Loading tool system for axle pressure experiment of spaceflight cylindrical shell

Abstract

The invention provides a loading tool system for an axle pressure experiment of a spaceflight cylindrical shell, and belongs to the field of experiment tool design of a main bearing member of an aviation and spaceflight structure. The tool system mainly comprises a tool pedestal, a tool pedestal switching frame, a bidirectional actuator, an approximate rigid connection column, a force sensor, a limiting block, a loading cap and an experimental switching ring. The tool system is simple in principle, simple in loading control, compact in structure, and small in occupation space, a loading system is independent from a measuring system, and a measuring space is ensured to the largest extent. The installation sequence is changed to realize switching between an axle pressing condition and an axle pulling condition simply, and the tool system can fully ensure that load distribution is uniform and accurate.

Description

technical field [0001] The invention relates to the field of experimental tooling design for main load-bearing components of aerospace structures, and proposes a loading tooling system for aerospace shell axial compression experiments. Background technique [0002] my country is stepping up the demonstration and development of a heavy-duty launch vehicle with a core diameter of 8.5 meters and a carrying capacity of 100 tons. The heavy-duty launch vehicle takes off and lifts the thrust, so that the grid-reinforced panel faces high mechanical service performance requirements to withstand huge axial compression loads, and the load-bearing capacity of the panel is more sensitive to the initial geometric defects, which leads to the actual bearing capacity of the structure being lower than that based on perfect The model predicts a much smaller structural capacity, a property described by a reduction factor much smaller than 1. Traditional structural weight reduction design metho...

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Problems solved by technology

[0005] The present invention mainly solves the problem of the experimental verification of the static strength and stiffness of the main load-bearing structure of the main load-bearing structure of the rocket body section in my country and the experimental verification of the new method of the urgently needed reduction factor, and proposes a loading tool for the axial pressure test of the aerospace shell system to realize the purpose of precise loading of the axial load in the axial compression and axial tension experiments of the cylinder shell

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