Some Mechanical Problems Of Space Electromagnetic Emission

Electromagnetic railgun firing in the process of artillery,accompanied by the produc tion of heat,and the heat mainly comes from the joule heat and rail track after electrify pr oducing and armature friction,the friction heat of only a small fraction of the heat spread into the air,the rest is absorbed by the orbit,orbit in the temperature,again with the surro unding medium.In air,heat propagation ways mainly include air convection and heat con duction and thermal radiation,but with the development of aerospace technology,in spac e,and under the environment of the moon,the cooling study of electromagnetic launcher is essential,especially in the absence of air medium vacuum heat propagation path only t hermal radiation;Although in recent years,the research of electromagnetic orbital launch ers in space and the moon has made a lot of progress,but mainly focused on the electrom agnetic launch orbit,the research results on the temperature problem in the process of ele ctromagnetic orbital launch are relatively few.Considering the plasma environment in sp ace and the large temperature difference between day and night on the moon,the issue of orbit heat dissipation and the launch cycle caused by it cannot be ignored.Firstly,the temperature field of the electromagnetic launch orbit and the armature in different environments of space and earth is compared.Secondly,the optimal exit Angle,exit velocity,impact stress and deformation of the projectile can be obtained by calculatin g,analyzing the trajectory and exit velocity of the projectile under the lunar environment.Finally,according to the environment of the satellite,the optimal intersection point,exit velocity,exit Angle,optimal trajectory of the projectile launched by the electromagnetic l auncher in space and the target satellite are calculated by numerical simulation,as well as the stress and deformation of the target satellite when it impacts on the target satellite.Comsol software is used to couple the electric,magnetic,thermal and other physical fields of the electromagnetic launch orbit,and the current density distribution on the orbi t and the armature is obtained.Finally,the temperature rise/temperature drop of the orbit and the armature is calculated during the launch.Then the influence of internal and exter nal conditions on the temperature field and stress field of the armature and the orbit is ana lyzed.The internal conditions,such as the geometric parameters of the armature,the mat erial parameters of the armature,the material emissivity of the armature and the orbit,etc.External conditions such as: the size of the input current and voltage,external environme nt temperature,etc.The optimal trajectory,the optimal Angle,the exit velocity,and the i mpact on the moon or the target after the long-distance delivery of the lunar electromagn etic orbital launcher and the satellite electromagnetic launch are simulated.