With the maturity of electromagnetic launch technology, research on electromagnetic weapon test technology is gradually carried out. Due to the influence of strong pulsed magnetic field and high overload environment in the process of electromagnetic launch, the current research focuses on non-contact external measurement method, and the on-board storage test technology of electromagnetic weapon cannot form a complete test data system. Based on this, this paper carries out the launching environment analysis of synchronous induction coil launcher and the design and analysis of the missile-borne test system. After the dynamic launch test verification, the missile-borne storage test technology of synchronous induction coil launcher is finally formed.
Firstly, the simulation model of synchronous induction coil emitter was established by taking multistage drive coil and test 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 4.2T, and the variation law of the radial magnetic induction intensity is consistent with that in the axial direction, but the amplitude in the tail area is much smaller than that 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 has the largest axial extremum, which increases to 778.3kN within 2.2ms, and then it tends to be stable and fluctuates around 750kN. When the last stage driving coil is triggered, the axial thrust becomes negative instantaneously and its amplitude reaches -457kN.
Secondly, the missile-borne storage test device is designed and placed at the test warhead. Miniaturized circuit module was equipped with uniaxial magnetic field/acceleration sensor to realize the automatic triggering test of the axial acceleration and internal magnetic induction intensity: Choose passive mode to realize the shielding, respectively design different special materials of the outer layer, isolation layer and internal shell. Compared with no shielding conditions, the average shielding efficiency is 28.16dB, lower than the circuit module to withstand electromagnetic interference requirements; The potting epoxy resin reinforcement measures were selected to realize protection. The maximum stress is found at the contact point between the reinforced epoxy resin and the circuit module. At this time, the test projectile has the maximum launch acceleration, the launch time is 12.65ms, and the maximum stress is 59.73MPa, which is less than the maximum tensile strength of the material.
Thirdly, the dynamic launching test platform of synchronous induction coil was built, parameters were set by computer, and data were collected after the test. The measured value of axial magnetic induction intensity was consistent with the simulation value, but the former was larger than the simulation value and fluctuated greatly at the end of the launch. It was analyzed that the installation base, buffer device and other factors were not considered. The measured value of the axial acceleration data is consistent with the simulation rule, but the test projectile presents a "regular collision" effect during the first three levels of driving coil, and the measured value of the axial acceleration from the fourth to the 16th level is 634.1g (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 192.7m/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, which is 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 one-way test was carried out, and the phenomenon of initial collision and final fluctuation was found, it provides a basis for the subsequent research on the multi-DOF motion of synchronous induction coil launcher carrier.