Assembly method capable of achieving hole and bush extrusion strengthening twice

Abstract

The invention belongs to the field of squeezing and relates to an assembly method capable of achieving hole and bush extrusion strengthening twice. The assembly method comprises the steps that firstly, strengthening is conducted on a hole (4) for the first time by means of an extrusion bar (3) with certain extrusion capacity through an extrusion drawing gun (1); secondly, a bush (5) manufactured according to requirements is placed in the hole (4); and thirdly, strengthening is conducted on the hole (4) again by means of the extrusion bar (3) with certain extrusion capacity through the extrusion drawing gun (1), and assembly of the bush (5) is completed at the same time.

Description

technical field [0001] The invention belongs to the technical field of metal parts assembly, and relates to an assembly method for extrusion strengthening of a key hole of a key high-cycle fatigue life part of a helicopter and a liner extrusion strengthening assembly method. Background technique [0002] Helicopters are unsteady-state aircraft, and their main life-span parts, such as the lift system and the main reduction platform, are characterized by high load and high frequency, and the high-stress areas (fatigue fracture areas) of these parts are mainly in the holes. At present, our main treatment methods for this part are boring and grinding for hole processing, and temperature difference method for hole bushing assembly. As the weight, life and reliability requirements of helicopters increase, the disadvantages of this treatment method are gradually highlighted, and the weight and life cannot be balanced; the temperature difference assembly is prone to initial damage o...

AI Technical Summary

Problems solved by technology

As the weight, life and reliability requirements of helicopters increase, the disadvantages of this treatment method are gradually highlighted, and the weight and life cannot be balanced; the temperature difference assembly is prone to initial damage on the inner surface of the hole and is uncertain, reducing the reliability of key life parts. Sex, reduce the life evaluation conclusion of key life parts; after temperature difference assembly, the bonding force between the hole and the bushing is small, and the hole and the bushing are prone to fretting wear after the hole is stressed

Especially after a large number of TB6 titanium alloys and aluminum matrix composites are used in the main life parts of the helicopter lift system, due to the high sensitivity of TB6 titanium alloys to defects, the initial damage of aluminum matrix composites due to the low hardness of the body during temperature difference assembly The probability is relatively high, and the current processing method has initially been unable to meet the requirements of the new generation of helicopters for weight, life and reliability, and has become an uncertain factor affecting flight safety.

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