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.
[1] 马伟明, 鲁军勇. 电磁发射技术[J].国防科技大学学报,2016,38(6):1-5.
Ma Weiming, Lu Junyong.Electromagnetic launch technology[J]. Journal of National University of Defense Technology,2016,38(6):1-5.
[2] Hasirci U, Balikci A, Zabar Z, et al.concerning the design of a novel electromagnetic launcher for earth-to-orbit micro- and nanosatellite systems[J]. IEEE Transactions on Plasma Science,2011,39(1): 498-503.
[3] 王群, 耿云玲. 电磁炮及其特点和军事应用前景[J].国防科技,2011,32(2):1-1.
Wang Qun, Geng Yunling.Electromagnetic Gun and Its Characteristics and Military Application[J]. National Defense Science & Technology,2011,32(2): 1-1.
[4] Turman B N.Coilgun Launcher for Nanosatellites[R]. Office of Scientific & Technical Information Technical Reports,1999.
[5] 王韶霞, 王玉晶, 王慧锦. 电磁发射实验中的测速系统研究[J].鲁东大学学报,2012,28(3):231-234.
Wang Shaoxia, Wang Yujing, Wang Huijin.Research on Velocity Measuring System in the Electromagnetic Launching Experiment[J]. Ludong University Journal, 2012,28(3):231-23 4.
[6] 贾学松. 三级感应线圈型电磁发射器系统仿真及实验研究[D].合肥:安徽大学,2018.
Jia Xuesong.Simulation and experimental research on three-stage induction coil electromagnetic transmitter system[D]. Hefei: Anhui University,2018.
[7] 李松乘,鲁军勇等.电磁发射装置弹丸弹道姿态测量[J].电工技术学报,2020,35(23):4835-4842.
Li Songcheng, Lu Junyong,et al.Research on Ballistic Attitude Measurement of Projectile in Electromagnetic Launcher[J]. Transactions of China Electrotechnical Society, 2020,35(23):4835-4842.
[8] 王永峰. 基于微小型测试仪的侵彻过载测试技术研究[D].太原:中北大学,2016.
Wang Yongfeng.Study on Penetration Overload Test Technology based on Micro Tester[D]. Taiyuan: North University of China,2016.
[9] 杨文卿. 高过载强磁高温复合环境下弹载测试系统设计[D].太原:中北大学,2019.
Yang Wenqing.Design of Missile-borne Test System under High Overloading, High-temperature and Strong Electromagnetic Complex Environment[D], Taiyuan: North University of China,2019.
[10] 牛明杰. 战斗部侵彻过载参量存储测试系统研究[D].南京:南京理工大学, 2018.
Niu Mingjie.Research on warhead penetration overload parametric storage test system[D]. Nanjing: Nanjing University of Science and Technology,2018.
[11] 管少华,关晓存.多级同步感应线圈发射器电枢内部强磁场屏蔽与优化[J].电工技术学报,2020,35(2): 333-340.
Guan Shaohua, Guan Xiaocun.Shield of Armature of Multi-Stage Synchronous Induction Coil Launcher Internal High Magnetic Field and Optimization[J]. Transactions of China Electrotechnical Society, 2020,35(2): 333-340.
[12] Zhang Y, Gang X, Gong Y, et al. Armature Structure Research of a Synchronous Induction Coil Launcher [J]. IEEE Transactions on Plasmaence,2017, PP(99):1-5.
[13] 廖桥生,张祥金,李豪杰,等.轨道炮弹丸所处强磁场环境屏蔽设计与仿真[J].火炮发射与控制学报, 2016,37(2): 67-72.
Liao Qiaosheng, Zhang Xiangjin, Li Haojie, et al.Simulation of in-bore high magnetic shielding for railgun projectile[J]. Journal of Gun Launch &Control, 2016,37(2): 67-72.
[14] Bologna M, Marracci M, Micheletti R, et al.Resonant shield concept as alternative solution in railguns[J]. IEEE Transactions on Plasma Science, 2015, 43(5): 1628-1633.
[15] Cui Shumei, Wang Shaofei, Wu Shaopeng.Magnetic field shielding of electromagnetic launch missile[C]// 19th IEEE Pulsed Power Conference(PPC), San Francisco,2013:1-4.
[16] Becherini G,Fraia S D,Ciolini R,et al.Shielding of high magnetic fields[J]. IEEE Transactions on Magnetics, 2009, 45(1): 604-609.
[17] 王建坤. 高速深侵彻过程测试关键技术的研究[D].原:中北大学,2015.
Wang Jiankun.Study on the key technology of high speed deep penetration text[D]. Taiyuan: North University of China,2015.
[18] 王耀先. 复合材料结构设计[M].北京:化学工业出版社,2001.
Wang Yaoxian.Composite structural design[M]. Beijing: Chemical Industry Press,2001.