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    2026,24(4):1-7, DOI: 10.6052/1672-6553-2026-004
    Abstract:
    Gauss’s principle of least constraint is a classical differential variational principle. Due to its generality, it is regarded as the most suitable fundamental principle for dynamics. Meanwhile, its formulation as a minimization problem has, with the rapid advancement of modern computational technology, renewed scholars’ interest in this long established principle. In textbooks on analytical mechanics, Gauss’s principle is usually introduced in two forms: the minimization of the Gauss constraint and the variational form in the sense of Gauss. The equivalence between these two forms constitutes the most fundamental issue in the theoretical extension of Gauss’s principle. This paper discusses the applicable conditions for the equivalence of the two forms of Gauss’s principle, and clearly states that when the constraints can be fully described by constraint equations, the two forms are both necessary and sufficient for each other. Furthermore, non ideal constraints are classified according to the representation of constraint forces, and the equivalence as well as the applicable conditions of the extended Gauss’s principle under different constraint force models are examined separately. The results show that the two forms are equivalent only when the non ideal constraint forces are independent of the ideal constraint forces. Compared with the minimization form, the variational form of Gauss’s principle is more general, with its theoretical foundation resting on Newton’s second law and the assumption of ideal constraints. Using the sliding motion of a simple rigid rod as an example, the existence conditions for the minimization form of Gauss’s principle are demonstrated. The discussion in this paper provides a fundamental analytical basis for extending Gauss’s principle to different constrained systems.
    2026,24(4):8-21, DOI: 10.6052/1672-6553-2025-100
    Abstract:
    Nonlinear dynamics sparse identification methods based on system sparsity priors (hereafter referred to as sparse modeling) represent a quintessential technique in data driven dynamic modeling. By reformulating dynamic modeling into sparse optimization problems, this method effectively achieves a balance between model interpretability and practical performance. However, traditional sparse optimization methods based on specific loss functions and regularizers often struggle to balance the accuracy, sparsity, robustness, and computational efficiency of the models. To address this, focusing on the core optimization problem of sparse modeling, this paper proposes a unified iterative solution framework based on the Alternating Direction Method of Multipliers (ADMM) to flexibly accommodate sparse optimization problems with diverse objectives. Within this framework, the loss functions encompass squared loss, absolute deviation loss, and Huber loss, while the regularization terms include the conventional one norm and its variants, alongside the one half quasi norm non convex regularizer. By comprehensively integrating non convex regularizers, robust loss functions, and accelerated iterative techniques, the proposed method systematically enhances the overall performance of the model across the aforementioned multidimensional metrics. Finally, the effectiveness of the proposed method is validated using the six dimensional Lorenz 96 chaotic system. The results indicate that: (1) the proposed framework can uniformly solve sparse optimization problems containing various combinations of loss functions and regularizers, encompassing non smooth/non convex optimization problems; (2) the introduction of non convex regularizers significantly enhances the ability to characterize the sparse features of the system; (3) the adoption of an accelerated iterative strategy effectively improves the efficiency of solving for sparse solutions.
    2026,24(4):22-29, DOI: 10.6052/1672-6553-2026-002
    Abstract:
    In this paper, a parameter optimal accelerated iterative learning control (AILC) algorithm is proposed to address the repetitive tracking control for discrete linear time varying systems within a finite time interval. In each iteration, based on the learning outcomes from the previous iteration, different extraction matrices are employed to discard data meeting the accuracy criteria, thereby reducing the model's dimensionality and the operational running time, which accelerates the learning control convergence speed and decreases the computational and storage resources required for system operation. The analysis of tracking error convergence leads to the derivation of the control gain design scheme through a parameter optimization method. Finally, simulation comparative experiments between the proposed parameter optimal AILC algorithm and the traditional iterative learning control (ILC) algorithm verify its effectiveness.
    2026,24(4):30-38, DOI: 10.6052/1672-6553-2025-057
    Abstract:
    In order to investigate the nonlinear dynamic characteristics of the star gear transmission system under wide frequency excitation, the time varying mesh stiffness is introduced, and the nonlinear dynamic analysis model of high speed star gear transmission considering the gyroscopic effect is established by combining the mesh error, tooth surface friction, gear backlash, etc. The nonlinear dynamic response of the star gear transmission system is obtained by solving the problem using the Runge Kutta method, and the nonlinear dynamic response of the star gear transmission system is further obtained by the bifurcation diagram of the mesh damping ratio of the system under wide frequency excitation. The nonlinear dynamic response of the star gear transmission system is obtained by using the Runge Kutta method, and furthermore, the bifurcation diagram of the meshing damping ratio of the system under the excitation is obtained. The results show that the high rotational speed will make the system's period interval decrease, the chaos interval lengthen, and the vibration amplitude become larger.
    2026,24(4):39-46, DOI: 10.6052/1672-6553-2026-005
    Abstract:
    A high quality factor (Q factor) is a critical parameter determining the sensing sensitivity and frequency stability of MEMS resonators. However, given the complex energy dissipation mechanisms at the micro/nano scale, conventional design approaches relying on geometric intuition struggle to maximize the Q factor within an environment of multiple coupled damping sources. To address this challenge, this paper proposes a topology optimization design methodology tailored for high Q MEMS beam resonators. First, grounded in thermoelasticity and elastic wave radiation theories, a comprehensive multiphysics simulation framework incorporating both thermoelastic damping (TED) and anchor loss is established. By integrating Perfectly Matched Layers (PMLs) with coupled thermal structural equations, the total energy dissipation of the resonator is quantified with high precision. Subsequently, a density based topology optimization algorithm is employed to evolve the structure of a silicon clamped clamped beam, with the objective of maximizing the Q factor of the fundamental mode. The study yields two novel topological configurations exhibiting significantly reduced energy loss. Physical mechanism analysis reveals that the optimized material distribution effectively interrupts transverse heat flow pathways, thereby suppressing TED, while simultaneously inducing a “soft clamping” redistribution of strain energy near the anchors to minimize energy leakage into the substrate. Simulation results demonstrate that, compared with a conventional solid straight beam of identical dimensions, the optimized designs achieve an approximately six fold enhancement in the overall Q factor. This work confirms the effectiveness of the multiphysics coupled topology optimization strategy, providing new theoretical guidance and technical pathways for the design of high performance MEMS resonators.
    2026,24(4):47-57, DOI: 10.6052/1672-6553-2026-006
    Abstract:
    With the increasing demands for pilot perception fcontrol consistency in modern high maneuverability flight missions, the six degree of freedom (6 DOF) human centrifuge has become an important platform for high fidelity complex flight simulation. This paper focuses on the dynamic flight simulation algorithm for the 6 DOF human rated centrifuge. First, a kinematic model of the centrifuge is established, and the perceptual characteristics of the human vestibular system are analyzed. On this basis, a model predictive control (MPC) method is proposed, which integrates the requirements of motion simulation with the mechanism of human perception. Under the MPC framework, the method comprehensively considers the physical constraints of the platform, coordinates the tracking errors of linear and angular motions, and introduces a human vestibular model to construct a pilot sensation optimization index, thereby achieving real time and high fidelity simulation of flight acceleration signals. Compared with the spherical washout algorithm, the proposed method shows significant improvements in both motion tracking accuracy and perceptual consistency. This study provides an effective motion control solution for achieving high fidelity dynamic flight simulation on a 6 DOF human rated centrifuge.
    2026,24(4):58-64, DOI: 10.6052/1672-6553-2026-001
    Abstract:
    Hyper velocity kinetic impacts, penetration detonations, and similar methods are important means to alter the established orbits of potentially threatening asteroids, and they are also hot topics of research both domestically and internationally. Using multi spacecraft formation technology can achieve the cumulative effects of kinetic impacts and penetrative detonation, resulting in greater orbital deflection. Multi spacecraft formations not only need to ensure accurate impacts on asteroid targets but also must maintain a specific formation configuration during flight. To address the formation control requirements, a formation keeping guidance method has been designed. Mathematical simulation results indicate that this method, while ensuring the target hit, meets the requirements for the cooperative formation configuration and the orientation of the formation plane normal during flight, demonstrating significant engineering application value.
    2026,24(4):65-74, DOI: 10.6052/1672-6553-2025-095
    Abstract:
    Acoustic sensing faces inherent challenges in balancing sensitivity and bandwidth for weak acoustic signal detection under extreme environmental conditions. This study proposes a self assembled gradient acoustic metamaterial driven by shape memory alloy, which optimizes sound pressure enhancement through dynamic regulation of material parameters and geometric characteristics. By establishing an analytical acoustic field model using effective medium theory and Wentzel Kramers Brillouin (WKB) approximation, the research reveals the synergistic regulation mechanisms of material elastic modulus, density gradient, and frequency characteristics on acoustic wave propagation properties. Multiphysics coupled simulations verify the acoustic pressure amplification patterns across the 1~13 kHz broadband range. Results indicate that adjusting geometric gradient parameters to modify effective refractive index can overcome the sensitivity bandwidth trade off in conventional sensors: large taper angle structures (60°) achieve rapid acoustic energy amplification in high frequency ranges (9.7~12.9 kHz), while small taper angle designs (30°) effectively extend the gain coverage for low frequency waves (2.1~5.3 kHz). The developed metamaterial with dynamic reconfigurability provides a novel technical approach for weak acoustic signal detection in industrial equipment, offering theoretical foundations and experimental validation to resolve performance contradictions in traditional acoustic sensors. This advancement holds significant implications for enhancing fault diagnosis reliability in complex operational conditions.
    2026,24(4):75-85, DOI: 10.6052/1672-6553-2025-101
    Abstract:
    A 242.4 m high reinforced concrete hyperbolic natural draft cooling tower is taken as the engineering prototype. Rigid model wind tunnel pressure tests are conducted, and Reynolds number effects are simulated by controlling the surface roughness of the model. With an appropriate roughness arrangement, the measured shape coefficients agree very well with the design curves for the smooth tower and the K1.0 ribbed tower specified in the Code for Design of Industrial Circulating Cooling Water. The measured pressure time histories are then converted to the prototype scale according to similarity laws and applied to a finite element model that includes both the shell and the V shaped concrete filled steel tube columns. The wind induced radial displacement responses and wind vibration coefficients of the cooling tower under the basic wind action are obtained. The results show that the wind vibration coefficient increases monotonically along the height, reaching about 1.48 near the throat, which is significantly lower than the code value of 1.9. When the structural damping ratio decreases from 5% to 2%, the increase in wind vibration coefficient is less than 1%, indicating that the response is mainly governed by buffeting produced by turbulent wind and is not sensitive to damping within this range. Considering the surrounding buildings of the power plant, the overall changes in wind pressure distribution and wind vibration coefficients are small, and only for several unfavorable wind directions does the maximum wind vibration coefficient increase slightly to about 1.66.
    2026,24(4):86-94, DOI: 10.6052/1672-6553-2026-003
    Abstract:
    Bridge frequency is an important parameter reflecting the structural characteristics of a bridge. Using a vehicle equipped with an acceleration sensor to pass over the bridge for frequency identification avoids the inefficiencies, complexity, and high costs associated with installing sensors directly on the bridge. By installing a lightweight ‘ single axis cantilever amplifier’ with a rigid cantilever on the crossing vehicle and combining it with Fast Fourier Transform (FFT), the visibility of bridge frequencies can be significantly improved. The effects of different parameters on bridge frequency identification are discussed. The results show that: the resolution of bridge frequency decreases as vehicle speed increases; increasing the cantilever length is beneficial for bridge frequency identification; vehicle damping has little effect on bridge frequency identification; road surface roughness is unfavorable for frequency identification, but after introducing multiple vehicle excitations, the first few bridge frequencies can be identified; due to the energy dissipation from the bridge damping, the acceleration amplitude corresponding to the first few identified bridge frequencies is significantly reduced, yet the effect of the single axis cantilever amplifier remains obvious.
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    2014,12(3):269-273, DOI: 10.6052/1672-6553-2014-043
    [Abstract] (3934) [HTML] (0) [PDF 336.30 K] (22153)
    Abstract:
    Aiming at the problem that the longitudinal modes of structural system of rocket need to be identified from its integral modes in engineering, a method that automatically identifies the longitudinal modes of structural system of rocket was proposed according to the theory of modal effective mass. Taking the vibration characteristics of system with lumped mass as a computing example, applying the finite element software, the beam model of system with lumped mass was established, and the longitudinal modes of the system were automatically identified based on the method. Compared with the system modal information calculated by the method of modal analysis, this automatic identification method not only can accurately identify the longitudinal modes of vibrating system, but also has automatic and high efficiency identification feature. It provides a theoretical basis for the dynamic model of POGO vibrating system in liquid rockets and other model of engineering systems to be accurately and promptly established.
    2017,15(5):385-405, DOI: 10.6052/1672-6553-2017-039
    [Abstract] (2475) [HTML] (0) [PDF 1.91 M] (19724)
    Abstract:
    In this review article, the growth and related academic communications in the dynamics of multibody systems are firstly surveyed. Then, the recent advances in the numerical algorithms for solving the dynamic equations of flexible multibody systems, the contact/impact dynamics of flexible multibody systems and the deployment of flexible space structures are systematically reviewed, together with several open problems of concern. Finally, some suggestions are made for the prospective researches on the dynamics of flexible multibody systems.
    2014,12(3):193-200, DOI: 10.6052/1672-6553-2014-046
    [Abstract] (3725) [HTML] (0) [PDF 748.46 K] (19658)
    Abstract:
    The spacecraft's ability to adapt to the harsh dynamics environment is critical for the whole space mission. Vibration test control technology is the key part of the dynamic environment test. The current progress, fundamental principles and key techniques development level of the spacecraft and vibration control algorithms overseas were analyzed. The basic ideas, effective ways and suggestions were given to domestic following research.
    2014,12(1):18-23, DOI: 10.6052/1672-6553-2013-068
    [Abstract] (3528) [HTML] (0) [PDF 1.13 M] (19120)
    Abstract:
    The electromechanical coupling model of cantilevered piezoelectric harvester was developed by considering the nonlinearities of piezoelectric material, based on Hamilton theory, Rayleigh-Ritz method, Euler-Bernoulli beam theory and constant electrical field across the piezoelectric element. The response characteristics of the system were investigated numerically, and the influences of piezoelectric material nonlinear coefficient on the system response were analyzed. By exploring the nonlinear characteristics of the piezoelectric vibrator near the resonant frequency, the nature of the multi-solutions and jump phenomena in the resonance region was revealed. The results were verified experimentally. which provides a theoretical basis for the study of nonlinear mechanism of piezoelectric power generation system.
    2014,12(3):243-247, DOI: 10.6052/1672-6553-2014-054
    [Abstract] (2962) [HTML] (0) [PDF 1.07 M] (18701)
    Abstract:
    Random vibration test is very important to the aerospace equipment. The windage of ASD outside the frequency bandwidth was analyzed. The reason, premonition, affection and effective way were given. And the commonly used random vibration test and vibration test metrology standard for the ASD outside the frequency bandwidth were analyzed.
    2016,14(2):97-108, DOI: 10.6052/1672-6553-2015-009
    [Abstract] (2976) [HTML] (0) [PDF 1.87 M] (18537)
    Abstract:
    Based on the current research status of multi agents system control theory and technology, the paper makes a detailed overview for unmanned ground systems. From two aspects of behaviour and task cooperative control for multi agents, the relevant theory and application problem is discussed. Moreover, some existed open problems are presented and a possible future development is proposed. For unmanned ground systems, cooperative control will be of great importance in promoting social and military benefits and maximizing the executive function of ground mission.
    2015,13(5):361-366, DOI: 10.6052/1672-6553-2014-064
    [Abstract] (1672) [HTML] (0) [PDF 826.19 K] (18342)
    Abstract:
    Dynamic and control systems often contain uncertain parameters that may result in uncertain predictions. In the interest of quantifying the effects of parameter uncertainties on response variability, this paper develops a stochastic response surface based method for the sensitivity analysis of uncertain parameters. Stochastic response surfaces were firstly constructed to describe the explicit relationships between uncertain parameters and responses. Then partial derivations were performed on the mathematical expressions of stochastic response surfaces in order to obtain sensitivity indices that simultaneously embody the effects of parameter means and standard deviations. Lastly, the developed method has been verified against a numerical cantilever beam containing uncertain geometric and material parameters. The sensitivity analysis results were compared with those given by the analysis of variance method.
    2014,12(3):225-229, DOI: 10.6052/1672-6553-2014-051
    [Abstract] (2895) [HTML] (0) [PDF 1.38 M] (18293)
    Abstract:
    Based on the staggered solution procedure of ANSYS and CFX software, the fluid structure coupling response of projectile during tail slapping has been researched. Structural response was simulated by using FEM and flow field was simulated by using inhomogeneous model and SST turbulence model. Finally, the influences of fluid structure coupling effect have been analyzed and the change law of body stress has been given.
    2013,11(1):12-19, DOI: 10.6052/1672-6553-2013-003
    [Abstract] (2954) [HTML] (0) [PDF 530.95 K] (18159)
    Abstract:
    The dynamics of the whole aero-engine system has always been the important part that cannot be neglected in the research and design of the engine, as the framework of the engine, the vibration of the casing directly reflects the level of the whole aero engine vibration. In this paper, an analysis was made on the research of the problems and fault classification of aero-engine casing dynamics, and an overview was made on the research of present situation, development trend, problems and solutions of the domestic and foreign of casing dynamics, which expanded the present situation of the Inclusiveness problems of aero-engine casing dynamics. Finally, some proposals were put forward for the development of the casing dynamics suitable for our country aero-engine technology level.
    2008,6(4):301-306, DOI:
    [Abstract] (1642) [HTML] (0) [PDF 0.00 Byte] (17798)
    Abstract:
    The problem of P and PI feedback control to a time delay system was investigated,with the emphasis on the determination of the feedback gains that ensured the asymptotical stability of the delayed system. By means of Lambert W function,the feedback gain of P control can be expressed explicitly,so that the optimal feedback gain can be easily obtained. For the system under a PI control,the stable region of the feedback gains was determined on the basis of stability switches and D subdivision,and the optimal feedback gains that enabled the system to admit maximal stable margin were figured out numerically by using Lambert W function. From the viewpoint of computation,the present method is much simpler than the available methods.
    2012,10(1):21-26, DOI:
    [Abstract] (1195) [HTML] (0) [PDF 567.09 K] (17758)
    Abstract:
    A discrete finite dimensional dynamical model was built to describe the space large overall motion of tethered satellite system with an infinite dimensional viscoelastic tether in a long time. The tethered satellite system is a complex nolinear dynamic system. Considering the tether’s viscoelasticity, distributed mass and space form, the established improved bead model can meticulously describe the tether’s vertical and horizontal vibration. According to tether’s characteristic of tensile and not compressive, the slack tether unit model was set up to accurately reflect real stress of tether. The determination of the number of degrees of freedom of the system was studied. Based on numerical integral calculation, the dynamic response was obtained via numerical simulation of the deployment, retrievement and retainment process of tethered satellite system in a long time. The result is convergent. The simulation proves the important role of the stable equilibrium position in the dynamics of tethered space system.
    2014,12(2):183-187, DOI: 10.6052/1672-6553-2014-025
    [Abstract] (1722) [HTML] (0) [PDF 811.52 K] (17498)
    Abstract:
    PMSM due to little harmonic, high precision torque, commonly is used in the servo system and the high performance speed control system. In this paper,the physical model of PMSM is simplified and the mathematical model of the motor is established in order to facilitate research.Thispaper uses id=0 control manner which is the simplest manner is vector control methods,motor electromagnetic torque equation is established based on rotor field oriented vector control.The system model, speed and current control block are build and simulated with MATLAB/Simulink.Simulation results shows that the waveform is consistent with thoretical analysis,the model has fast response and small overshoot.The system runs stably with good dynamic and static characteristics. The simulation makes full use of modularization design. All the parameters and their influence on the system can be changed and observed.It also can easily validate the control strategies and select the most suitable one. So this kind of simulation is good for system design and adjusting and validating.
    2014,12(3):205-209, DOI: 10.6052/1672-6553-2014-059
    [Abstract] (2506) [HTML] (0) [PDF 467.15 K] (15042)
    Abstract:
    This paper investigated the passive nonlinear vibration control method used for energy absorbing in structures of spacecrafts. The structure and the dynamic model of the nonlinear energy sink which could adapt to the space environment were proposed. As nonlinear spring could not be acquired easily in reality, we proposed a new design for the NES based on employing an asymmetric NES force which was generated by two pairs of aligned permanent magnets. Then, the dynamic model for a cantilever beam structure coupled with nonlinear energy sink had been built theoretically. In addition, the passive vibration suppression effect of the nonlinear energy sink on the cantilever beam structure under transient excitation had been analyzed through Galerkin method and numerical analysis method. The results showed that the NES acquired up to 92% dissipation of the system energy imposed by shock excitation, hence the NES could adapt to the space environment and improve the reliability of space system.
    2014,12(3):283-288, DOI: 10.6052/1672-6553-2014-061
    [Abstract] (3599) [HTML] (0) [PDF 479.50 K] (14365)
    Abstract:
    A method was presented to analyze the nonlinear flutter. Based on this method, the flutter characteristics of the high aspect wing were illustrated. The numerical results show that the flutter speed is decreased when the first horizontal bending mode involved. Secondly, this study discussed how the main direction of the composite influenced the character of the nonlinear vibration and flutter, and established the method of the flutter clipping to the high aspect wing. And the result shows that the stiffness of structure can be changed by changing the main direction of the composite. It mainly changes the horizontal bending mode, makes the main direction tend to the trailing edge, and then makes the section line move to the leading edge. Further analyzing the nonlinear flutter reveals that it is the changing of the horizontal bending mode that causes the flutter speed change obviously. And by the section line of this mode moves ahead, the flutter speed will become larger. In the study, two examples were illustrated to validate its truthiness.
    2013,11(4):357-362, DOI: 10.6052/1672-6553-2013-041
    [Abstract] (1822) [HTML] (0) [PDF 350.50 K] (12358)
    Abstract:
    At present, the main task of designing a mounting system of automotive engine powertrain is to select appropriate stiffness, position and angle of mounting components so that free-vibration modal frequency of the mounting system can avert from the exciting-force frequency at the idle speed of the engine and the natural frequency of vibration of the vehicle body and that the decoupling degree of each mode shape is increased as far as possible, so as to improve the vibration-isolation effect of the mounting system. The design of a mounting system based on strict decoupling at predetermined frequencies is to make the modal frequencies of the designed mounting system completely equal to the frequencies predetermined in accordance with the frequency planning of automotive design, and to enable strict decoupling of each mode shape of each mode, i.e., the decoupling degree of vibration energy in every direction equals to 1. Based on a free-vibration equation for a mounting system, this paper presents an equation system for designing a mounting system with strict decoupling at predetermined frequencies, provides a solving method for this equation system by using the theory of generalized inverse matrix or method of constructing function, so as to provide an optimal design method more efficient and simpler than the current modal optimization method of mounting system. Relevant example has validated the correctness of equations and solving method of the strict-decoupling design at predetermined frequencies.
    2016,14(3):247-252, DOI: 10.6052/1672-6553-2015-052
    [Abstract] (2309) [HTML] (0) [PDF 2.18 M] (9606)
    Abstract:
    Tires are the only carrier of the contact between the vehicle and road surface. Their mechanical property is important for analysis and control on the vehicle dynamic response. At present, the tire simulation mostly focuses on the steady state model. But it can not describe the dynamic characteristic of the tire accurately. Therefore, it plays a significant role to add the dynamic tire model in the vehicle dynamics simulation. The tire friction model in the multi body dynamical software ADAMS is static, where the friction is regarded as a static value. However, in actual, the friction between the tire and road surface is dynamic, and it should be a dynamic function of the relative velocity and displacement. To this end, in this paper, the dynamic tire LuGre model using the Matlab/Simulink software is constructed. Through connecting the interface with Adams/Car, co simulation between the vehicle model and the simulink tire model is carried out in order to achieve the dynamic contact between tire and road and improve the accuracy of vehicle system analysis.
    2014,12(1):36-43, DOI: 10.6052/1672-6553-2013-110
    [Abstract] (2616) [HTML] (0) [PDF 2.22 M] (8085)
    Abstract:
    The coupling nonlinear dynamic model of dual rotor system was established by using finite element method, and then the critical speed of revolution and mode shape were calculated by using the software MATLAB. In addition, the unbalance responses of dual rotor system were studied, and the vibration performances in different speeds of dual rotor casing systems were obtained. The research provides a theoretical basis for the design of the dual rotors system in engineering.
    2014,12(3):253-258, DOI: 10.6052/1672-6553-2014-056
    [Abstract] (2498) [HTML] (0) [PDF 1.00 M] (6490)
    Abstract:
    Taking account of the structural stiffness and the low order vibration frequencies, two schemes of multi-objective topology optimization were proposed to obtain the best aircraft lifting-surface structural design. Based on penalized density theory, the scheme one (named as constrain method) is to convert the multi-objective optimization to single-objective optimization by considering the minimum structural mass as the objective with constraints of reference points displacements and the low order vibration frequencies. The scheme two (named as the combination of constrain method and criterion function method) settles the multi-objective optimization by defining combined compliance index (CCI) as the objective, with the constraints of volume fraction and the low order vibration frequencies. The CCI is the function of structural compliance and low order vibration frequencies. Numerical results demonstrate the proposed schemes not only realize reducing the structural mass but also raise the first and second order frequencies.
    2014,12(3):201-204, DOI: 10.6052/1672-6553-2014-048
    [Abstract] (2592) [HTML] (0) [PDF 296.79 K] (6181)
    Abstract:
    Non-linear factors cannot be avoided in the design of aircraft structures. In this paper, a two-degree-of-freedom airfoil and cubic stiffness nonlinearities in pitching degree-of-freedom operating in supersonic flight speed regimes has been analyzed. The averaging method and the theory of flutter were used to analyze the nonlinear dynamic system of the dualistic airfoil in the supersonic flow. Then the correctness of the theoretical calculation was verified by numerical calculation, and the analysis result was given.
    2014,12(1):62-66, DOI: 10.6052/1672-6553-2013-097
    [Abstract] (2048) [HTML] (0) [PDF 832.87 K] (5607)
    Abstract:
    A spline finite point method was presented to study the natural frequency of arch. The displacement mode shape function of the arch free vibration was simulated with a linear combination of cubic B spline. The free vibration frequency equation of arch structures was derived according to Hamilton principle, in which the effect of the dead load was considered. Meanwhile, the effect of the dead load on the natural frequency of arch structures was analyzed. The results show that the natural frequency of arch is reduced. The effect of influence depends on the stiffness of the arch itself. When the arch stiffness is certain, the bigger the rise span ration and the radius to thickness ration, the higher the effect of the dead load on the natural frequency of arch structures.

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