弹射与阻拦一体式电磁弹射装置的电磁特性分析

doi:10.12382/bgxb.2023.1120

摘要/Abstract

摘要：

针对线性弹射装置占地面积大、结构复杂和质量大的固有缺点,提出一种单轴一体式钢索拖动新型电磁弹射和阻拦装置。装置由永磁储能电机、电涡流离合器、电涡流制动器和绕线轮等组成。介绍了装置的结构和工作原理。基于安培环路定理建立电涡流离合器和电涡流制动器的电磁理论模型。通过与三维有限元计算结果对比,分析电涡流离合器和电涡流制动器的电磁特性。通过制作的电涡流制动器的小型试验样机验证电磁理论模型的正确性和有效性,最终进行动力学分析。研究结果表明,该装置可以使30000kg的飞机在2.1s内从0m/s加速到70m/s,并能够使72m/s的飞机在2.6s停下,满足设计指标的要求。

关键词: 电磁弹射与阻拦, 电涡流离合器, 电涡流制动器, 安培环路定理, 电磁特性

Abstract:

In view of the inherent disadvantages of large footprint, complex structure and heavy weight of linear catapult device, this paper proposes an electromagnetic ejection and arresting gear with a single axis integrated steel cable drive. The gear consists of permanent magnet energy storage motor, eddy current clutch, eddy current brake and winding wheel. The structure and working principle of the gear are introduced. The electromagnetic theoretical models of eddy current clutches and eddy current brakes are developed based on the Ampere loop theorem. By comparing the results with 3-D finite element calculations, the electromagnetic characteristics of eddy current clutch and eddy current brake are analyzed. The correctness and effectiveness of the electromagnetic theoretical model are verified using a small-scale experimental prototype of the eddy current brake. Finally, a dynamic analysis of the electromagnetic ejection and arresting gear is conducted. The results indicate that the gear can accelerate a 30000kg aircraft from 0m/s to 70m/s within 2.1s. And it can also make a 72m/s aircraft stop in 2.6s, meeting the design requirements.

Key words: electromagnetic ejection and arrest, eddy current clutch, eddy current brake, Ampere circuital theorem, electromagnetic characteristics

中图分类号:

TM359.4

赵童, 李德胜, 叶乐志, 贾亚辉, 王斌, 李泽群. 弹射与阻拦一体式电磁弹射装置的电磁特性分析[J]. 兵工学报, 2024, 45(11): 3938-3948.

ZHAO Tong, LI Desheng, YE Lezhi, JIA Yahui, WANG Bin, LI Zequn. Analysis of Electromagnetic Characteristics of an Integrated Electromagnetic Ejection and Arresting Gear[J]. Acta Armamentarii, 2024, 45(11): 3938-3948.

图/表 29

图1 动力单元结构

Fig.1 Power unit structure

表1 动力单元的技术指标

Table 1 Technical indicators of power unit

参数	数值
宽度B/mm	6900
高度H/mm	3300
质量G/kg	约170000
弹射飞机质量M/kg	≤30000
飞机起飞速度v₁/(m·s^-1)	≤83
飞机着舰速度v₂/(m·s^-1)	≤72
弹射时间t₁/s	≤ 2.4
阻拦时间t₂/s	≤ 3
弹射距离L_l/m	100
离合器所需的传动力矩T_c/(kN·m)	≤2600
制动器所需的制动力矩T_b/(kN·m)	≤ 3800

图2 弹射原理图

Fig.2 Ejection principle diagram

图3 阻拦原理图

Fig.3 Arresting principle diagram

图4 离合器模型

Fig.4 Clutch model

图5 制动器模型

Fig.5 Brake model

图6 离合器和制动器的二维原理图

Fig.6 2D schematic diagram of clutch and brake

图7 500r/min时转子内表面的磁通密度

Fig.7 Magnetic flux density on the inner surface of rotor at 500r/min

图8 磁通密度和励磁系数的关系

Fig.8 Relationship between magnetic flux density and excitation coefficient

图9 涡流的真实路径

Fig.9 Real path of eddy current

图10 1/16离合器模型和网格划分

Fig.10 1/16 clutch model and grid division

图11 1/16制动器模型和网格划分

Fig.11 1/16 Brake model and grid division

表2 单列离合器参数

Table 2 Single row clutch parameters

参数	数值
磁极长L_m/mm	100
磁极宽h_m/mm	280
磁极半径R_e/mm	1218
转子1内径R_i1/mm	910
转子2厚L₂/mm	30
转子2半径R_r2/mm	1250
离合器轴向宽度l_c/mm	308
气隙l_g/mm	2
极距τ_p/mm	230
极对数p	16
转子电导率σ_c/(MS·m^-1)	2
单线圈电励磁F_f/A	833×60
转子1转速n₁/(r·min^-1)	≤1500
转子2转速n₂/(r·min^-1)	≥0

表3 单列制动器参数

Table 3 Single row brake parameters

参数	数值
磁极长L_m/mm	150
磁极宽h_m/mm	350
磁极半径R_e1/mm	1468
转子厚L_r/mm	30
转子半径R_r/mm	1500
制动器轴向宽度l_c/mm	400
气隙l_g/mm	2
极距τ_p/mm	270
极对数p	16
转子电导率σ_c/(MS·m^-1)	2
单线圈电励磁F_f/A	1142×70
转速n/(r·min^-1)	630

图12 离合器和制动器静态气隙磁密

Fig.12 Clutch and brake static air gap magnetic densities

图13 离合器和制动器反应磁通密度

Fig.13 Clutch and brake response magnetic flux densities

图14 离合器转速差为100r/min和制动器转速为100r/min时理论计算和三维有限元计算的气隙磁密分布

Fig.14 Theoretical calculation and three-dimensional finite element calculation of air gap magnetic density distribution for clutch speed difference of 100r/min and brake speed of 100r/min

图15 离合器的传动力矩-转速差特性

Fig.15 Transmission torque-speed difference characteristics of clutch

图16 制动器的制动力矩-转速特性

Fig.16 Braking torque-speed characteristics of brake

图17 电涡流制动器试验样机

Fig.17 Eddy current brake test prototype

图18 试验台架示意图

Fig.18 Schematic diagram of test bench

图19 试验样机的力矩特性-转速

Fig.19 Speed-torque characteristics of experimental prototype

表4 弹射相关参数

Table 4 Parameters related to ejection

参数	数值
飞机质量M/kg	13000
飞机起飞速度v₁/(m·s^-1)	66.7
弹射距离L_l/m	110

表5 阻拦相关参数

Table 5 Parameters related to arresting

参数	数值
飞机质量M/kg	30000
飞机着舰速度v₂/(m·s^-1)	72
阻拦时间t₂/s	2.6
阻拦距离L_a/m	100

图20 弹射动力学流程图

Fig.20 Flow chart of ejection dynamics

图21 动力单元与直线电机对比

Fig.21 Comparison between power unit and linear motor

图22 30t的飞机动力学分析结果

Fig.22 Dynamics analysis results of 30t aircraft

图23 阻拦动力学模型

Fig.23 Arresting dynamics model

图24 飞机速度和钢索受力

Fig.24 Aircraft speed and cable force

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