Design of a linear electric actuator for an aircraft engine control lever

In this paper the design process of a linear electric actuator development for an aircraft engine control lever is described. Initially, a computer model of a linear electric drive with a hexagonal armature was developed and the main parameters of the drive were obtained. Based on the obtained values, a prototype was made. Experimental studies have shown an increased value of the idling efforts, so a decision to refine the prototype was made. In particular, metal shavings were added between the armature magnets, as a result of which the forces were reduced.