Abstarct: In this thesis, a research on Double-Sided linear induction launchers has been discussed. Due to the ever-increasing development and progress of various industries and the replacement of mechanical systems with electric machines, the aviation industry has not been excluded from this. The use of linear machines as aircraft launchers has been the focus of some countries for decades. In this thesis, with the aim of finding an optimal design for the construction of a laboratory sample of a magnetic launcher, research on induction linear machines has been carried out. The initial modeling of this design has been done with the help of finite element software. Considering the constraints of the optimal design, using the trial and error method, the search for the optimal model among the possible structures has been done. The parameters of the considered optimization are dimensions, energy and acceleration of the projectile. In this design, the length of the primary core is considered fixed at 2 meters. Considering the constant heat distribution along 2 meters, structures with different pole steps have been created. Finally, by examining the effect of the pole step and the length of the secondary plate according to the optimization constraints, the optimal model has been extracted. In order to obtain the optimal model, at first, the constant current analysis of the starting power was investigated. Considering the transitory conditions and the results obtained from the analysis of the launch force, the optimal structure has been investigated to achieve the maximum speed when the projectile exits the initial core. According to the simulation results obtained from the transient performance of the launcher, the dimensions of the secondary plate have been investigated. baxsed on this analysis, two transition zones for optimal performance have been obtained. Taking into account the constraint of the maximum allowed acceleration, the final optimal model has been extracted. In order to test the performance of the obtained model, its laboratory sample has been made and tested in the dimensions of a quarter of the original model. In the practical test, taking into account the energy changes of the projectile at the moment it starts moving and until the moment it leaves, the output power changes have been investigated in the range of 45 to 13,000 watts. According to this performance range, changes in speed and efficiency have been investigated and evaluated according to changes in input voltage. baxsed on the results obtained from the practical test, due to the transient performance of the launcher, the speed changes linearly according to the input voltage, which is caused by the transient performance of the system. baxsed on the results obtained from the efficiency analysis, the maximum efficiency of the launcher equal to 0.12% at the voltage of 390 volts has been practically calculated. According to the tests, the maximum speed is 1.5 meters per second at a voltage of 450 volts.