WING MODEL FOR STATIC AEROELASTICITY WIND TUNNEL TEST

A wing model for static aeroelasticity wind tunnel test belongs to the technical ﬁeld of aeroelasticity tests.In the wing model, the model steel joint and the spar frame are connected 5 with the composite material skin. The spar frame is of structure having two main beams and a single auxiliary beam...

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Bibliographische Detailangaben
Hauptverfasser:	XINYU AI, WEIZHE FENG, SHAOJIE GE, WEI QIAN, LING XIAO, XING LI
Format:	Patent
Sprache:	eng
Schlagworte:	AIRCRAFT AVIATION COSMONAUTICS DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING ORREPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLYADAPTED FOR USE IN CONNECTION WITH AIRCRAFT HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFTCOMPONENTS, NOT OTHERWISE PROVIDED FOR MEASURING PERFORMING OPERATIONS PHYSICS TESTING TESTING STATIC OR DYNAMIC BALANCE OF MACHINES ORSTRUCTURES TESTING STRUCTURES OR APPARATUS NOT OTHERWISE PROVIDED FOR TRANSPORTING
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Beschreibung
Zusammenfassung:	A wing model for static aeroelasticity wind tunnel test belongs to the technical ﬁeld of aeroelasticity tests.In the wing model, the model steel joint and the spar frame are connected 5 with the composite material skin. The spar frame is of structure having two main beams and a single auxiliary beam. The piezometer wing ribs are arranged among the spar frame and the plurality of supporting wing ribs. The embedded piezometer tubes are arranged in the piezometer wing ribs, the lightweight filling foam is arranged among the spar frame and the plurality of supporting wing ribs. An outer surface of a frame segment formed by the lightweight filling 10 foam, the plurality of supporting wing ribs, the piezometer wing ribs and the spar frame is covered with the composite material skin. The frame segment is assembled on the model steel joint to form the wing model for the static aeroelasticity wind tunnel test. The wing model for a static aeroelasticity wind tunnel test has high-precision aerodynamic shape and high-strength loading capacity. The changes in the pressure distribution of the required wing section can be 15 measured in real time during the wind tunnel test. The wing model realizes the integration of force and pressure measurement of the static aeroelasticity model, and obtain accurate aerodynamic data when the wing model is deformed under force. FIG]