• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.40 no.2
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• pp.165-170
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• 2012

This paper contains the test method to obtain aerodynamic hinge moments acting on the control surface of air vehicle wing. During the flight, hinge moments make difference between actual control surface angle and control angle which is measured by sensor of actuator. The hinge moments can be obtained by using this difference. Static ground load test and calibration test were conducted to obtain torsional stiffness of control surface actuation system. This results are used to calculate hinge moments. In addition, the mechanical errors of actuation system such as slip angle of mounting point and backlash could be estimated. Using flight test results, this experimental measurement method of hinge moment acting on control surface is conducted. The results of this method are similar to those of numerical simulation method, and the validity of this method is proved.

• Journal of the Korea Institute of Military Science and Technology
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• v.19 no.4
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• pp.476-482
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• 2016

In this study, a method using single Wheatstone bridge flexure has been presented to measure hinge moment acting on control surfaces of wind tunnel models. The structural simplicity of the flexure reduces difficulty regarding gauging and wire-routing, and also makes it feasible to install flexures even inside thin wings. Some flexures were designed and fabricated under typical aerodynamic loads in wind tunnel test, and the strains on the flexure according to applied loads were compared with the result of the analysis by finite element method. The relation between applied loads and output signals showed good linearity, and the standard deviation on the residual errors from linear equation obtained by least square method was within 1.0 % of the maximum design moments. In addition, the FEM analysis on the thickness of load-connecting part of the flexure showed that the sensitivity was improved as the thickness became thin as much as desired to avoid buckling.