Simulation Of Dynamic Characteristics Of Nose-wheel Turning And Shimmy Suppression For Large Civil Aircraft

Aircraft landing gear is an important component of aircraft for parking on the ground, taxiiing,take-off，landing and dissipating the impact energy to ensure the safty of aircraft during taxiing,take-off，landing and good handling as well as stability. Good handling requirs aircraft to achieve180°turning on runway(360°for carrier-based planes). Good stability requires that nose-wheelshimmy phenomenon does not occur,even if wind or other lateral loads were loaded on the aircraft.In this paper, firstly, nose landing gear and main landing gear were build respectively inADAMS/aircraft, with one large civil aircraft as the example.Secondly,full aircraft was build usingthose systems and inherent rigid fuselage of ADAMS/aircraft. After the simulation of ground glide,the relationship between glide speed and maximal control angle as well as the minimum turningradius under different glide speed were given.For current common piston shimmy-damper，this paperanalyzes the principle of the produce of damp force.Then，the damping coefficient of a certainshimmy-damper was calculated.After the simulation of nose-wheel shimmy suppression，an effectiveminimum damping coefficient which can stop nose-wheel shimmy were given. For some structureparameters，after the analysis of its influence to the damping coefficient,the revision opinions weregiven.