The development of altitude and remote control for aircraft requires larger rudder piece pitch angle, and Electric actuator needs to withstand larger bending moment as the attitude control executive mechanism. Traditional bending moment and torsional moment of Electric actuator rely on output shaft bearing which are difficult to meet the requirement of resisting large moment. Based on a particular type of Electric actuator system, this paper analyzes its moment resisting capacity, proposes an idea of seperating bearing objects of bending and torsional moment for aircraft, and designs an innovative actuator structure. Moment test experiments show that moment resisting capacity of the new Electric actuator is enhanced to 150% more than orginal one.
Moment Resisting Performance Analysis and Structure Optimization for Electric Actuator
2012
5 Seiten
Aufsatz/Kapitel (Buch)
Englisch
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