In the topology optimization of compliant mechanisms, positional and shape factors significantly affect structural mechanical properties. The formation of concentrated hinge regions not only weakens structural strength but also hinders manufacturability. To this end, we propose a topology optimization method for hinge-free compliant mechanisms, incorporating geometric nonlinearity and utilizing the bi-directional evolutionary structural optimization (BESO) method. Initially, the design domain is discretized, where the 0-1 distribution of the BESO method prevents element distortion during nonlinear finite element analysis, thus enhancing numerical stability and convergence. The deformations of the compliant mechanism at the input and output are constrained under unit excitation, effectively suppressing the emergence of concentrated hinges. This leads to improved structural strength and manufacturability. Finally, hinge-free mechanisms are fabricated via additive manufacturing. Experimental results from samples show excellent agreement with finite element simulations, validating the effectiveness of the proposed hinge-suppression strategy in compliant mechanism design.

Thin-walled metal components frequently undergo multiaxial bending fatigue during operation, necessitating an experimental method to replicate loading conditions for investigating material properties. In this study, a novel biaxial bending test method using ultrasonic fatigue technology was proposed. The design involved a cruciform TC4 titanium alloy specimen tuned to a natural frequency of 20 kHz based on the principle of harmonic vibration, featuring vertically superimposed fourth-order and third-order bending modes to ensure the maximum stress region remained in the test section. Arc transitions were utilized in other regions to mitigate stress concentration. Finite element simulations and strain gauge tests were conducted to calibrate stress amplitudes in the specimens. Analysis of S-N curves, crack propagation paths, and fracture morphologies revealed the failure mechanisms of biaxial bending fatigue in the very high cycle regime under varied loading conditions. It was found that TC4 titanium alloy exhibited no fatigue limit in the very high cycle regime, showing a continuous downward trend. Owing to gradient stress distribution, biaxial bending fatigue demonstrated significantly longer fatigue life compared to uniaxial ultrasonic fatigue. Meanwhile, crack propagation behavior resembled conventional biaxial fatigue, producing H-shaped or Y-shaped cracks. Fracture surfaces exhibited a brittle characteristic in a large area of the crack initiation zone, with morphology primarily characterized by facets and tearing ridges formed through facet coalescence. In contrast to uniaxial bending fatigue, the facets in biaxial bending showed a batten pattern akin to multiaxial fatigue failure.

The fractional-order constitutive model traditional integer-order model in fields due to its fewer parameters and clearer physical meaning. In this study, the fractional-order standard linear solid model is adopted to deeply explore the linear creep buckling characteristics of viscoelastic thin plates under the force-coupling effect. To ensure the accuracy of numerical analysis, the Hermite-type radial basis function (HRBF) is used in this study. The calculation results high accuracy. that the stability of fractional-order viscoelastic thin plates significant time. Specifically, as time progresses, both the critical load and critical temperature of the thin plate show a downward trend, while the deformation displacement after buckling continuously increases.

This study investigates the electromechanical characteristics of a conical dielectric elastomer actuator in a non-ideal state, specifically focusing on the dielectric constant related to tensile deformation. By using the Ogden elastic strain energy function with multiple material constants and incorporating a linear permittivity that depends on the tensile rate, the constitutive relation for a non-ideal state is further deduced. The model is solved employing the shooting method, allowing for analysis of the mechanical performance and electromechanical stability of conical dielectric elastomers. We observe significant out-of-plane nonlinear axisymmetric deformation when the membrane is subjected to external force and external voltage, both with and without pre-stretch. By changing the voltage while maintaining constant external force, we identify model parameters and assess how varying electrostriction coefficients impact radial strength, circumferential stretch, and the true electric field. As the electrostriction coefficient decreases, tensile deformation in the membrane becomes increasingly uniform under no pre-stretch conditions, and the true electric field distribution tends to become more even. Under prestretch conditions, tensile deformation in the membrane remains stable, and the true electric field distribution is more consistent. When the electrostriction coefficient is sufficiently small, both the tensile deformation and the true electric field distribution tend to be stable, enhancing the overall stability of the dielectric elastomer. It is found that the prestretch condition exhibits greater stability than the no pre-stretch scenario. This research enhances our understanding of the electromechanical properties in non-ideal states, providing a theoretical foundation for the stable operation of conical dielectric elastomers in practical applications. The findings can guide the design of conical dielectric elastomer actuators, assisting engineers in optimizing design parameters to improve the performance and reliability of actuators.

Aircraft ground handling is significantly impacted by shimmy, which reduces landing gear lifespan and increases accident rates. This study employs a nonlinear energy sink (NES) to mitigate landing gear shimmy. Focusing on the landing gear of a light aircraft, a dynamic model incorporating an NES device is developed. First, the NES device's impact on the stability region and amplitude of landing gear shimmy is analyzed, demonstrating its effectiveness in mitigating shimmy. Beside, the study examines how parameters such as nonlinear stiffness, linear stiffness, mass, damping coefficient, and vertical distance from the NES device to the landing gear's S-axis influence damping. Furthermore, under specified optimization goals, suitable parameter ranges are selected and a genetic algorithm is employed for global optimization. Finally, the reliability of the optimized results is confirmed through time-domain analysis. This research indicates that NES devices can enhance landing gear anti-shimmy performance, offering significant practical value.

Magnesium (Mg), a lightweight metal material, is constrained in its applications due to poor plasticity and low strength at high temperatures. Graphene (Gr) possesses a large specific surface area and high strength, making it an ideal reinforcement for improving the mechanical properties of materials. A molecular dynamics (MD) simulation was employed to investigate the mechanical behaviors of single-crystal Mg and Gr/Mg composites under compressive loading. Through the analysis of stress-strain curves, atomic structure diagrams, and dislocation distributions, the microscopic deformation mechanisms of single-crystal Mg and Gr/Mg composites under compressive loading were explored. Additionally, the influence of factors such as the number of Gr layers, loading strain rate, and temperature on the mechanical properties of materials was studied. Results reveal that single-crystal Mg exhibits anisotropic characteristics under compressive loading. Addition of Gr enables the activation of difficult-to-initiate slip systems in the Mg matrix due to grain refinement. This leads to stress release and difficulty in initiating twinning deformation. Near the Gr interface, defects such as dislocations and twins nucleate and proliferate, effectively transferring the load to Gr, thereby elevating the average flow stress during the plastic deformation stage of the composites. Furthermore, the Mg matrix restricts the folding and bending of Gr, leading to an enhancement in material toughness. As a result, when the Gr/Mg composite is compressed along the [0 0 0 1] crystal direction to a strain of 0.35, the Gr remains intact without fracture. Dislocations in Gr/Mg composite materials cannot penetrate the Gr layer, thus suppressing Mg matrix damage. Increased dislocation lines can resist compressive plastic deformation. In composites featuring multiple layers of Gr, the yield stress, yield strain, and average flow stress during the plastic deformation stage increase with the number of Gr layers. Additionally, the yield strain is higher when Gr layers are separated compared to being stacked. Within the temperature range of 10 K-600 K, the elastic modulus and yield stress of Gr/Mg composites decrease with increasing temperature. However, the strain rate has a minor effect on the elastic modulus and average flow stress during the plastic deformation of Gr/Mg composites. Nonetheless, increasing the strain rate can enhance the yield stress and yield strain of the composites.

This study examines the tensile properties of skin suturing interfaces created through a silica gel reverse molding process, focusing on the reliability of clinical adhesive properties post-suturing. Four types of skin suturing interfaces, inspired by natural bionic structures, are designed, with primary attention on their tensile stiffness. An equivalent mechanical model is constructed using mechanical theories of suturing interfaces, and a theoretical model is developed to predict the tensile stiffness of each structure. Numerical simulations and physical experiments are conducted to analyze the brittle failure behavior and tensile failure modes of the suturing structures. The influences of shape factor, tooth tip angle, and tip region on the tensile properties of the interface are thoroughly investigated. A parameter mapping model using tensile strength as the evaluation index is constructed for each sensitive factor. It is found that the skin suturing interface exhibits brittle failure behavior, with the zigzag structure showing significantly higher tensile stiffness compared to other suturing structures. As the tooth tip angle increases, the stiffness of the suturing structure decreases, while the tip area enhances the tensile properties of the interface. These results are anticipated to help improve skin wound healing rate after clinical suturing.

The pseudo-Stroh formulism can transform the governing equations of multi-field coupling materials such as quasicrystals into a linear eigensystem, enabling the exact solution of multilayered structures with simply-supported boundary conditions. This provides an important reference for various numerical and experimental methods of quasicrystal beams in engineering practice. In this paper, the free vibration and bending problems of one-dimensional (1D) hexagonal quasicrystal (QC) laminated beams with functional gradients are investigated using the pseudo-Stroh formula. A simply-supported QC laminated beam is modeled, and the transfer matrix method is used to derive the exact solutions for natural frequency of free vibration and bending deformation displacements of the beam under simply-supported boundary conditions. The obtained results are compared with the existing ones to verify the accuracy and precision of the presented model. Numerical examples are provided to show the effects of high span ratio, layer thickness ratio, and functional gradient coefficient on the natural frequency, bending deformation, and mode shape of simply-supported 1D QC laminated beams under two different stacking sequences. The results show that natural frequency increases with the increase of functional gradient coefficient. Phonon displacement decreases while phason displacement increases with the increase of functional gradient coefficient under the two stacking sequences. Functional gradient coefficient and stacking sequence minimally affect phonon displacement modes but significantly impact phason displacement modes. Moreover, they notably affect phason stresses compared to phonon stresses in QC laminated beams. Thus, the optimal natural frequency and deformation displacement of a QC beam can be achieved by adjusting geometric size, stacking sequence, and functional gradient coefficient of the layered beam. These findings can provide theoretical references for various numerical methods and experimental studies on QC beams.

This study focuses on the aerothermoelastic characteristics of composite laminated panels with fully simply-supported boundaries in supersonic airflow, implementing macro fiber composites (MFCs) for active flutter-boundary control. In modeling the equation of motion, the influence of in-plane thermal load on transverse bending deflection is considered, and the aerodynamic pressure in supersonic airflow is calculated on the basis of supersonic piston theory. Motion differential equations of the structural system are derived from classical laminated plate theory and Hamilton's principle with the assumed mode method, then transformed into state space equations. By solving the state matrix eigenvalues, natural frequencies of the structural system are obtained. Aerothermoelastic characteristics of the laminated panel are analyzed via the frequency domain method, assessing the effects of ply angle and geometric parameters of the laminated panel on critical flutter aerodynamic pressure and critical buckling temperature. The proportional feedback control method is used to design the controller, and flutter boundaries of the laminated panel are computed under different control gain coefficients. Results demonstrate that the laminated panel with a ply angle of [90°/-90°/90°] exhibits the lowest aerothermoelastic stability across various aspect ratios. For larger ply angles, an increase in aspect ratio enhances the aerothermoelastic stability of the laminated panel. Adjusting MFC ply angles effectively increases critical flutter aerodynamic pressure. Moreover, the proportional feedback control method can significantly enhance flutter boundaries, but the control gain coefficient requires to be adjusted to ensure stability and performance of the control system. A control gain coefficient that is too small results in weak control, while one that is too large can destabilize the structural system.

This study investigated the dynamic response of continuous-density-graded aluminum foam sandwich tubes subjected to internal explosion loads. A finite element model for continuous-density-graded aluminum foam and sandwich tubes was established in polar coordinates using 3D-Voronoi technology. The influences of core density distributions, such as positive-gradient, negative-gradient, and V-shaped gradient including middle-high-gradient (high in the middle and low at both ends) and middle-low-gradient (low in the middle and high at both ends), core density gradient, assembly methods of tube walls and the core, and the length-to-diameter ratio of explosives on the anti-shock performance of the sandwich tube structure were analyzed. Results demonstrate that, for the same core density gradient, the maximum deformation of the outer tube in the sandwich tube with a negative-gradient core is the least, while the sandwich tube with a middle-low-gradient core exhibits the highest specific energy absorption, and the sandwich tube with a middle-high-gradient core shows the weakest anti-shock performance. As core density gradient increases, the maximum deformation of the outer tube in the sandwich tube with a negative-gradient core significantly decreases. The specific energy absorption for the sandwich tube with a middle-low-gradient core rises initially before declining, while the anti-explosion performance of the sandwich tube with a middle-high-gradient core deteriorates. Optimal bonding between tube walls and the core effectively improves the specific energy absorption of sandwich tubes with a uniform, negative-gradient, or middle-low-gradient core, but it also increases the maximum deformation of the outer tube. For varying length-to-diameter ratios of explosives, the maximum deformation of the outer tube in the sandwich tube with a negative-gradient core is smaller. The present work aims to provide valuable insights for designing such structures for protective engineering applications.

The connection conditions and vibration suppression methods of coupled shell structures have received much attention, particularly as these structures play a crucial role in aero-engine components. In this paper, the vibration characteristics of a rotating hard coating damping double-thin-walled cylindrical shell coupled structure under bolt connection conditions are studied. First, a discontinuous arc connection is constructed to simulate actual bolt connection conditions by improving the artificial spring distribution method of the continuous entire circumference. And the artificial spring technique is used to define the boundary conditions of the shell structure. Next, the strain energy of the hard-coating shell structure is determined based on Sander's shell theory. The effect of rotational speed is considered, and the Rayleigh-Ritz method is used to derive the dynamic equations of the shell structure. In addition, the efficient state space method is used for calculation. The rationality and accuracy of the theoretical methods are validated through literature comparisons and finite element analysis. Additionally, the effects of rotational speed, connection stiffness, hard-coating thickness, and boundary conditions on the traveling wave vibration characteristics of the shell structure are analyzed. The results show that the traveling wave frequency increases significantly when the connection stiffness is in the range of 10⁸～10¹⁰. Besides, the rotation leads to a separation phenomenon and an overall increasing trend in the traveling wave frequency. A greater hard coating thickness notably impacts the traveling wave frequency, exhibiting a maximum increase of 5.87% in the traveling wave frequency when the hard-coating thickness rises from 0 to 0.85 mm. These findings provide valuable theoretical insights and data support for the engineering design of hard-coating coupled double-thin-walled cylindrical shell structures.