads were stably controlled. It was also confirmed that the internal pressure of the test specimen measured in real time during the test was maintained well within the required pressure range and that the behavior of the EFT was suitably predicted through a numerical analysis. After the structural test, it was found through an inspection that the test specimen did not undergo serious structural damage under the required flight-load condition. In conclusion, through structural testing, it was validated that the newly developed external fuel tank had sufficient structural integrity under all required flight-load conditions.

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supporting

confidence: 68%

Section: Test Setup and Test Profilementioning

confidence: 99%

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Validation of the structural integrity of an aircraft external fuel tank through a structural test under flight-load conditions

Kim

An³

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…During the development of aircraft, aircraft wings must be subjected to static or fatigue testing [1][2][3][4][5][6] to simulate real working conditions. The data acquisition system is used to obtain the maximum force and displacement information that the aircraft wing can withstand and through the output signal of the servo drive circuit to make the electro-hydraulic servo valve to complete the force loading test on the aircraft wing.…”

Section: Introductionmentioning

confidence: 99%

Design and implementation of high precision servo channel loading card for fatigue testing of aircraft wings

Zhao

Xiao

Shen

2023

Circuit Theory & Apps

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SummaryA servo channel loading card (SCLC) with high precision data acquisition and output is developed for static and fatigue testing of aircraft wings. A high‐performance processor field programmable gate array (FPGA) is at the core to control the excitation source (ES) output circuit to provide excitation for the force and displacement sensor. To improve the precision of the ES output circuit, a 3DA‐based ES auto‐calibration circuit is designed. Simulation results show that the 3DA improves the precision of the automatic calibration of the ES circuit. The sensor signals are collected through high precision analog channels, and the signals are automatically zero calibrated and numerical control gain processed. Ultimately, a voltage or current signal is generated through the drive circuit to control the electro‐hydraulic servo loading system to complete a high precision force loading test on the aircraft wings. The experimental results show that the board designed has high reliability in both acquisition and output. The ES output achieved a precision of 0.1375 mV/V, the precision of signal acquisition achieves a precision of −0.175 mV/V, and the servo drive output achieves a precision of −0.06 mV/V, meeting the expected design precision of 1 mV/V.

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Static Structural Testing of Composite Wing Structure for Vertical Takeoff and Landing (VTOL) Unmanned Aerial Vehicles

Hwang,

Han,

Kim

2024

Int. J. Aeronaut. Space Sci.

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Structural Safety Evaluation of Test Fixture for Static Load Test of External Fuel Tank for Fixed-Wing Aircraft

Cited by 7 publications

References 17 publications

Validation of the structural integrity of an aircraft external fuel tank through a structural test under flight-load conditions

Validation of the structural integrity of an aircraft external fuel tank through a structural test under flight-load conditions

Design and implementation of high precision servo channel loading card for fatigue testing of aircraft wings

Static Structural Testing of Composite Wing Structure for Vertical Takeoff and Landing (VTOL) Unmanned Aerial Vehicles

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