Multi-discipline uncertainty propagation analysis method based on Newton iteration
An uncertainty and Newton iteration technology, applied in the field of multidisciplinary uncertainty propagation analysis based on Newton iteration, can solve problems such as large errors, reduce calculation time, save calculation costs, and reduce dependencies
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Embodiment 1
[0047] In order to fully understand the characteristics of the invention and its applicability to engineering practice, the present invention uses a two-discipline coupling system to carry out uncertainty propagation analysis, and the relationship between variables is expressed as:
[0048]
[0049] Table 1 shows the uncertainty information of the input parameters in the embodiment. In this embodiment, four deviation coefficients of 0.025, 0.050, 0.075, and 0.100 are used for calculation, and the analytical solution is used as a comparison, and the fixed point Iterative methods were compared with sensitivity-based methods.
[0050] Table 1
[0051]
[0052]
[0053] The specific results are shown in Table 2:
[0054] Table 2
[0055]
[0056] It can be seen from Table 2 that the results obtained by the multidisciplinary uncertainty propagation analysis method based on fixed point iteration have serious interval expansion, which is not applicable to some problems. M...
Embodiment 2
[0058] In order to fully understand the characteristics of the invention and its applicability to engineering practice, the multidisciplinary uncertainty propagation analysis method based on Newton iteration is used to verify its effectiveness through a typical wing static aeroelastic problem. For a rigid wing in incompressible flow, the up and down translation of the wing has no effect on the aerodynamic moment, so the problem can be simplified as Figure 4 The model shown. In this embodiment, the angle of attack and aerodynamic moment of the wing are coupled state variables, and the multidisciplinary analysis model can be written as:
[0059]
[0060] where M 0 is the zero-lift moment, α is the angle of attack of the wing, α 0 is the zero-liter angle of attack, is the lift line slope, q is the incoming flow pressure and ρ is the air density, v is the incoming flow velocity, e is the distance from the aerodynamic center to the elastic axis, K α is the stiffness of t...
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