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Deformation Monitoring and Inversion of Morphing Wing Trailing Edge Based on Smart Skin

Author: ZouJun
Tutor: WangBangFeng
School: Nanjing University of Aeronautics and Astronautics
Course: Measuring Technology and Instruments
Keywords: morphing wing smart skin monitoring system finite element simulation strain
CLC: V215
Type: Master's thesis
Year: 2012
Downloads: 78
Quote: 1
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Abstract

The wing has a great important influence on aircraft’s lift-drag ratio, ceiling speed,maneuverability, controllability and stability, economy and security, etc. In order to pursue higherperformance wing, the morphing wing technology which based on the smart structure has become theforefront of aviation technology’s development. A smart skin is introduced and a smart skin testsystem that based on STM32is designed in this paper, and morphing wing’s trail edge’s deformationmonitoring and inversion are studied within this paper.Firstly, a finite element simulation about skin’s substrates is operated, and a stress map of theskin surface which can provide a basis for subsequent experiments is given. Then, smart skinspecimens are manufactured, which is for testing the mechanical properties.Secondly, a smart skin test system that based on STM32is designed, whose hardware includingsignal conditioning circuits, TFLCD display module and the associated peripheral circuits. The goalof this system is to realize smart skin test data’s collection, storage and upload.Then, the output characteristics of those two kinds of smart interlayer are tested. The differencebetween the two is the different thickness of interlayer’s flexible substrates. Test results show that:those two kinds of interlayer’s sensitivity coefficients are less than strain foil, and the thicker theflexible substrates the greater impact on the smart interlayer sensitivity coefficient. Smart interlayersensitivity coefficient is inversely proportional with the thickness of flexible substrates. The outputcharacteristics of the skin test which use different gate length shows that, the measured strain of thelarge gate-length is smaller than the small gate-length’s result. Strain analysis shows that the strain ofwave crest is asymmetry, the closer to the peak apex the greater strain is, and so, experimental resultsand simulation results are identical.Finally, the relationship between morphing wing trailing edge and skin deformation is introduced,and a wing trailing edge deformation monitoring system which based on smart skin test system isdeveloped initially.

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