Design Of Dual Actuator Nose Wheel Steering Mechanism For Large Civil Aircraft And Analysis Of Handing Stability

The nosewheel steering technology as the core of the aircraft ground handling, the importance isself-evident. With the vigorous development of large civil aircraft in recent years, in order to meet thedevelopment of C919and technical reserve of follow-up models, it is advisable to launch the designand application work of the nosewheel steering system with two actuacors which can sastify the civilaircraft’s demand ensuring it can turn with large steering angle and turning moment, which cancontribute to increase our country’s marketability of large aircraft with proprietary intellectualproperty rights and is of great significance for the success of our country’s large civil aircraft.In this paper, set double actuated drum nose wheel steering system as the research object,research on nosewheel steering technology from steering mechanism design、turning test programdesign and front wheel steering stability. First, both static and dynamic torque are designed, thencombined the results of the preliminary design, its engineering design. And analysis dynamic strengthof mainly hosted ear piece based on Lms Virtual.lab Motion and Nastran. At the same time, carry outthe function validation test program design of nose wheel steering, which focused on the layout of thetest platform, the test system design, engineering design platform. And static strength analysis for thetest fixture is done to ensure security of the test, which laying a solid foundation for production andturning test.The front wheel steering stability under the influence of the asymmetric load is mainlyresearched, according to the aim theory and PID control technology, using Amesim softwareestablished pilot direction control model, using Lms.Virtual. Lab Motion software established thevirtual prototype of the plane, by defining the input variables (nose wheel corner) and output variables(lateral displacement、 velocity), realized the research on lateral stability of an aircraft byLms.Virtual.Lab Motion and Amesim.The results show that this system has a corrective effect to agreat degree of control the lateral offset of the aircraft; by comparing the numerical solution withunited simulation, both basic meet, which has verified the feasibility of this closed-loop controlsystem to simulate the aircraft by the dynamic response of asymmetric loads. Lay the foundation forresearching on the ground operation stability characteristics under the influence of the asymmetricload, and the intelligent control system also included.