The Design Of Wing Folding Actuator For A Certain Shipboard Aircraft

The surface ship plays an important part in the national maritime operations,and the carrier aircraft is one of the indispensable combat tools of the surface ship.The performance and quantity of carrier aircraft determine the combat ability of the warship.The larger the carrier aircraft quantity is,the stronger the strength is.In order to save the space occupied by the wings and enhance the carrying capacity of the ship,the wings of the carrier aircraft need to be designed to be foldable.The wing folding actuator,also known as wing folding and unfolding mechanism,is the core mechanism of the folding wing.Its performance directly determines the quality of a folding system.This project relies on a cooperative project with a research institute,which requires that a kind of wing folding actuator for a certain type of shipboard aircraft should be designed under the specified size,mass and load.The target is to make the wing folding actuator lighter,safe,reliable and suitable to be installed between the inner and outer wings of the shipboard aircraft.The wing folding actuator’s movement should be stable with impact free.The main research contents are as follows:(1)According to the general process of scheme design based on functional principles,the wing folding actuator is designed.The four alternatives are proposed,and the optimal structure is selected through the decision matrix for subsequent structural design in this paper.(2)The structure of the folding actuator is designed.Material selection,designing and checking calculation for parts are completed.The motion laws of the driving and driven parts of the mechanism are designed.Aiming at the involute structure spiral groove of the inverse cylindrical cam,the spiral groove profile equation is solved based on coordinate transformation and conjugate surface theory,and the coordinate value of the space profile is determined by MATLAB programming.Finally,Solid Works is used to complete the three-dimensional modeling of the wing folding actuator to verify whether it meets the quality requirements.(3)Adams is used to simulate the kinematics and dynamics of the wing folding actuator,and ANSYS is used to analyze the stress.The influence of friction force on angular displacement,angular velocity,angular acceleration and end impact force is analyzed.The stability in the process of motion and the impact from beginning to end are analyzed.It is verified whether the motion law of the design meets the design requirements.Under the given load,ANSYS is used to analyze the stress and verify whether the strength of wing folding actuator meets the requirements.The scheme design of this paper selects the wing folding actuator scheme of inverse cylindrical cam mechanism to achieve folding and spline transmission of torque.The designed three-dimensional model mass is 64.725 kg,which meets the design requirements that is less than 80 kg.In the case of friction force,the deployment angle is90 °,which meets the design requirements.The total time from flattening to the end of locking is 15.044 s,which meets the design requirements that is no more than 20 s.The length,width and height of the actuator designed are 1786 mm,230mm and 92 mm respectively,meeting the size requirements.And Adams simulation results prove that the motion is relatively stable,and there is no impact at all.The results of ANSYS simulation show that the strength of wing folding actuator meets the requirements under the given load.