Open AccessDynamical Analysis for the INS Vibration Control System Used in UAV
Author(s) -
Yuxing Duan,
Xiao Li,
Bo Su,
Xin Wang,
Qiang Yang
Publication year - 2020
Publication title -
iop conference series. materials science and engineering
Language(s) - English
Resource type - Journals
eISSN - 1757-899X
pISSN - 1757-8981
DOI - 10.1088/1757-899x/887/1/012026
Subject(s) - vibration , vibration isolation , isolator , inertial measurement unit , stiffness , inertial frame of reference , control theory (sociology) , damping ratio , acceleration , coupling (piping) , damping torque , offset (computer science) , structural engineering , vibration control , engineering , physics , computer science , acoustics , mechanical engineering , classical mechanics , aerospace engineering , direct torque control , control (management) , electrical engineering , voltage , electronic engineering , artificial intelligence , induction motor , programming language
A six-degree-of-freedom mechanical dynamic model and its equations of the damping system are established for the offset installation environment of the UAV. The influence parameters of the damping system on the vibration coupling state is studied based on the model. And the optimal parameters of the damping system are obtained by doing the mechanical dynamic calculation. And then the vibration isolator of the UAV strap-down inertial measurement unit is designed and manufactured. Finally, the damping system was tested and verified on the shaking table and in the flight environment of the UAV. It is shown that the damping system could implement the tri-axial equal rigid design when the shaft-to-radius stiffness of the isolator is about 0.8. And the experiments also prove this point. The damping system weakens the coupling problem of the strap-down inertial measurement unit effectively, and it reaches the quasi-decoupled state. The amplitude of the acceleration decreases by more than 50% after vibration isolation.