Pull rod and rocker arm are important parts of aircraft control system, its strength, stiffness and stability can largely affect the aircrafts control effect, sometimes the flight safety will be influenced [2]. A type of aircraft control system has been upgraded and modified, therefore the pull rod and rocker arm of the flap control system need to take the static strength test. Based on field test and finite element simulation analysis, this paper has the static strength of pull rod and rocker arm checked, and to verify the correctness of the finite element model and lay foundation for the optimization design of components of aircraft control system.
A study on stages of queuing system in aircraft control system
