Non-probability credible reliability topological optimization design method for aircraft structure
A topology optimization and design method technology, applied in design optimization/simulation, special data processing applications, geometric CAD, etc., can solve problems that need to be deepened, lack of credible evaluation, and distribution rules cannot be obtained, so as to improve the rationality Effect
Inactive Publication Date: 2021-01-05
BEIHANG UNIV
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Problems solved by technology
However, considering the unavoidable uncertainty effects in the actual aircraft design and use process, conventional deterministic analysis and optimization methods are no longer applicable, and it is urgent to develop innovative design processes and methods driven by reliability constraints
Combined with the complex service environment and limited sample data fa
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[0030] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.
[0031] Such as figure 1 As shown, the present invention proposes a non-probabilistic credible reliability topology optimization design method for aircraft structure, comprising the following steps:
[0032] (1) According to the aircraft's complex service environment and structural material properties, select uncertain parameters describing structural characteristics or external loads, such as the structural overall stiffness interval matrix K I ,...
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The invention discloses a non-probabilistic credible reliability topological optimization design method for an aircraft structure. According to the method, non-probability credible reliability topological optimization design is carried out for an aircraft structure under the conditions of a complex service environment and a limited sample by fully considering the influence of uncertainty parameters such as structural elastic parameters and loads. The method comprises the following steps: firstly, establishing a non-probabilistic credible reliability constraint index under a given credibility level, and then obtaining an optimal configuration of a structure under given load and boundary conditions through iteration by taking the structure quality as an optimization target, taking the relative density of a unit as a design variable and adopting a moving asymptotic optimization algorithm. According to the method, the influence of uncertainty on structural configuration under the conditionof limited test samples is reasonably represented in the topological optimization design process, and both safety and economy are considered.
Description
technical field [0001] The present invention relates to the technical field of structural topology optimization design, in particular to a non-probabilistic credible reliability topology optimization design method for an aircraft structure, which takes into account the elastic modulus of materials, structural external loads and allowable displacements under a given degree of reliability The non-probabilistic credible reliability index is established, and the topology optimization of the aircraft structure is carried out based on the SIMP interpolation model. Background technique [0002] With the rapid improvement of the level of science and technology, computer technology and equipment manufacturing capabilities, the design concept of advanced aircraft structures in the future will undergo tremendous changes. As the front end of the entire design, the optimization of the overall layout scheme of the aircraft structure has a profound impact on the subsequent detailed design,...
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Login to View More IPC IPC(8): G06F30/15G06F30/23
CPCG06F30/15G06F30/23
Inventor 王晓军倪博文李云龙王磊
Owner BEIHANG UNIV