With the rapid advancement of electromagnetic launch technology,enhancing the structural stability and thermal resistance of armatures has become essential for improving the overall efficiency and reliability of railg...With the rapid advancement of electromagnetic launch technology,enhancing the structural stability and thermal resistance of armatures has become essential for improving the overall efficiency and reliability of railgun systems.Traditional aluminum alloy armatures often suffer from severe ablation,deformation,and uneven current distribution under high pulsed currents,which limit their performance and service life.To address these challenges,this study employs the Johnson–Cook constitutive model and the finite element method to develop armature models of aluminum matrix composites with varying heterogeneous graphene volume fractions.The temperature,stress,and strain of the armatures during operation were analyzed to investigate the effects of different graphene volume fractions on the deformation and damage behavior of aluminum matrix composite armatures under the multi-field coupling of electromagnetic,thermal,and structural interactions.The results indicate that,compared to the 6061 aluminum alloy matrix,the graphene-reinforced aluminum matrix composite armature significantly suppresses ablation damage at the tail and throat edges.The incorporation of graphene notably reduces the temperature rise during the armature emission process,increases the muzzle velocity under identical current excitation,and mitigates directional deformation of the armature.The 1 wt.% graphene-reinforced aluminum matrix composite armature demonstrates better agreement with experimental results at a strain rate of 2000 s^(-1),while simultaneously improving stress-strain response,reducing temperature rise,and improving velocity performance.展开更多
目的研究航天器火工冲击缓冲方案,降低火工冲击对航天器上设备的影响。方法根据火工冲击环境防护设计原则设计3种系统级缓冲方案,由NASTRAN软件进行响应预示,用星箭分离局部结构解锁分离试验数据进行验证及模型修正。结果在星箭连接界...目的研究航天器火工冲击缓冲方案,降低火工冲击对航天器上设备的影响。方法根据火工冲击环境防护设计原则设计3种系统级缓冲方案,由NASTRAN软件进行响应预示,用星箭分离局部结构解锁分离试验数据进行验证及模型修正。结果在星箭连接界面增加间断面的加速度响应最大衰减量为62%,增加复杂构型结构的加速度响应最大衰减量为82%,采用冲击隔离的加速度响应最大衰减量为60%。结论在星箭连接界面增加间断面、复杂构型结构或减小星箭界面接触面积均有一定的缓冲效果,系统缓冲设计时应综合考虑质量、结构连接刚度、缓冲效果、卫星状态、运载火箭状态约束等条件。冲击响应预示计算结果与试验结果基本吻合(在±6 d B内),表明这种预示方法能够较准确预示某卫星结构火工冲击响应。展开更多
基金funded Basic Research Projects of Higher Education Institutions in Liaoning Province(JYTZD20230004)Future Industry Frontier Technology Project in Liaoning Province in 2025(2025JH2/101330141)Key Research and Development Program of Liaoning Province in 2025.
文摘With the rapid advancement of electromagnetic launch technology,enhancing the structural stability and thermal resistance of armatures has become essential for improving the overall efficiency and reliability of railgun systems.Traditional aluminum alloy armatures often suffer from severe ablation,deformation,and uneven current distribution under high pulsed currents,which limit their performance and service life.To address these challenges,this study employs the Johnson–Cook constitutive model and the finite element method to develop armature models of aluminum matrix composites with varying heterogeneous graphene volume fractions.The temperature,stress,and strain of the armatures during operation were analyzed to investigate the effects of different graphene volume fractions on the deformation and damage behavior of aluminum matrix composite armatures under the multi-field coupling of electromagnetic,thermal,and structural interactions.The results indicate that,compared to the 6061 aluminum alloy matrix,the graphene-reinforced aluminum matrix composite armature significantly suppresses ablation damage at the tail and throat edges.The incorporation of graphene notably reduces the temperature rise during the armature emission process,increases the muzzle velocity under identical current excitation,and mitigates directional deformation of the armature.The 1 wt.% graphene-reinforced aluminum matrix composite armature demonstrates better agreement with experimental results at a strain rate of 2000 s^(-1),while simultaneously improving stress-strain response,reducing temperature rise,and improving velocity performance.
文摘目的研究航天器火工冲击缓冲方案,降低火工冲击对航天器上设备的影响。方法根据火工冲击环境防护设计原则设计3种系统级缓冲方案,由NASTRAN软件进行响应预示,用星箭分离局部结构解锁分离试验数据进行验证及模型修正。结果在星箭连接界面增加间断面的加速度响应最大衰减量为62%,增加复杂构型结构的加速度响应最大衰减量为82%,采用冲击隔离的加速度响应最大衰减量为60%。结论在星箭连接界面增加间断面、复杂构型结构或减小星箭界面接触面积均有一定的缓冲效果,系统缓冲设计时应综合考虑质量、结构连接刚度、缓冲效果、卫星状态、运载火箭状态约束等条件。冲击响应预示计算结果与试验结果基本吻合(在±6 d B内),表明这种预示方法能够较准确预示某卫星结构火工冲击响应。
