The invention relates to a
laser cladding
repair method for a lip crack of a
piston rod of an aircraft 300M steel
landing gear. The method comprises the following steps of 1, determining
laser repairprocess parameters by simulating stretching,
impact and fatigue performance experiments of the
piston rod, and meanwhile determining that the groove type of
laser cladding repair is V-shaped; 2, selecting a
simulation part before repairing, carrying out a
simulation part fatigue experiment, evaluating an experiment result, and determining a final laser cladding repair process; 3, carrying out laser repair on the crack of the
piston rod; 4, detecting a repair area of the
piston rod to find no crack and non-fusion defect after the repair is completed; and 5,
processing the repair area, recovering the size, and meeting the drawing or
assembly requirements. According to the laser cladding
repair method, the fatigue experiment is carried out on the
simulation part of the
piston rod to determinethe final repair process, it is guaranteed that the
piston rod do not crack in the long period of use, so that the safety use requirements of an aircraft in the service life period can be ensured.