|
|
|
| Missile-Borne Storage Testing Technology Research of Synchronous Induction Coil Launcher |
| Shi Jingbin, Guan Xiaocun, Guan Shaohua, Wu Baoqi |
| National Key Laboratory of Science and Technology on Vessel Integrated Power System Naval University of Engineering Wuhan 430033 China |
|
|
|
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.
|
|
Received: 23 October 2022
|
|
|
|
|
|
[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): 1-7.
Wang Qun, Geng Yunling.Electromagnetic gun and its characteristics and military application[J]. National Defense Science & Technology, 2011, 32(2): 1-7.
[4] Turman B N.Coilgun launcher for nanosatellites[R]. Office of Scientific & Technical Information Tech-nical Reports, 1999.
[5] 马伟明, 鲁军勇. 电磁发射技术的研究现状与挑战[J]. 电工技术学报, 2023, 38(15): 3943-3959.
Ma Weiming, Lu Junyong.Research progress and challenges of electromagnetic launch technology[J]. Transactions of China Electrotechnical Society, 2023, 38(15): 3943-3959.
[6] 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): 231-234.
[7] 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.
[8] 李松乘, 鲁军勇, 程龙, 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, Cheng Long, et al.Research on ballistic attitude measurement of pro-jectile in electromagnetic launcher[J]. Transactions of China Electrotechnical Society, 2020, 35(23): 4835-4842.
[9] 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.
[10] 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.
[11] 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.
[12] 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.
[13] Zhang Y, Gang X, Gong Y, et al.Armature structure research of a synchronous induction coil launcher[J]. IEEE Transactions on Plasmaence, 2017, 45(7): 1574-1578.
[14] 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.
[15] 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.
[16] 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.
[17] Becherini G, Fraia S D, Ciolini R, et al.Shielding of high magnetic fields[J]. IEEE Transactions on Mag-netics, 2009, 45(1): 604-609.
[18] 王建坤. 高速深侵彻过程测试关键技术的研究[D].太原: 中北大学, 2015.
[19] 王耀先. 复合材料结构设计[M]. 北京: 化学工业出版社, 2001. |
|
|
|
2024, Vol. 39 
