Actually measured data-based spacecraft component assembly simulation method

Abstract

The invention discloses an actually measured data-based spacecraft component assembly simulation method. The assembly simulation method includes the following steps that a parametrized three-dimensional rapid modeling method is utilized to generate actually measured dimension-based three-dimensional small component models after final assembly inspection personnel actually measure and input the dimensions of key small component interfaces into a corresponding parametrized three-dimensional modeling system; a reverse point cloud curved surface fitting method is utilized to convert the surface shapes of real objects of large key components into discrete geometric coordinate points, and on the basis, the modeling of complex curved surfaces is carried out, so that reverse three-dimensional digitalized models of the large key components are formed; the assembly process is simulated and analyzed; ergonomics is simulated and evaluated. By combining a virtual reality scene with reverse real object modeling, the actually measured data-based spacecraft component assembly simulation method disclosed by the invention detects interference points and risk sources in advance to find out assembly incoordination and other problems, thus increasing the reliability of the final spacecraft assembly process and the efficiency of final assembly.

Description

technical field [0001] The invention relates to the field of assembly, in particular to an assembly simulation method for spacecraft components based on actual measurement data. Background technique [0002] During the satellite assembly process, due to the influence of manufacturing and assembly errors, thermal control multi-layer coating implementation, design changes and other factors: ① There are certain differences between the appearance of large antennas, large payload equipment and other components and the theoretical design values, which may easily lead to Insufficient operating space during the actual installation process or interference with peripheral equipment; ② Small components such as satellite instruments and equipment, pipelines, cables, and corresponding directly affiliated parts are prone to mismatch with the interface on the cabin due to interface coordination problems. At present, the above problems are usually solved by physical trial assembly. The limi...

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Problems solved by technology

[0002] During the satellite assembly process, due to the influence of manufacturing and assembly errors, thermal control multi-layer coating implementation, design changes and other factors: ① There are certain differences between the appearance of large antennas, large payload equipment and other components and the theoretical design values, which may easily lead to Insufficient operating space during the actual installation process or interference with peripheral equipment; ② Small components such as satellite instruments and equipment, pipelines, cables, and corresponding directly affiliated parts are prone to mismatch with the interface on the cabin due to the problem of interface coordination

At present, the above problems are usually solved by physical trial assembly. The limitations of this method are: ① it takes up a lot of man-hours, which leads to the delay of the development progress; ② there are quality risks, especially the trial assembly of large components, which is prone to interference and damage Other star products

[0004] However, the assembly simulation objects of the above-mentioned various systems and methods all use theoretical design models, lacking actual product shape and size data, and the assembly process scheme obtained by simulating the assembly process based on the theoretical shape data often cannot reflect the actual situation, and the guiding significance is limited.

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