Adhesive joint assembly integrated structure for antenna supporting truss and aluminum honeycomb plate

Abstract

The invention provides an adhesive joint assembly integrated structure for an antenna supporting truss and an aluminum honeycomb plate. The adhesive joint assembly integrated structure comprises a supporting truss, a first stringer assembly, a supporting rod, a supporting plate, a second stringer assembly and a bottom plate, wherein the supporting truss comprises a rod part as well as a supporting joint and a mounting joint arranged on the rod part; the first truss assembly comprises a plurality of first stringers, ends of the first stringers are connected with the supporting joint, and the other ends of the first stringers are equipped with stringer joints; one end of the supporting rod is connected with the mounting joint, and the supporting base is arranged at the other end of the supporting rod; the supporting plate is fixed with the mounting bases through the stringer joints; the second stringer assembly comprises a plurality of second stringers, ends of the second stringers are connected with the stringer joints, and the other ends of the second stringers are equipped with supporting bases; and the bottom plate is arranged on the supporting bases. The adhesive joint assembly integrated structure has the following innovative design: the carbon fiber antenna supporting truss and the aluminum honeycomb plate are integrally designed, and the honeycomb plate structure is introduced, so that torsion rigidity of the structural form of the truss honeycomb plate is greatly improved.

Description

Technical field [0001] The invention relates to an aerospace vehicle structure, in particular to an antenna support truss and aluminum honeycomb panel glued assembly integral structure capable of carrying a large number of payloads. Background technique [0002] At present, the carbon fiber truss structure in the spacecraft structure is simply composed of joints and rods, and the joints and rods are connected by bolts or glued. This kind of pure truss structure has the following shortcomings: [0003] 1) The truss structure is relatively simple, and the truss as a whole mostly relies on the space diagonal rods to resist torsion, and the torsional stiffness of the truss is low; [0004] 2) Insufficient utilization of the internal space of the truss, only the external plane of the truss can provide installation bearing for the effective load, and the utilization efficiency is low; [0005] 3) The truss gluing assembly method is simple and the assembly accuracy is limited, which can no ...

AI Technical Summary

Problems solved by technology

[0003] 1) The truss structure is relatively simple, and the truss as a whole relies on space cable-stayed members to resist torsion, and the torsional stiffness of the truss is low;

[0004] 2) The utilization rate of the internal space of the truss is insufficient, and only the external plane of the truss can provide the installation load for the payload, and the utilization efficiency is low;

[0005] 3) The truss glued assembly method is simple and the assembly accuracy is limited, which can no longer meet the requirements of high-precision resolution satellites

[0006] The above deficiencies largely limit the application and popularization of truss structures in spacecraft structures.

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