Rapid design and management method for spacecraft device installation fasteners

Abstract

The invention relates to a rapid design and management method for spacecraft device installation fasteners. According to the requirements for the selection range of all kinds of spacecraft device installation standard fasteners, the selection range of the spacecraft device installation fasteners is determined, a spacecraft device installation standard fastener database is established, and the installation forms of the spacecraft device installation fasteners are summarized; according to the parameters including device installation apertures, the depths of mounting holes, the installation forms, the types of the fasteners and the thicknesses of mounting plates, an algorithm for basic parameters of the device installation fasteners is established, a fastener data sharing platform based on a three-dimensional light-weight model is established with mechanical interface information of a stand-alone device as a data foundation for automatic calculation of device fastener parameters, automatic matching of specifications, parametric design and automatic assembly of the three-dimensional light-weight model and visual inspection of fastener design results. As a result, the working efficiency of fastener design is improved, and the uniqueness and correctness of data are guaranteed.

Description

technical field [0001] The invention belongs to the field of mechanical design and mechanical matching, and relates to a rapid design of fasteners installed in equipment and a management method based on process information. Background technique [0002] The connection design using fasteners is a common mechanical assembly method for spacecraft products. Fasteners widely used in the assembly design of manned spacecraft mainly include screws (bolts), nuts, washers, etc. There are more than 11,000 fasteners in China. The design, procurement, final assembly and management of fasteners is a systematic project that runs through the entire life cycle of the spacecraft from design to matching, to final assembly, to inspection, to in-orbit operation. [0003] Spacecraft design is a knowledge-intensive system engineering, including the joint participation of several subsystems, and the stand-alone equipment of each subsystem is developed by different research and development units. ...

AI Technical Summary

Problems solved by technology

[0011] 1) There is no strict specification for the length of screws (bolts). Due to different personal design habits and experiences, even if the same type of equipment is assembled and designed, the lengths of screws (bolts) given by different people will be different, resulting in too many types of screws (bolts). ;

[0012] 2) Since there is no three-dimensional interference simulation design, it is impossible to check whether there is interference, and it is impossible to judge in advance the accessibility during the implementation of the final assembly, such as whether the operation space, force measurement space, fastener fall-off method and space meet the requirements;

[0013] 3) Not only the design and calculation of fasteners is cumbersome, but also the statistics and summary of fasteners are heavy workload, low efficiency, and high error rate;

[0014] 4) The stand-alone equipment development unit, structural layout and final assembly design department, procurement department and general assembly implementation department lack unified data transmission and information sharing in the process of "single machine design-structural layout and final assembly design-fastener procurement-final assembly implementation", It seriously affects the design efficiency and restricts the digitalization, informatization and integration process of design-supporting-assembly

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