An aircraft cardan shaft remanufacturing and repairing process

Abstract

The invention relates to the technical field of repairing cardan shafts of aircraft horizontal tail control systems, and particularly relates to an aircraft cardan shaft remanufacturing and repairingprocess. The process includes (1) removal of an original plating, (2) hydrogen removal, (3) measurement, (4) defect removal, (5) grinding after-treatment, (6) cleaning, (7) protection, (8) surface pretreatment, (9) preheating before spraying, (10) component spraying, (11) coating processing, (12) grinding after-treatment and (13) surface treatment. The process solves a problem that a high number of components are scrapped because aircraft cardan shafts cannot be repaired due to inner pore abrasion and scratches. Through selection and preparation of a wear-resistant coating, inner pore wear resistance after a cardan shaft is repaired is greatly improved and service lifetime of components is prolonged.

Description

technical field [0001] The invention relates to the technical field of repairing a cardan shaft of an aircraft horizontal tail control system, in particular to a process for remanufacturing and repairing an aircraft cardan shaft. Background technique [0002] The cardan shaft is an important part used to transmit the load of the actuator in the aircraft's horizontal tail control system. Due to the high frequency of use and the large transmission load, damage is inevitable. Among them, the wear and scratch of the inner hole are the most important forms of damage. It accounts for more than 70% of the total scrapped parts. At present, there is no good repair method for the damage of this type of cardan shaft. Most of the replacement methods are used to meet the functional requirements of the system. Performance, processing size and shape accuracy have high requirements, the manufacturing process is complicated, the processing pass rate of parts is low, and the replacement cost ...

AI Technical Summary

Problems solved by technology

[0002] The cardan shaft is an important part used to transmit the load of the actuator in the aircraft's horizontal tail control system. Due to the high frequency of use and the large transmission load, damage is inevitable. Among them, the wear and scratch of the inner hole are the most important forms of damage. It accounts for more than 70% of the total scrapped parts. At present, there is no good repair method for the damage of this type of cardan shaft. Most of the replacement methods are used to meet the functional requirements of the system. Performance, processing size and shape accuracy have high requirements, the manufacturing process is complicated, the processing pass rate of parts is low, and the replacement cost is high

[0003] For the wear and scratch damage of the cardan shaft inner hole, welding and electroplating have been used to repair the damage. The welding process is difficult to control the local temperature and the heat input is high, which is easy to cause local deformation of the parts and be scrapped; the electroplating process is due to Poor dispersibility of the solution in the hole, it is difficult to obtain a uniform thickness and fine coating, and even chromium tumors will be generated at the port, and repeated rework will increase the risk of hydrogen embrittlement failure of the part

Aiming at the problems of large heat input, poor repair layer uniformity, and poor process stability in the traditional process, this method adopts an angled explosion spraying method to control the heat input during the repair process to ensure the uniformity of the repair layer, and through grinding Cutting and grinding methods to ensure the final size and surface roughness of the parts

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