Landing gear is an important component of the aircraft structure, subjected to both static and random vibration loads during operation. This study presents a method for evaluating the fatigue life of landing gear under complex, multivariate loading conditions. The study combines classical techniques (Miner’s rule, Rainflow counting) with numerical simulation to analyze aircraft landing gear. Finite element analysis (FEA) was performed in ANSYS on a CAD model developed in SOLIDWORKS to determine the stress distribution, displacement, and lifespan. Miner’s rule was used to calculate the cumulative damage, considering the S-N curve of the landing gear material (AL7075-T6) and the FALSTAFF load spectrum. The analysis results show that under static loading, the landing gear of the MALE UAV experiences the highest stress during landing, reaching 37.55 MPa, but remains within the safety limit with a service life of 1.025e7 cycles. Under random vibration loading, the landing gear achieves a fatigue life greater than 17,983 h. This method enables the assessment of damage accumulation on the landing gear, supporting optimization, repair, and maintenance processes.