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http://dx.doi.org/10.5139/JKSAS.2018.46.6.464

Flap Hinge Moment Estimation through Ground and Flight Tests  

Ko, Myung-Gyun (7-3, Agency for Defense Development)
Publication Information
Journal of the Korean Society for Aeronautical & Space Sciences / v.46, no.6, 2018 , pp. 464-470 More about this Journal
Abstract
In this paper, a practical method of estimating the flap hinge moments which change according to the aircraft flap operations was introduced. For the flap design, the hinge moment derived by structural load analysis and wind tunnel tests was able to be compared with the real flight hinge moment, and the static safety of the flap structure could be verified though this comparison. In order to perform the tests, two strain gauges were installed on the flap hinge and an onboard device for aircraft load monitoring was utilized. Through the ground test, the correlation between the strain and the moment of the flap hinge was calibrated with analytic and finite element analysis. During the flight test, strain signals together with the flap deflection angles and airspeed were recorded. Finally, the flight hinge moments could be predicted by the measured strain which was calibrated with the analytic and the finite element analysis.
Keywords
Flap; Hinge moment; Ground and flight test; Aircraft load monitoring; Static safety;
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Times Cited By KSCI : 2  (Citation Analysis)
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1 Joo Y. S., Lee J. S., Park C. Y., Kim M. S., and Yoo H. J., "The Study on Aircraft Load Survey Test Technique," Proceeding of The Korean Society for Aeronautical and Space Sciences Spring Conference, Apr. 1994, pp. 224-228.
2 Park J. M., and Chung S. J., "The Study on Experimental Measurement Method of Hinge Moment Acting on Control Surface of Air Vehicle," Journal of The Korean Society for Aeronautical and Space Sciences, Vol. 40, No. 2, Feb. 2012, pp. 165-170.   DOI
3 Makarov K. A., and Pavlenko A. A., "Numerical Invetigation of an Aileron Hinge Moments and Effectiveness on a High Lift Wing Airfoil," 29th Congress of the International Council of the Aeronautical Sciences, Sep. 2014.
4 Cavalieri A. V. G., Girardi R. D., and Araujo. T. B., "Experimetal Determination of the Aerodynamic Characteristics and Flap Hinge Moment of the Wing Airfoil used at ITA's Unmanned Aerial Vehicle," 19th International Congress of Mechanical Engineering, Nov. 2007.
5 Federal Aviation Administration, Federal Aviation Regulations - Part 23 Airworthiness Standards : Normal, Utility, Acrobatic and Commuter Category Airplanes.
6 MSC.NASTRAN Version 68 Aeroelastic Analysis User's Guide, MSC NASTRAN Software corporation, Sep. 2009.
7 DT3625-1 Columbia Research Laboratories, Inc., Strain Sensors-Model DT3625 Series.
8 MIL-STD-1530D(USAF) - Aircraft Structural Integrity Program (ASIP), Department of Defense, 2016.
9 MIL-A-8871A(USAF) - Airplane Strength and Rigidity Flight and Ground Operation Tests, Department of Defense, 1971.
10 Park C. Y., Ha J. S., and Kim S. Y., "Aircraft Load Monitoring System Development & Application to Ground Tests Using Optical Fiber Sensors," Journal of The Korean Society for Aeronautical and Space Sciences, Vol. 45, No. 8, Aug. 2017, pp. 639-646.   DOI
11 MIL-STD-1553B - Aircraft Internal Time Division Command/Response Multiplex Data Bus, Department of Defense, 1978.
12 MSC.NASTRAN 2017 Linear Static Analysis User's Guide, MSC Software corporation, Nov. 2016.