In order to verify the performance of the designed electrical landing gear, which is used for adaptive landing of helicopters, the kinematics of the equipment is calculated and analyzed. The working space of the landing gear is simulated by Monte Carlo method, and the landing swaying angles which the landing gear can adapt to are analyzed. Finally, simulations are carried out to the nose landing gear. A motion trajectory is given, and the simulated motion in ADAMS is compared with the planning trajectory, and to prove the precision of the kinematics calculation. This research can validate the flexibility and adaptability of the designed landing gear, and lay a foundation for the motion control of helicopters’ adaptive landing.