Module-based static testing method for large multi-module spacecraft structure

Abstract

A module-based static testing method for a large multi-module spacecraft structure. The method comprises: decomposing a large multi-module spacecraft into a plurality of modules according to connection interfaces, and performing load testing and envelope analysis on each individual module to determine a load condition for the module; superimposing an acceleration load of test conditions with the mass of a loaded part of the module to determine the stress of a loading point, and establishing a finite element model for analysis, wherein the stress of a root part under an actual load is less than or equal to the actual load on the module, and a local loading stress envelopes an actual state stress; performing finite element analysis on a tooling design to confirm that tooling transmits the actual load; and performing a static load test, and completing the test.

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