Quick design optimization method for large structure

Abstract

The invention discloses a quick design optimization method for a large structure. The quick design optimization method comprises the following steps of 1, acquiring overall basic parameters and determining structure configuration according to the acquired overall basic parameters; 2, acquiring a loading condition, and calculating an equivalent axial load of the large structure according to the most harsh working condition; 3, optimizing the structure configuration by using an analytic method optimization design algorithm, namely setting an initial condition according to the equivalent axial load, selecting weight, a remaining strength factor or rigidity as a criterion through a formula, and performing iterative optimization on the structure configuration to obtain a plurality of groups of optimal parameters; 4, selecting proper optimal parameters to establish a wireframe model used for strength finite element analysis and a skeleton model for main structure modeling; 5, performing three-dimensional digital prototype modeling according to the wireframe model and the skeleton model.

Description

technical field [0001] The invention relates to the technical field of modeling, in particular to a fast design optimization method for large structures. [0002] Background technique [0003] In the existing technology of structural modeling in the aerospace field, the common method is to design each component first, and then carry out the overall assembly coordination after completing the design of the components. The advantage of this modeling method is that each model is independent, the requirements for machine configuration are low, and the requirements for personnel design ability are low. The disadvantage is that the design process lacks an overall concept, the modeling is not standardized, and the modification workload is heavy when external conditions change. The application of this design method has certain limitations in the aerospace field that requires strict design standardization, refinement, and rapidity. [0004] In the structural system of the launch veh...

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Problems solved by technology

[0004] In the structural system of the launch vehicle, there are nearly 20 compartments with independent functions and requirements. If the traditional modeling design method is used, the modeling cycle is long and the modification is difficult. Moreover, the modeling of each compartment is not standardized, and the structural matching is poor, which seriously affects work efficiency

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