Flap control systems of Cessna Citation X, Learjet 45 and Dash-8.

 

Grouped here are three different actuators adopted for the flap control systems of the business aircrafts Cessna Citation X and Learjet 45 and for the De Havilland Dash-8.

Components experiencing high applied loads and important stress levels were verified with finite element models (bracket, gimbal, universal joint, housing). All other mechanical components were treated with conventional methods of stress analysis (ballscrew, torque limiter, worm gear, bearings, screws, pins, springs, splines). The types of loads involved in these kind of structures are tipically static limit and ultimate external actuation forces due to aerodynamic forces and jam and operating dynamic load cycles which induce fatigue. Generally the ballscrew must be verified against buckling and the internal components require a wear analysis.