Assembly method of complex components on large aircraft combining thermal deformation and gravity deformation

Abstract

The invention relates to a method for assembling complex components on a large aircraft that integrates thermal deformation and gravity deformation, and belongs to the technical field of large aircraft manufacturing. The attitude adjustment and positioning steps of the method include: (1) discretizing the key features on the complex part and its three-dimensional model into a key feature point set; (2) obtaining the coordinate values ​​of the key feature points on the two; (3) based on the assembly environment temperature , use the finite element analysis model to calculate the coordinate deviation of key feature points caused by temperature and gravity; (4) based on the acquired coordinate deviation, correct the coordinate values ​​of key feature points on complex parts; (5) based on the The corrected coordinate values ​​of the key feature points on the complex part and the coordinate values ​​of the key feature points on the 3D model are used to calculate the pose coordination matrix T for adjusting the pose of the complex part to the target pose. The method can effectively improve the assembly efficiency and precision of complex components on large aircraft, and can be widely used in the technical field of manufacturing large aircraft.

Description

technical field [0001] The invention relates to the technical field of assembly of large aircraft, in particular to a method for assembling complex components on a large aircraft, and thermal deformation and gravity deformation are integrated during the assembly process. Background technique [0002] In the assembly process of large aircraft, especially the assembly process of complex structural components on it, due to its large size, repeated adjustments and repairs are required during the installation process to meet the installation accuracy requirements. Aiming at this technical problem, the patent document whose publication number is CN107263044A discloses a design method of a large-scale aircraft outer wing box assembly system considering thermal deformation factors, and a leading edge Attitude adjustment and positioning system for components; in these existing technologies, based on improving the structure of the installation tooling, it is expected to solve the prob...

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Problems solved by technology

[0003] In the above scheme, based on the improvement of the tooling structure, although the problem of thermal deformation coordination between components and tooling can be solved, there are still measurement coordinates produced by thermal deformation and gravity deformation during the on-site installation of large aircraft The problem of deviation, especially the process of attitude adjustment and positioning of a single component or the first component during pose coordination (that is, the reference component referred to in the subsequent component installation process), plus a single component that needs attitude adjustment and positioning on a large aircraft Or the reference component is usually a complex structural component, and thermal deformation and gravity deformation will have a serious impact on its installation accuracy and efficiency. The process of attitude adjustment and positioning of components usually requires multiple adjustments and repairs

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