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Aircraft landing gear steering system is the key role in modern aircraft’s ground control,which is directly relateded to the safety of aircraft taking off and landing. Now, the main research about landing gear of aircraft has been foused on landing buffering, vibration attenuating ,safety and reliability,and anti-skid braking system,but has a little about aircraft’s nose wheel steering system.In this paper, The problem has been explored, that the turning angle of this system has bad tracking during aircraft taking off and landing.First, the principles of the aircraft nose wheel steering system,which includes mechanical subsystem, control subsystem and hydraulic subsystem are introduced,and the characteristic of aircraft’s ground manavers and the principles of hydraulic drive system are studied. and then,the physical model of nose wheel steering system based on multi-domain physical modeling language Modelica is made by software Dymola.which can analyze the dynamic performance exactly.Second, the principles of robust design including Taguchi method,Response Surface Mothodology,Tolerance Design are introduced for the problem of aircraft nose wheel steering system, then the objective of the robust design is defined. The parameters which has a greater impact for steering system can be selected by the method of Taguchi and the software of Matlab, the certain optimist level of this factors can be made. Then, the Response Surface Mothodology based on the result of Taguchi method is carried out, The tolerance design is used to get the robust result lastly.Finally, the result of optimization can be analyzed and verified by Monte Carlo analysis in this paper. The turning angle has good tracking after the robust design, which meets the requirement.The research result of aircraft nose wheel steering system provide the principles and method for the research of aircraft landing gear,which have some practical value.
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