In order to study the dynamic performance of aircraft landing gear retraction and retraction, the dynamic model of an aircraft nose landing gear retraction and retraction mechanism was established by using ADAMS software; A dynamic simulation model of the landing gear hydraulic control system was established using AMESim. The hydraulic system includes the landing gear retraction actuator, end buffer device, various control valves, etc. Using ADAMS as the main control software and utilizing the interface module in AMESim, joint simulation of ADAMS and AMESim was achieved, comprehensively analyzing the working performance of the landing gear and hydraulic system, and verifying the reliability of the landing gear system"s collaborative work. We calculated and analyzed the effects of aerodynamic loads, control oil temperature, overload coefficient, and mid way reversing on the dynamic characteristics of landing gear deployment and retraction under different operating conditions. The research results indicate that increasing the overload coefficient will increase the load on the hydraulic actuator; Under low temperature conditions, the landing gear retraction speed slows down, but it can reduce the load fluctuations generated in the actuator; The increase in aerodynamic resistance leads to an increase in the time for the landing gear to retract; During the process of retracting the landing gear, the reverse direction occurs midway, and the earlier the reverse direction, the greater the impact load generated.