Wind tunnel test data static aeroelastic correction method, device and equipment, and medium
A technology for aero-elastic correction and wind tunnel testing, applied in the field of aviation wind tunnel testing, can solve the problems of lack of multiple iterative couplings, deviation of model deformation results, etc.
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Embodiment 1
[0031] figure 1 It is a flow chart of the wind tunnel test data static air bomb correction method provided by Embodiment 1 of the present invention. This embodiment can be applied to the wind tunnel test of civil passenger aircraft. The swept wing of the test model generates static air under the action of aerodynamic force. In the case of elastic deformation, the method specifically includes the following steps:
[0032] Step 110 , based on the three-dimensional structured fluid grid of the wing test model, perform fluid dynamics numerical simulation to obtain aerodynamic load data on the surface of the wing test model.
[0033] The output file of the fluid dynamics numerical simulation software contains aerodynamic load data and three-dimensional structured fluid grid information, and the three-dimensional structured fluid grid includes information such as x, y, z coordinates and i, j, k coordinates of each node of the grid. Therefore, the aerodynamic load data on the surfac...
Embodiment 2
[0047] figure 2 It is a flow chart of the static aeroelastic correction method for wind tunnel test data provided by Embodiment 2 of the present invention. This embodiment is embodied on the basis of the above-mentioned embodiments. Such as figure 2 As shown, Embodiment 2 of the present invention provides a static aeroelastic correction method for wind tunnel test data, including the following steps:
[0048] Step 210, based on the digital model of the wing test model, generate a three-dimensional structured fluid grid and a geometrically nonlinear structural finite element model of the wing test model.
[0049] The digital model of the wing test model is the digital model used in the processing of the wing, which fully reflects the internal structural characteristics of the wing test model. According to the digital model of the wing test model, it can be used to construct the three-dimensional structure of the wing test model A geometrically nonlinear structural finite el...
Embodiment 3
[0097] Figure 4 A structural schematic diagram of a static aeroelastic correction device for wind tunnel test data provided by Embodiment 3 of the present invention, which can be used for static aeroelastic deformation of the swept wing of the test model in the wind tunnel test under the action of aerodynamic force, Furthermore, it is necessary to test the static aeroelastic correction of the wind tunnel test data, so as to reduce the deviation of the static aeroelastic correction of the wind tunnel test data. The device can be realized by software and / or hardware.
[0098] Such as Figure 4 As shown, the device includes: a first execution module 410, a numerical analysis module 420 and a second execution module 430, wherein,
[0099] The first execution module 410 is used to perform fluid dynamics numerical simulation based on the three-dimensional structured fluid grid of the wing test model, and obtain the aerodynamic load data on the surface of the wing test model;
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