Static aeroelasticity wind tunnel test wing model

Abstract

The invention discloses a static aeroelasticity wind tunnel test wing model, and belongs to the technical field of aeroelasticity tests. According to the wing model, a model steel connector and a wingbeam frame are connected with a composite material skin, the wing beam frame is of a beam frame structure with double main beams and a single auxiliary beam, pressure measuring wing ribs are arrangedin the wing beam frame and a plurality of supporting wing ribs, embedded pressure measuring pipes are arranged in the pressure measuring wing ribs, and light foam is arranged between the wing beam frame and the supporting wing ribs. The outer surface of a frame section jointly formed by light foam, a plurality of supporting wing ribs, pressure measuring wing ribs and a wing beam frame is coveredwith a composite material skin to be loaded on a model steel joint to form a static aeroelasticity wind tunnel test wing model. The aerofoil model has high-precision aerodynamic configuration and high-strength bearing capacity, can measure the change condition of required aerofoil profile pressure distribution in real time in the wind tunnel test process, realizes integration of force measurementand pressure measurement of a static aeroelastic model, and can obtain accurate aerodynamic force data in a state that the model is stressed to deform.

Description

technical field [0001] The invention belongs to the technical field of aeroelasticity test, and in particular relates to a static aeroelastic wind tunnel test wing model integrating force measurement and pressure measurement. Background technique [0002] The traditional static aeroelastic wind tunnel test wing model generally does not have the ability to measure pressure, and there is no specific accuracy requirement for the shape. It is only used to study the static aeroelastic characteristics of the model, and does not have the ability to measure real-time pressure distribution data during the wind tunnel test. capability and value. With the continuous development of large-aspect-ratio wing technology, the static aeroelastic effect has become increasingly prominent, and researchers' requirements for the accuracy of aerodynamic data are also constantly increasing. By measuring the real-time pressure distribution data of the static aeroelastic model during the wind tunnel ...

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Problems solved by technology

[0002] The traditional static aeroelastic wind tunnel test wing model generally does not have the ability to measure pressure, and there is no specific accuracy requirement for the shape. It is only used to study the static aeroelastic characteristics of the model, and does not have the ability to measure real-time pressure distribution data during the wind tunnel test. ability and value

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