Multi-operating-condition failure load based composite structure uncertainty optimization method
A composite material and optimization method technology, applied in design optimization/simulation, special data processing applications, instruments, etc., can solve problems such as conservative structure and large safety factor, achieve good fatigue resistance and improve efficiency
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[0089] In order to fully understand the characteristics of the invention and its applicability to engineering practice, the invention optimizes the design of the proposed aircraft composite material stiffened panel wall panel structure. The aircraft skin rib panel is subjected to two load conditions, namely compression condition and shear condition, the design loads are 98kN and 121.0kN respectively, and the safety factor is 1.1. The model and loading conditions are as follows Figure 1-Figure 4 shown.
[0090] The composite material adopts carbon fiber fabric material, and the interval boundaries of its properties are listed in Table 1.
[0091] Table 1 Interval boundaries of uncertain variables
[0092] elastic parameters
lower bound
Upper Bound
Intensity parameter
lower bound
Upper Bound
E. 1 (GPa)
43 . 859
62 . 112
x t (MPa)
417.131
542.420
E. 2 (GPa)
43 . 85 9
62 . 112
x c (MPa)
120 . 781
...
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