飞行器贮运一体化装置电插头机构分离特性研究

郝予琛; 于喆; 李昱霖; 张保刚; 秦旭锋; 李微微; 俞刘建

doi:10.7643/ issn.1672-9242.2026.05.005

PDF(3562 KB)

装备环境工程 ›› 2026, Vol. 23 ›› Issue (5) : 36-43. DOI: 10.7643/ issn.1672-9242.2026.05.005

航空航天装备

飞行器贮运一体化装置电插头机构分离特性研究

郝予琛¹, 于喆¹, 李昱霖^1,*, 张保刚¹, 秦旭锋², 李微微¹, 俞刘建¹

作者信息 +

Separation Characteristics of the Electrical Plug Mechanism for Aircraft Storage and Transportation Integrated Devices

HAO Yuchen¹, YU Zhe¹, LI Yulin^1,*, ZHANG Baogang¹, QIN Xufeng², LI Weiwei¹, YU Liujian¹

Author information +

文章历史 +

摘要

目的验证发射工况下飞行贮运一体化装置高速分离特性。方法搭建高速分离试验平台,对发射工况下飞行贮运一体化装置电插头装置的分离特性进行验证,并开展运动力学理论分析及多体动力学分析,找出影响分离特性的主要因素及作用机理。结果在筒弹高速分离过程中,试验后发现电插头机构未正常分离,且发生多处结构破坏,贮运装置及飞行器局部受损。对电插头机构的协调性进行了分析,判断电插头壳体在平动过程中陷入浮动座孔是电插头机构造成失效的主要原因。在试验结果的基础上,结合理论分析方法开展相应的机构优化,并再次进行了机构动力学仿真和优化后试验。此时插头机构分离顺畅,工作正常,从而验证了优化设计后电插头机构的合理性。结论通过结合理论、仿真和实验工作可以有效辨识影响电插头机构正常运动的关键因素,从而为后续贮运一体化装置可靠性分析提供重要数据支撑。

Abstract

The work aims to investigate the separation characteristics of the storage and transportation integrated device under launch conditions. A separation test platform was established to verify the separation characteristics of the electrical plug of the storage and launch integrated device under launch conditions. Kinematic theoretical analysis and multi-body dynamics simulation were further carried out to identify the key affecting factors of separation characteristics together with their action mechanisms. During the high-speed separation process of the canister and missile, the electrical plug mechanism failed to separate properly and sustained multiple structural damages, leading to localized damage to the storage device and the aircraft. An analysis of the coordination of the electrical plug mechanism revealed that the primary cause of failure was the jamming of the electrical plug housing into the floating seat hole during translational motion. Based on the test results, corresponding mechanism optimizations were carried out with theoretical analysis methods. Subsequently, dynamic simulations of the mechanism and post-optimization tests were performed. At this stage, the plug mechanism separated smoothly and functioned properly, thereby verifying the rationality of the optimized design of the electrical plug mechanism. The combination of theoretical research, numerical simulation and experimental tests enables effective identification of critical factors affecting the normal motion of the electrical plug mechanism, thus providing important data support for subsequent reliability analysis of the storage and transportation integrated device.

导出引用

郝予琛, 于喆, 李昱霖, 张保刚, 秦旭锋, 李微微, 俞刘建. 飞行器贮运一体化装置电插头机构分离特性研究[J]. 装备环境工程. 2026, 23(5): 36-43 https://doi.org/10.7643/ issn.1672-9242.2026.05.005

HAO Yuchen, YU Zhe, LI Yulin, ZHANG Baogang, QIN Xufeng, LI Weiwei, YU Liujian. Separation Characteristics of the Electrical Plug Mechanism for Aircraft Storage and Transportation Integrated Devices[J]. Equipment Environmental Engineering. 2026, 23(5): 36-43 https://doi.org/10.7643/ issn.1672-9242.2026.05.005

中图分类号： V414.9

参考文献

[1] 陈愚, 孙凤云. 贮运发射箱的结构与设计[J]. 包装工程, 2012, 33(15): 132-135.
CHEN Y, SUN Y F.Structure and Design of Storage and Transport Launcher[J]. Packaging Engineering, 2012, 33(15): 132-135.
[2] 张宏剑, 石玉红, 顾春辉, 等. 赋能运载火箭多功能化发展的机构技术与挑战[J]. 机械工程学报, 2026, 62(1): 2-17.
ZHANG H J, SHI Y H, GU C H, et al.Enabling Multifunctional Development of Launch Vehicles: Mechanism Technologies and Challenges[J]. Journal of Mechanical Engineering, 2026, 62(1): 2-17.
[3] 许斌, 郝予琛, 杨海洋, 等. 防空导弹结构轻量化技术的发展与展望[J]. 空天防御, 2024, 7(3): 1-13.
XU B, HAO Y C, YANG H Y, et al. Development and Prospect of Lightweight Technology for Anti-Aircraft Missile Structures[J]. Air & Space Defense, 2024, 7(3): 1-13.). (in Chinese)
[4] 张飞. 新型同时离轨发射方式及动力学特性研究[D]. 北京: 北京理工大学, 2016.
ZHANG F.Research on a Launch Method of Missile Leaving Guide Rail Simultaneously and Its Dynamics Characteristics[D]. Beijing: Beijing Institute of Technology, 2016.
[5] 曹燎原, 舒陶. 发射装置导轨的挂装校核方法[J]. 弹箭与制导学报, 2020, 40(1): 133-136.
CAO L Y, SHU T.Check Method of Launcher Rails Mounted Missile[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2020, 40(1): 133-136.
[6] 郝予琛, 张保刚, 李昱霖, 等. 冲击载荷下飞行器贮运一体化装置锁紧特性研究[J]. 弹箭与制导学报, 2025, 45(3): 366-370.
HAO Y C, ZHANG B G, LI Y L, et al.Study on the Locking Mechanism of Storage-Transportation Integrated Device for High-Speed Vehicle under Impact Loading Conditions[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2025, 45(3): 366-370.
[7] 郝予琛, 张保刚, 李昱霖, 等. 飞行器意外点火工况下贮运装置解锁特性研究[J]. 弹箭与制导学报, 2025, 45(1): 80-84.
HAO Y C, ZHANG B G, LI Y L, et al.Research on Unlocking Characteristics of Storage and Transportation Device under Accidental Vehicle Ignition Condition[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2025, 45(1): 80-84.
[8] 李微微, 张保刚, 张兴勇, 等. 抑制导弹径向跳动的辅助支撑装置: CN202110547728.6[P].2021-09-07.
LI W W, ZHANGBG, ZHANG X Y, et al. Auxiliary Supporting Device for Inhibiting Radial Runout of Missiles: CN202110547728.6 [P].2021-09-07.
[9] 张保刚, 于喆, 胡洁, 等. 一种连接器自适应插合装置: CN201610687132.5[P].2016-12-14.
ZHANGBG, YU Z, HU J, et al. Connector Adaptive Plugging Device: CN201610687132.5[P].2016-12-14.
[10] 俞刘建, 张保刚, 梅睿, 等. 发射装置电插拔机构的封装结构及封装方法: CN107478108B[P].2019-06-14.
YU L J, ZHANGBG, MEI R, et al. The Electricity Inserts Pulls Out of the Emitting Device Encapsulation Method and Structure: CN107478108B[P].2019-06-14.
[11] 吴媛. 贮运发射箱结构设计及有限元分析[D]. 成都: 电子科技大学, 2009.
WU Y.Structural Design and Finite Element Analysis of a Storage and Launch Canister[D]. Chengdu: University of Electronic Science and Technology of China, 2009.
[12] 王凤金, 王爱伟, 曹绘娜, 等. 零秒脱落连接器可靠性设计及指标验证[J]. 装备环境工程, 2023, 20(1): 59-64.
WANG F J, WANG A W, CAO H N, et al.Reliability Design and Index Verification of Zero-Second Separating Connector[J]. Equipment Environmental Engineering, 2023, 20(1): 59-64.
[13] 王腾, 郁大照, 王泗环, 等. 某型飞机典型电连接器接插件插拔特性和接触电阻仿真研究[J]. 装备环境工程, 2021, 18(2): 37-43.
WANG T, YU D Z, WANG S H, et al.Simulation Study on Plug and Pull Characteristics and Contact Resistance of Electrical Coupler Connectors on Aircraft[J]. Equipment Environmental Engineering, 2021, 18(2): 37-43.
[14] 曹燎原. 轨式发射装置发射分离安全影响因素研究[D]. 上海: 上海交通大学, 2012.
CAO L Y.Research of Launching Breakaway Security Effect Factor in Projector Launcher[D]. Shanghai: Shanghai Jiao Tong University, 2012.
[15] 孙继红, 武令伟, 陈冰. 脱插机构的误差灵敏度分析与优化设计[J]. 舰船科学技术, 2023, 45(11): 171-175.
SUN J H, WU L W, CHEN B.Insert-Draw Sensitivity Analysis Based on the Geometric Error Transformation Model[J]. Ship Science and Technology, 2023, 45(11): 171-175.
[16] 李哲. 分离脱落电连接器稳健设计技术的研究[D]. 哈尔滨: 哈尔滨工业大学, 2015.
LI Z.Study on Seperation Electrical Connector Robust Design[D]. Harbin: Harbin Institute of Technology, 2015.
[17] 褚金钱, 李咏强, 章兰英. 脱落电连接器智能对接系统的柔顺设计与分析[J]. 航天工程大学学报, 2024, 1(1): 85-93.
CHU J Q, LI Y Q, ZHANG L Y.Flexible Design and Analysis of Intelligent Docking System for Detached Electrical Connectors[J]. Journal of Space Engineering University, 2024, 1(1): 85-93.
[18] 撒国栋, 王栋, 刘振宇, 等. 运载火箭非火工分离机构复用可靠性研究综述与展望[J]. 机械工程学报, 2026, 62(1): 59-78.
SA G D, WANG D, LIU Z Y, et al.Review and Prospect of Reuse Reliability Research on Non-Pyrotechnic Separation Mechanism of Launch Vehicle[J]. Journal of Mechanical Engineering, 2026, 62(1): 59-78.
[19] 安进, 吴长春. 机载发射装置插拔机构设计[J]. 机械与电子, 2012, 30(3): 76-78.
AN J, WU C C.Design of Insert-Draw Mechanism in Airborne Launcher[J]. Machinery & Electronics, 2012, 30(3): 76-78.
[20] 国防科学技术工业委员会. 飞机/悬挂物电气连接系统接口要求: GJB 1188A—99[S]. 北京: 中国标准出版社, 1999.
Commission of Science, Technology and Industry for National Defense. Requirements of Interface for Aircraft/Store Electrical Interconnection System: GJB 1188A—99[S]. Beijing: Standards Press of China, 1999.
[21] 王鑫, 袁晓光, 杨星. 基于拉格朗日方法的飞行器多体分离姿态动力学分析研究[J]. 西北工业大学学报, 2014, 32(1): 18-22.
WANG X, YUAN X G, YANG X.Research on Multi-Body Separation Dynamics Using Lagrange Method[J]. Journal of Northwestern Polytechnical University, 2014, 32(1): 18-22.
[22] 孟光, 周徐斌, 苗军. 航天重大工程中的力学问题[J]. 力学进展, 2016, 46(1): 267-322.
MENG G, ZHOU X B, MIAO J.Mechanical Problems in Momentous Projects of Aerospace Engineering[J]. Advances in Mechanics, 2016, 46(1): 267-322.
[23] 刘广, 张保刚, 江玉刚, 等. 自适应联动插拔机构建模与仿真[J]. 系统仿真技术, 2017, 13(4): 330-337.
LIU G, ZHANG B G, JIANG Y G, et al.Modeling and Simulation of Adaptive Linkage Insert-Draw Mechanism[J]. System Simulation Technology, 2017, 13(4): 330-337.
[24] 黑蕾, 曾志, 杨森, 等. 火箭发射电气分离机构设计和试验[J]. 固体火箭技术, 2023, 46(5): 797-806.
HEI L, ZENG Z, YANG S, et al.Design and Test Verification of the Electrical Disconnecting Mechanism in Rocket Launcher[J]. Journal of Solid Rocket Technology, 2023, 46(5): 797-806.
[25] 俞刘建, 张保刚, 许自然, 等. 发射装置电插拔机构的动能分离机构: CN201710533715.7[P].2019-08-09.
YU L J, ZHANG B G, XU Z R, et al. Launching Device Electric Plugging Mechanism Kinetic Energy Separation Mechanism: CN 107565304 B [P].2019-08-09.
[26] 刘永亮, 任克亮, 马旭轮, 等. 平面四杆机构在舰载垂直发射装置舱口盖系统中的应用分析[J]. 装备环境工程, 2019, 16(5): 13-17.
LIU Y L, REN K L, MA X L, et al.Application of Plane Four Poles Mechanism in Hatch Opening System of Ship Vertical Launcher[J]. Equipment Environmental Engineering, 2019, 16(5): 13-17.
[27] 白瑜光, 张胜, 曹玉顺, 等. 机载发射架地面试验系统的动力学特性仿真与优化[J]. 系统仿真学报, 2025, 37(12): 3151-3160.
BAI Y G, ZHANG S, CAO Y S, et al.Dynamic Characteristic Simulation and Optimization of Ground Test System for Airborne Launch Rack[J]. Journal of System Simulation, 2025, 37(12): 3151-3160.
[28] 刘锋. 基于RecurDyn的旋转弹发射出筒过程动力学仿真[J]. 计算机辅助工程, 2014, 23(6): 52-55.
LIU F.Dynamics Simulation on Launch Process of Rotative Missile Based on Recur Dyn[J]. Computer Aided Engineering, 2014, 23(6): 52-55.
[29] 中华人民共和国国家质量监督检验检疫总局, 中国国家标准化管理委员会. 轴用弹性挡圈: GB/T 894—2017[S]. 北京: 中国标准出版社, 2017.
General Administration of Quality Supervision, Inspection and Quarantine of the People's Republic of China, Standardization Administration. Retaining Rings for Shaft: GB/T 894—2017[S]. Beijing: Standards Press of China, 2017.
[30] 贺媛媛, 王琦琛, 张航, 等. 扑旋翼飞行器机构动力学建模与功率优化[J]. 机械工程学报, 2023, 59(17): 33-43.
HE Y Y, WANG Q C, ZHANG H, et al.Mechanism Dynamic Model and Power Optimization of Flapping Wing Rotor[J]. Journal of Mechanical Engineering, 2023, 59(17): 33-43.