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.