Research And Precision Analysis Of Infrared Guidance Testing Device

Modern warfare is a high-tech war,and high-precision weapons play an important role in the war.As an important weapon,missiles can not be ignored in its fighting capacity.The development of the missile embodies the comprehensive national strength of a country.Therefore,the performance testing of the missile is particularly important.The target practice with actual missile requires a lot of financial and material resources.The hardware in the loop simulation test using missile test equipment on the ground can reduce the cost and improve the utilization rate,which is of great significance for the development of national defense construction.The project comes from the latitudinal project development of the "comprehensive test system of infrared guided missile" in a horizontal project.The purpose of the paper is to design a simulation device for testing the performance of infrared guided missiles,and analyze the factors that affect the accuracy of the test device,so as to provide theoretical basis for structure optimization.Firstly,the paper analyzes the present research status at home and abroad of infrared guided missile test device,and introduces the method of structural parameter optimization-orthogonal test method.Combined with the design requirements of the project,the working process of the testing device is analyzed,and the overall scheme of the testing device of the infrared guided missile is proposed.Then the structure of the device is designed,including the missile pose simulation mechanism and the infrared target simulation mechanism.After that,the force analysis of the rear support mechanism and the ADAMS kinematics simulation of the target simulation mechanism were used to complete the selection of the two electrical motors.And then the control system is designed.Secondly,the paper analyzes the accuracy of the test device from two aspects: the pose accuracy of the missile simulation and the infrared target simulation.The critical factors of error were analyzed and quantified including the transmission error of missile support,spindle rotation error of the rotating structure and deflection errors of parts.After that,the errors are summarized and the main factors affecting the accuracy of the device are found out,which provides a theoretical basis for structural improvement and optimization of structuralparameters to improve device accuracy.Thirdly,the main error factors affecting the precision of the device,the preliminary design of the shell,the slide table and the light tube support seat,are improved.The orthogonal test method is used to optimize the parameters of the improved structure,and the better structure is obtained.The parameter index is selected first,and the orthogonal table is used to arrange the combination of all factors.The 3D modeling of the parts is carried out according to the combination of different factors,and then the finite element analysis is carried out.The results of the test were subjected to range and variance analysis to obtain the significance of the degree of influence of each experimental factor on the test results.The optimal level under the single index are found out and finally the better structure parameters of the double index are determined.The device obtained by the optimization of the structural parameters is analyzed again and compared with the results of the preliminary design.The structure that meets the requirement of precision is obtained.Finally,the experimental verification of the prototype is carried out.It is verified that the movement range of the rear support frame in the vertical direction has reached the requirement.It is proved that the rotation mechanism can change automatically when it turns to the limit angle,and the angle error in the change direction is within the error range.It is proved that the motion error of the spindle angle of the rotating mechanism is not quite different from the theoretical error.