Abstract：With the maturity of electromagnetic launch technology, research on electromagnetic weapon test technology is gradually carried out. Due to the influence of a strong pulsed magnetic field and high overload environment in the electromagnetic launch, current research focuses on the non-contact external measurement method, and the on-board storage test technology of electromagnetic weapons has not formed a comprehensive test data system. Therefore, this paper analyzes the launching environment of the synchronous induction coil launcher, then designs the missile-borne test system. After the dynamic launch test verification, the missile-borne storage test technology of the synchronous induction coil launcher is finally formed. Firstly, the simulation model of synchronous induction coil emitter is established by taking the multistage drive coil and the testing projectile as the research object. (1) The axial magnetic induction intensity of the test projectile increases first and then decreases with the launch time. The peak value at the tail area of the armature reaches 4.2 T, and the variation in radial magnetic induction intensity is consistent with that in the axial direction. However, the amplitude in the tail area is much smaller than in the axial direction. (2) The thrust of the test projectile fluctuates periodically with the launch time. The thrust of the initial test projectile, triggered by the first-stage driving coil, reaches its maximum axial value at 778.3 kN within 2.2 ms and then stabilizes, fluctuating around 750 kN. When the last stage driving coil is triggered, the axial thrust instantaneously becomes negative, reaching a peak amplitude of -457 kN. Secondly, a missile-borne storage test device is designed and placed at the test warhead. The miniaturized circuit module is equipped with a uniaxial magnetic field/acceleration sensor to realize the automatic triggering test of the axial acceleration and internal magnetic induction intensity. Choose the passive mode to realize the shielding design with special materials for the outer layer, isolation layer, and internal shell. Compared with no shielding conditions, the average shielding efficiency is 28.16 dB, lower than the circuit module to withstand electromagnetic interference requirements. The potting epoxy resin reinforcement measures are selected to realize protection. The maximum stress is found at the contact point between the reinforced epoxy resin and the circuit module, where the test projectile has the maximum launch acceleration, the launch time is 12.65 ms, and the maximum stress is 59.73 MPa less than the maximum tensile strength of the material. Thirdly, the dynamic launching test platform of the synchronous induction coil is built, parameters are set by the computer, and data are collected after testing. The measured axial magnetic induction intensity is consistent with the simulation but larger than the simulation value and fluctuates greatly at the end of the launch. The installation base, buffer device, and other factors are not considered. The measured axial acceleration data are consistent with simulations. However, the test projectile presents a “regular collision” effect during the first three levels of the driving coil. The measured axial acceleration from the fourth to the 16th level is 634.1 g (4.7% error compared with the simulation value). At this time, the test projectile presents a “suspension” characteristic. The test projectile presents the phenomenon of “periodic nutation” at the 17th to 30th level of the drive coil, and the integral value of its exit velocity is deduced to be 192.7 m/s. The error is 1.17% compared with the simulation value and 0.1% compared with the test value of the thru-beam photoelectric switch. The analysis shows that the integral value is closer to the test value, consistent with the actual situation. Finally, through the dynamic test of the test projectile launched by the 30-stage synchronous induction coil launcher, the effective axial magnetic induction intensity data and axial acceleration test data are obtained, which verified the feasibility of the missile-borne storage test technology in the synchronous induction coil launcher. Since only a one-way test is carried out, and the phenomenon of initial collision and final fluctuation is found, it provides a basis for the subsequent research on the multi-DOF motion of synchronous induction coil launcher carriers.
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2024, Vol. 39 
