旋转部件在交通运输、风能发电等诸多领域具有重要作用。三维数字图像相关方法(Three-Dimensional Digital Image Correlation,3D–DIC)作为一种非接触光学测量手段,能够获取旋转部件在运转过程中的全场位移、变形及振动信息,从而为故...旋转部件在交通运输、风能发电等诸多领域具有重要作用。三维数字图像相关方法(Three-Dimensional Digital Image Correlation,3D–DIC)作为一种非接触光学测量手段,能够获取旋转部件在运转过程中的全场位移、变形及振动信息,从而为故障诊断、健康监测以及气动结构优化设计提供重要数据支撑。本文对近年来3D–DIC技术的发展与应用进行了全面综述。首先介绍了3D–DIC技术的基本原理及其针对旋转物体的变形测量系统;针对大角度旋转测量中出现的退相关问题,详细阐述了国内外学者在初值估计和形函数设计等方面所提出的改进。随后,通过若干典型应用案例,展示了该技术相较于传统变形测量手段的优势。最后,对该技术的应用前景和发展趋势进行了展望。展开更多
Traditional dynamic analysis of mechanical structures,often limited to individual beams or plates,fails to fully capture their dynamic behaviors.In systems where space and mass are constrained,such as the battery supp...Traditional dynamic analysis of mechanical structures,often limited to individual beams or plates,fails to fully capture their dynamic behaviors.In systems where space and mass are constrained,such as the battery support structures in electric aircraft,conventional absorbers and isolators are insufficient for effective vibration control.This study simplifies the battery support structure of electric aircraft as an integrated composite beam consisting of three interconnected beams,and investigated its structural dynamics properties and nonlinear vibration control under thermal conditions caused by battery heat.The nonlinear vibration control is performed using the Nitinol steel wire ropes(Ni Ti-ST),with nonlinear damping properties.The natural frequencies of system are determined using the Rayleigh-Ritz technique.Theoretical results are validated through both Finite Element Method(FEM)and hammer tests.Moreover,the dynamic equations are derived using the Lagrange method and discretized via the Galerkin Truncation Method(GTM).The Harmonic Balance Method(HBM)is used to evaluate the vibration responses of the integrated model,with further verification through the Runge-Kutta Method(RKM).The experiments are conducted to corroborate the theoretical analysis.The results show that the system frequency changes in stages with the increase of the stiffness of the integrated composite beam connection.Especially in the case of varying environments,as the temperature increases,the frequency of system will first increase to a certain maximum value and then gradually decrease.Furthermore,the NiTi-ST effectively reduces vibration in the integrated composite beam,particularly under varying temperatures and external excitations.展开更多
Unmanned combat aerial vehicles require lightweight,stealth-capable exhaust systems.However,traditional metallic nozzles increase radar detectability and reduce range,while advanced composites offer high performance b...Unmanned combat aerial vehicles require lightweight,stealth-capable exhaust systems.However,traditional metallic nozzles increase radar detectability and reduce range,while advanced composites offer high performance but are expensive.Therefore,to improve the operational range and survivability of unmanned combat aerial vehicles,a lightweight,high-temperature-resistant,oxidation-resistant,and low-observable composite exhaust nozzle is developed to replace conventional metallic straight-type nozzles.The nozzle features a double serpentine shape to reduce radar and infrared signatures and is manufactured as a monolithic structure using the filament winding process,accommodating the complex geometry and large size(length:1.8 m,width:0.8 m).The exhaust nozzle consists of a ceramic matrix composite made of silicon carbide fibers and a silicon oxycarbide matrix,which absorbs and scatters radio frequency signals while withstanding prolonged exposure to high-temperature(700℃)oxidizing environments typical of engine exhaust gases.The polysiloxane resin used to produce the silicon oxycarbide matrix poses significant challenges owing to its low tackiness and high viscosity variations depending on the presence of nanoparticles,making filament winding difficult.These challenges are addressed by optimizing resin viscosity and winding pattern design.As a result,the tensile strength of the composite specimens fabricated with the optimized viscosity increases by 228.03% before pyrolysis and 97.68%after pyrolysis,compared with that of the non-optimized specimens.In addition,the density and tensile strength of the composite processed via three cycles of polymer infiltration and pyrolysis increased by 13.08% and 80.37%,respectively,compared to those of the non-densified composite.High-temperature oxidation and flame tests demonstrate exceptional thermal and oxidative stability.Furthermore,when compared with carbon fiber-reinforced ceramic matrix composites,the developed composite exhibits a permittivity at least two levels lower and a reflection loss below7 dB within the frequency range of 9.3-10.9 GHz,underscoring its superior electromagnetic stealth performance.展开更多
为研究鸟撞飞机典型结构过程中鸟体姿态对鸟撞损伤的影响规律,以某型水陆两栖飞机-机翼前缘这一典型结构为研究对象,通过光滑粒子流体动力学(Smoothed Particle Hydrodynamics,SPH)耦合有限元法(Finite Element Method,FEM)建立鸟撞数...为研究鸟撞飞机典型结构过程中鸟体姿态对鸟撞损伤的影响规律,以某型水陆两栖飞机-机翼前缘这一典型结构为研究对象,通过光滑粒子流体动力学(Smoothed Particle Hydrodynamics,SPH)耦合有限元法(Finite Element Method,FEM)建立鸟撞数值模型,并通过鸟撞试验验证计算模型的准确性。最后,以试验修正后的机翼前缘数值模型为依托,研究分析鸟体俯仰和偏航12种撞击姿态下机翼前缘的损伤变形情况和冲击响应规律。结果表明,仿真分析和试验结果通过一致性验证;蒙皮凹坑和凹陷范围随鸟体姿态角增大而增大,鸟体剩余能量随之降低;俯仰角增大,前缘结构吸收的能量更多,蒙皮高应力区增大,结构更易破坏。因此对于鸟撞威胁影响更大的重要飞机结构的抗鸟撞安全评估应计入鸟体姿态的影响。研究结果可在飞机抗鸟撞设计与适航评估方面提供重要参考。展开更多
文摘旋转部件在交通运输、风能发电等诸多领域具有重要作用。三维数字图像相关方法(Three-Dimensional Digital Image Correlation,3D–DIC)作为一种非接触光学测量手段,能够获取旋转部件在运转过程中的全场位移、变形及振动信息,从而为故障诊断、健康监测以及气动结构优化设计提供重要数据支撑。本文对近年来3D–DIC技术的发展与应用进行了全面综述。首先介绍了3D–DIC技术的基本原理及其针对旋转物体的变形测量系统;针对大角度旋转测量中出现的退相关问题,详细阐述了国内外学者在初值估计和形函数设计等方面所提出的改进。随后,通过若干典型应用案例,展示了该技术相较于传统变形测量手段的优势。最后,对该技术的应用前景和发展趋势进行了展望。
基金supported by the National Natural Science Foundation of China(No.12272240)the Liaoning Revitalization Talents Program,China(No.XLYC2203197)。
文摘Traditional dynamic analysis of mechanical structures,often limited to individual beams or plates,fails to fully capture their dynamic behaviors.In systems where space and mass are constrained,such as the battery support structures in electric aircraft,conventional absorbers and isolators are insufficient for effective vibration control.This study simplifies the battery support structure of electric aircraft as an integrated composite beam consisting of three interconnected beams,and investigated its structural dynamics properties and nonlinear vibration control under thermal conditions caused by battery heat.The nonlinear vibration control is performed using the Nitinol steel wire ropes(Ni Ti-ST),with nonlinear damping properties.The natural frequencies of system are determined using the Rayleigh-Ritz technique.Theoretical results are validated through both Finite Element Method(FEM)and hammer tests.Moreover,the dynamic equations are derived using the Lagrange method and discretized via the Galerkin Truncation Method(GTM).The Harmonic Balance Method(HBM)is used to evaluate the vibration responses of the integrated model,with further verification through the Runge-Kutta Method(RKM).The experiments are conducted to corroborate the theoretical analysis.The results show that the system frequency changes in stages with the increase of the stiffness of the integrated composite beam connection.Especially in the case of varying environments,as the temperature increases,the frequency of system will first increase to a certain maximum value and then gradually decrease.Furthermore,the NiTi-ST effectively reduces vibration in the integrated composite beam,particularly under varying temperatures and external excitations.
基金supported by the Agency for Defense Development Grant Funded by the Korean Government(Grant No.912822501).
文摘Unmanned combat aerial vehicles require lightweight,stealth-capable exhaust systems.However,traditional metallic nozzles increase radar detectability and reduce range,while advanced composites offer high performance but are expensive.Therefore,to improve the operational range and survivability of unmanned combat aerial vehicles,a lightweight,high-temperature-resistant,oxidation-resistant,and low-observable composite exhaust nozzle is developed to replace conventional metallic straight-type nozzles.The nozzle features a double serpentine shape to reduce radar and infrared signatures and is manufactured as a monolithic structure using the filament winding process,accommodating the complex geometry and large size(length:1.8 m,width:0.8 m).The exhaust nozzle consists of a ceramic matrix composite made of silicon carbide fibers and a silicon oxycarbide matrix,which absorbs and scatters radio frequency signals while withstanding prolonged exposure to high-temperature(700℃)oxidizing environments typical of engine exhaust gases.The polysiloxane resin used to produce the silicon oxycarbide matrix poses significant challenges owing to its low tackiness and high viscosity variations depending on the presence of nanoparticles,making filament winding difficult.These challenges are addressed by optimizing resin viscosity and winding pattern design.As a result,the tensile strength of the composite specimens fabricated with the optimized viscosity increases by 228.03% before pyrolysis and 97.68%after pyrolysis,compared with that of the non-optimized specimens.In addition,the density and tensile strength of the composite processed via three cycles of polymer infiltration and pyrolysis increased by 13.08% and 80.37%,respectively,compared to those of the non-densified composite.High-temperature oxidation and flame tests demonstrate exceptional thermal and oxidative stability.Furthermore,when compared with carbon fiber-reinforced ceramic matrix composites,the developed composite exhibits a permittivity at least two levels lower and a reflection loss below7 dB within the frequency range of 9.3-10.9 GHz,underscoring its superior electromagnetic stealth performance.
文摘为研究鸟撞飞机典型结构过程中鸟体姿态对鸟撞损伤的影响规律,以某型水陆两栖飞机-机翼前缘这一典型结构为研究对象,通过光滑粒子流体动力学(Smoothed Particle Hydrodynamics,SPH)耦合有限元法(Finite Element Method,FEM)建立鸟撞数值模型,并通过鸟撞试验验证计算模型的准确性。最后,以试验修正后的机翼前缘数值模型为依托,研究分析鸟体俯仰和偏航12种撞击姿态下机翼前缘的损伤变形情况和冲击响应规律。结果表明,仿真分析和试验结果通过一致性验证;蒙皮凹坑和凹陷范围随鸟体姿态角增大而增大,鸟体剩余能量随之降低;俯仰角增大,前缘结构吸收的能量更多,蒙皮高应力区增大,结构更易破坏。因此对于鸟撞威胁影响更大的重要飞机结构的抗鸟撞安全评估应计入鸟体姿态的影响。研究结果可在飞机抗鸟撞设计与适航评估方面提供重要参考。
