Aircraft wing rib dynamics determination method based on formation superposition method
A technology of rib dynamics and determination method, which is applied in the field of aircraft wing rib structure design, and can solve problems such as difficulty in solving sensitivity
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[0033] like figure 2 As shown, the implementation steps of the present invention are specifically as follows:
[0034](1) Import the initial geometric model or finite element model of the aircraft wing rib, as well as the periodic excitation dynamic load under flight conditions;
[0035] (2) The initial geometric model of the aircraft wing rib is discretized as shown in figure 1 The finite element model composed of finite element elements is shown. If there is a finite element model, go to the next step directly;
[0036] (3) Determine the part of the wing rib structure of the aircraft that needs topology optimization, assign different attributes to the finite element elements in the finite element model in the step (1) to distinguish the parts that need to be optimized from the parts that do not need to be optimized, and then initialize the aircraft Pseudo-density value ρ of each element in the rib finite element model that needs to be optimized n , n is the number of fin...
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