| The strength test of the wing is very important in the static strength test of the whole aircraft.Most of the traditional loading methods use the single actuator to exert the loading force on the wing.In the loading process of traditional single actuator,the direction of loading force can not be adjusted,and extra force is needed to offset the influence of gravity,which leads to large experimental errors in the experiment.The parallel mechanism is widely used in the multi-dimensional loading experiment,which can adjust the loading force in real time and does not require extra compensation for its own gravity.The application of the parallel mechanism in the strength test of the wing can well reduce the experimental errors caused by the defects of the traditional loading method.The kinematic and dynamic characteristics of 2RPS-2UPS parallel mechanism are systematically analyzed.A series of parallel mechanisms were obtained based on spiral theory.Finally,2RPS-2UPS parallel mechanism was selected for research and analysis.The kinematics and dynamics characteristics of the 2RPS-2UPS parallel mechanism were analyzed,and the co-simulation was carried out by MTLAB Simulink plug-in and Recur Dyn software to verify the kinematics and dynamics characteristics of the mechanism.The transfer performance of the parallel mechanism was analyzed,and the key dimensions of the mechanism were optimized with the transfer performance as the evaluation index,which improved the mechanical properties of the whole mechanism.By analyzing and simplifying the force of the lever system,the force of the lever system on the moving platform is simplified into two forces and one moment.In the loading process,when the parallel mechanism is under heavy load,the force deformation of the component will have a great influence on the direction and magnitude of the loading force.The stiffness model of the 2RPS-2UPS parallel mechanism is established by analyzing the deformation of the mechanism,and the stiffness model is verified by ANSYS finite element software.It provides a theoretical basis for improving the stiffness of the mechanism.The control frame of the loading device was built based on fuzzy PID algorithm,and the feasibility of the control frame was verified by Simulink plug-in of MTLAB and Recur Dyn.The rigid-flexible coupling simulation model of a single parallel loading device was built,and the control frame of the loading device was designed during the wing strength experiment.The rigid-flexible coupling simulation model of multiple loading devices was established,and the feasibility of the application of loading devices in the wing strength experiment was verified by the co-simulation. |
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