Rational approximate optimization method for unsteady aerodynamic load of aerodynamic servo elastic system
A technology of aerodynamic load and servo elasticity, which is applied in the direction of file system, file system type, design optimization/simulation, etc., can solve the problem of strong empirical constraints, unsatisfactory fitting effect of generalized unsteady aerodynamic coefficient matrix, and poor fitting effect. Ideal and other problems to achieve the effect of reducing the numerical fitting error
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[0157] like Figures 1 to 8 As shown, the present embodiment is a process of processing the generalized unsteady aerodynamic coefficient matrix of a thin-walled wing structure with a large aspect ratio, and the present invention is further described in conjunction with the accompanying drawings and embodiments.
[0158] Step I, take out the CAD digital model data of the wing structure from the CATIA software. The geometric shape and internal skeleton structure of the UAV are as follows: figure 2 As shown, it can be divided into central wing, left and right outer wings, and the split points are A3L and A3R. The positions of key points are marked in the figure. The model is symmetrical about the midplane A0-B0. Table 1 shows the size parameters of the right half wing, and its half-span length is 8900mm.
[0159] Table 1 Wing plane dimension parameters
[0160] Location Length (mm) Location Length (mm) A0-B0 937.00 B31R-B32R 272.00 A1R-B12R 2141...
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