Design And Impact Dynamics Analysis Of The Lifting Mechanism Of Portable Missile Launcher

In the final stage of design and manufacture,a certain type of portable missile needs to be tested by missile launch controlling and testing system,so the design of such system is an important part of military engineering.Missile launch controlling and testing system needs to complete the action flow of launch and collect all the important signals in the process.Its working process includes the application of a lot of knowledge about mechanical engineering.According to the performance requirements of the missile launch controlling and testing system,this paper designs one system for practical engineering needs.This paper reviews the the main form and performance of the portable missile launchers both at home and abroad,especially the main characteristics of the missile lifting mechanism and the impact stability research situation.Considering the actual situation,a portable missile launch controlling and testing system is designed.This paper introduces the overall design scheme in detail,including the mechanical design,electric control design and cooling air system.The column rotation and pitch structure was analyzed and their clamping devices were calculated on the basis of the well-established model.Then the strength of the base part was tested by ANSYS software.A special missile lifting mechanism was designed by combining the spatial linkage mechanism with the missile heading angle guidance law.After the initial mechanism scheme was designed,the singular configuration of the mechanism was discussed by using the screw theory.Then the kinematic characteristics of the spatial linkage mechanism were analyzed by using the analytic projection method.According to the singular configuration of the original mechanism,an improved design scheme was proposed.The mapping relationship between the input and output of the improved mechanism was obtained by combining the minimum norm method with the least square method.Then the static error of the missile lifting mechanism was analyzed by the error transfer matrix.The stability of the missile lifting mechanism under the impact of the explosive bolt was analyzed.Based on the knowledge of the impact dynamics,the dynamic response characteristics of the lifting mechanism were analyzed in the direction of vibration theory by numerical simulation analytic method.Using ANSYS finite element analysis software,this paper discussed the dynamic response of the lifting mechanism to the impact of the explosive bolt at different launching angles.Firstly,the modal analysis of mechanism with different angles was carried out by using the Lanczons method to explore the law that the natural frequency changes roughly with the angle.Then,the modal superposition method was used to study the stress and displacement of the lifting mechanism with different launching angles in the impact process.Afterwards,the relevant laws were summarized,and the dynamic error value of the pitch angle was obtained.According to the design scheme,the prototype of the portable missile launch controlling and testing system was manufactured.The verification tests based on the missile launcher were carried out,including the movement verification test and the impact verification test of the lifting mechanism.In the movement verification test,the control and detection system of the lifting mechanism was established.The motor was controlled by PID method,and the correctness and accuracy of the actual motion of the mechanism were measured by the gyroscope.Adjusting the lifting mechanism to different angles,the dynamic angle error under impact was measured to prove the influence of azimuth angle and pitch angle to launch angle error,which provided reference for the selection of actual test angle.