Design And Experimental Verification Of All-electric Aircraft Nose Wheel Steering System

Aircraft landing gear is an important part of the aircraft.The aircraft wheel control technology is thecore of the modern aircraft ground controlling. With the development of the aircraft technology, recentlyother contries put forward the design idea of "more or all-electric drive", which means simple structures,less weight, much reliability, less cost. So the all-electric aircraft, would have widely prospects both inmilitary and civilian in the coming days. As the all-electric technology could be applied to the unmannedaerial vehicles firstly, the design standards for the unmanned aerial vehicles has been taken.According to unmanned aircraft electrical system and the design of the large turning moment ofturning requirements, first of all, this paper proposes a double worm type turning mechanism transmissionscheme and complete the institution of turning structure design.Secondly a control system was designed tosolve the servo motor control,synchronization control of double worm,clutch and control of torque limiterand the integration of control system design.The front wheel turning system was built in LMS Imagine.LabAMESim and the simulation model was simulated to analysis the system. Aimed at turning mechanismexperiment, the landing gear clamping piece form a complete set of institutions was designed,so thelanding gear can be experiment conveniently.Finally the function of the electrical system of turningexperiment was done In the electrical system of turning experiment platforms.The control system of doubleworm mechanism,worm gear and worm drive mechanism and electromagnetic clutch on-off switchfunction was verified.Through the experimental analysis shows that the double worm all-electricinstitutions of turning on the function of turning meet the requirements of the institution of turning, servomotor synchronization problem is also verified. The result of the experiment and comparing the results ofthe simulation model, the correctness of the simulation model is verified.Through the research work of this article, some valuable experience was provided for all aircraftbattery front wheel turning system design, analysis and the experiment and, laid the foundation for furtheroptimization design and experimental work.