Synthetic Fatigue Life Extension Method for Fleet and Standalone

Abstract

The invention discloses a comprehensive fatigue life prolongation method for fleet and stand-alone planes. By analyzing the known design analysis test results and field data, the key parts of life extension are determined; damage control standards and repair measures are formulated for the key parts of life extension; Fatigue testing machine, repair the fatigue testing machine covering the repair measures of the key parts of life extension, complete the fatigue test of the whole machine of the fatigue testing machine after repair, verify the repair measures and life extension indicators; carry out fatigue and damage tolerance analysis on the non-life extension key parts , to assess life extension requirements. The invention has the following beneficial effects: the concept of the key parts of life extension is proposed, and different measures and requirements are adopted for the key parts and non-key parts of life extension, so that life extension is easy to implement; the unified repair plan formulated according to the fleet and considering the difference in damage of single machines, single machine Damage dispersion is eliminated or reduced and controlled; greatly reducing fatigue testing time, cost and risk.

Description

technical field [0001] The invention relates to the technical field of fatigue, in particular to the technical field of aircraft fatigue life extension. Background technique [0002] For aircraft life extension, there are mainly single aircraft life extension methods and fleet life extension methods. The single machine life extension method takes the single machine as the object, needs the complete load history data of the single machine service life, determines the actual service life, and then determines the life extension life. The fleet life extension method takes the fleet as the object, considers the flight load of a single aircraft, the operating environment, damage, and the dispersion of repair status, determines and verifies the life extension repair plan and life index that meet certain reliability indicators, and uses the same repair plan for each aircraft in the fleet. Control according to the same life index. [0003] However, for some aging aircraft that are ...

AI Technical Summary

Problems solved by technology

[0004] 1) The aircraft was designed earlier, without considering the structural inspectability, and the structure cannot be dismantled and difficult to inspect;

[0005] 2) The aircraft lacks flight parameter recording equipment, so it is impossible to determine the load history of a single aircraft;

[0006] 3) The range of use of the fleet is wide, the environment and load vary greatly, and the status of each stand-alone machine varies greatly;

[0007] 4) During the use process, the flight training program of the aircraft was adjusted, the use conditions were changeable, and after several overhauls, the state of the aircraft was quite different from the design expectation

Prolonging the life of the machine group has long cycle and high cost. At the same time, it faces inconclusive technical problems such as the selection of fatigue testing machine, dispersion coefficient, conversion of field service life and test life, and the huge risk of fatigue test of the whole machine.