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| 1 | Bifurcation and chaos of the bladed overhang rotor system with squeeze film dampers显示文摘To study the nonlinear dynamic behavior of the bladed overhang rotor system with squeeze film damper (SFD), a blade-overhang rotor-SFD model is formulated using the lumped mass method and the Lagrange approach. The cavitated short bearing model is employed to describe the nonlinear oil force of the SFD. To reduce the scale of the nonlinear coupling system, a set of orthogonal transformations is employed to decouple the one nodal diameter equations of blades, which are coupled with the dy- namical equations of the rotor, with other equations of blades. In this way, the original system with 16+4n (n≥3) degrees of freedom (DoF) is reduced to a system with 24 DoF only. Then the parametric excitation terms in the blade-overhang rotor-SFD model are simplified in terms of periodic transforma- tions. The coupling equations are numerically solved and the solutions are used to analyze the dy- namic behavior of the system in terms of the bifurcation diagram, whirl orbit, Poincaré map and spec- trum plot. A variety of motion types are found such as multi-periodic, quasi-periodic, and chaotic mo- tions. Moreover, the typical nonlinear dynamic evolutions including the periodic-doubling bifurcation and reverse bifurcation are noted. It is noticed that there exist apparent differences in the dynamic behavior between the blade-overhang rotor-SFD models without and with considering the effect of blades. | CAO DengQing WANG LiGang CHEN YuShu HUANG WenHu | 2009 | Science China(Technological Sciences)2009，52，3： | 5 |
| 2 | Maneuver control of the hypersonic gliding vehicle with a scissored pair of control moment gyros显示文摘A maneuver control approach using a scissored pair of control moment gyros is proposed to improve the penetration ability of a hypersonic gliding vehicle(HGV) with a relatively high lift-drag ratio. Then, a multivariable strong coupling nonlinear bank-toturn dynamical model is established for the case of lateral maneuvering of an HGV equipped with a scissored pair of control moment gyros. According to the requirement of coordinated turning of the HGV in a lateral maneuver, a decoupling controller based on feedback linearization and a linear quadratic optimal algorithm is designed. Finally, the large airspace maneuvering trajectories of the HGV including S-shaped, cycloid and spiral maneuvering modes are designed by applying overload control technology. Simulations demonstrate that the designed maneuvering trajectory significantly increases the airspace range and flexibility of the vehicle. The coordinated turn control system achieves an accurate and rapid tracking of the maneuvering trajectories in large airspace. | ZHAO Kun CAO DengQing HUANG WenHu | 2018 | Science China(Technological Sciences)2018，61，8： | 5 |
| 3 | Modeling and analysis of cantilever beam with active-passive hybrid piezoelectric network显示文摘The active-passive hybrid piezoelectric network (APPN) is investigated to reduce the vibration of cantilever beam. Hamilton's principle with the Rayleigh-Ritz method is used to derive the equations of motion of the beam with the APPN. Only one piezoelectric actuator is bonded on the cantilever beam, so in the segment of the beam where the piezoelectric actuator is attached, the neutral axis is not the geometric center of the beam. This change on the neutral axis is considered in the process of deriving equations. Selecting RL circuit as passive shunt circuit, open-loop analysis is performed to gain insight into the passive damping features. Velocity feedback control is then employed to analyze the characteristics of the closed-loop system. Numerical results show that the APPN has a significant effect on vibration suppression, especially at narrow frequency bands. On this basis, variable RL circuit is proposed and analyzed for broadband vibration attenuation. Numerical simulations illustrate that this scheme is effective and feasible. | LI MingMing FANG Bo CAO DengQing HUANG WenHu | 2013 | Science China(Technological Sciences)2013，56，9： | 4 |
| 4 | Rigid-flexible coupling dynamic modeling and vibration control for flexible spacecraft based on its global analytical modes显示文摘In this study, we used global analytical modeswfny(GAMs) to develop a rigid-flexible dynamic modeling approach for spacecraft with large flexible appendages(SwLFA). This approach enables the convenient and precise calculation of the natural characteristics for designing an attitude control law for the spacecraft while simultaneously suppressing the active vibration of its flexible appendages. We simplify the flexible spacecraft as a rigid-flexible coupling hub-beam system with tip mass and derive the system's governing equations of motion based on Hamilton's principle. By solving the linearized form of those equations with their associated boundary conditions, we obtain the frequencies as well as the corresponding GAMs of flexible spacecraft,which we use to discretize the equations of motion. Using this approach, we performed numerical simulations to investigate the system's global modes and assess the performance of the controller based on the GAM model. The results reveal that the GAM model can be used to directly calculate the exact global modes of SwLFAs and that the controller based on the discrete GAM model can achieve a control-index for a SwLFA in a shorter time with less input energy than other methods. | LIU Lun CAO DengQing WEI Jin | 2019 | Science China(Technological Sciences)2019，62，4： | 3 |
| 5 | On the stability of stay cables under light wind and rain conditions 显示文摘 | Burton D Cao Dengqing Tucker R W | 2005 | Journal of Sound and Vibration2005，279，12： | 1 |
| 6 | Nonlinear dynamics of elastic rods using the Cosserat theory: modelling and simulation 显示文摘 | CAO Dengqing TUCKER R W | 2008 | International Journal of Solids and Structures2008，45，2： | 1 |
| 7 | Nonlin- ear dynamic modelling for MEMS components via the Cosserat rod dement approach显示文摘 | CAO Dengqing LIU Dongsheng WANG C H-T | 2005 | Journal of Micromechanics and Microengineering2005，15，6： | 1 |
| 8 | Nonlinear Vibration Characteristics of a Flexible Blade with Friction Damping Due to Tip-Rub显示文摘 | Cao Dengqing Gong Xiaochun Wei Dong | | 0，，1： | 1 |
| 9 | Nonlinear coupled dynamics of flexible blade-rotor-bearing systems 显示文摘 | Wang Ligang Cao Dengqing Huang Wenhu | 2010 | Tribology International2010，43，4： | 1 |
| 10 | A novel order reduction method for nonlinear dynamical system under external periodic excitations显示文摘The concept of approximate inertial manifold (AIM) is extended to develop a kind of nonlinear order reduction technique for non-autonomous nonlinear systems in second-order form in this paper.Using the modal transformation,a large nonlinear dynamical system is split into a 'master' subsystem,a 'slave' subsystem,and a 'negligible' subsystem.Accordingly,a novel order reduction method (Method I) is developed to construct a low order subsystem by neglecting the 'negligible' subsystem and slaving the 'slave' subsystem into the 'master' subsystem using the extended AIM.As a comparison,Method II accounting for the effects of both 'slave' subsystem and the 'negligible' subsystem is also applied to obtain the reduced order subsystem.Then,a typical 5-degree-of-freedom nonlinear dynamical system is given to compare the accuracy and efficiency of the traditional Galerkin truncation (ignoring the contributions of the slave and negligible subsystems),Method I and Method II.It is shown that Method I gives a considerable increase in accuracy for little computational cost in comparison with the standard Galerkin method,and produces almost the same accuracy as Method II.Finally,a 3-degree-of-freedom nonlinear dynamical system is analyzed by using the analytic method for showing predominance and convenience of Method I to obtain the analytically reduced order system. | CAO DengQing,WANG JinLin & HUANG WenHu School of Astronautics,Harbin Institute of Technology,PO Box 137,Harbin 150001,China | 2010 | Science China(Technological Sciences)2010，53，3： | 1 |
| 11 | hnpact Vibration Characteristics of a Shnauded Blade with Asymmetric Gaps Under Wake flow Excitations显示文摘 | Shiming Chu Dengqing Cao Shupcng Sun | 2013 | Nonlinear Dvn2013，72，： | 1 |
| 12 | Nonlinear coupled dynamics of flexible blade-rotor-bearing systems显示文摘 | WANG Ligang CAO Dengqing HUANG Wenhu | 2010 | Tribology International2010，43，4： | 1 |
| 13 | Stability Robustness Measures of Linear Discrete-Time Systems with Structured Perturbations | CAO Dengqing(Institute of APPlied Mechanics, Southwest Jiaotong University, Chengdu 610031, China) | 1999 | Systems Science and Systems Engineering1999，9，1： | 0 |
| 14 | Investigation on dynamic characteristics of a rod fastening rotor-bearing coupling system with fixed-point rubbing显示文摘The aim of this paper is to gain insight into the nonlinear vibration feature of a dynamic model of a gas turbine.First,a rod fastening rotor-bearing coupling model with fixed-point rubbing is proposed,where the fractal theory and the finite element method are utilized.For contact analysis,a novel contact force model is introduced in this paper.Meanwhile,the Coulomb model is adopted to expound the friction characteristics.Second,the governing equations of motion of the rotor system are numerically solved,and the nonlinear dynamic characteristics are analyzed in terms of the bifurcation diagram,Poincarémap,and time history.Third,the potential effects provided by contact degree of joint interface,distribution position,and amount of contact layer are discussed in detail.Finally,the contrast analysis between the integral rotor and the rod fastening rotor is conducted under the condition of fixed-point rubbing. | Yang YANG HJOUYANG Jin ZENG Hui MA Yiren YANG Dengqing CAO | 2022 | Applied Mathematics and Mechanics(English Edition)2022，43，7： | 0 |
| 15 | Vibration characteristics and flutter analysis of a composite laminated plate with a store显示文摘The effects of an external store on the flutter characteristics of a composite laminated plate in a supersonic flow are investigated. The Dirac function is used to formulate the interaction between the plate and the store. The first-order piston theory is used to describe the aerodynamic load. The governing equation of the composite laminated plate with an external store is established based on the Hamilton principle. The mode shapes are constructed by the admissible functions which are a set of characteristic orthogonal polynomials generated directly by the Gram-Schmidt process, and the boundary constraint is modeled as the artificial springs. The frequency and mode shapes of the plate under different boundaries are determined by the Rayleigh-Ritz method. The validity of the proposed approach is confirmed by comparing the results with those obtained from the finite element method(FEM). The effects of the mounting position, the center of gravity position and the mounting points spacing of the external store on the flutter boundary are discussed for both the simply supported and cantilever plates, respectively,which correspond to the two installation sites of the external store, i.e., the belly and wings of the aircraft. | Huagang LIN Dengqing CAO Yuqian XU | 2018 | Applied Mathematics and Mechanics(English Edition)2018，39，2： | 0 |
| 16 | Stability Criteria for Large-Scale Linear Systems with Structured Uncertainties显示文摘StabilityCriteriaforLarge┐ScaleLinearSystemswithStructuredUncertaintiesCaoDengqingInstituteofAppliedMechanics,SouthwestJiaoto... | Cao Dengqing Institute of Applied Mechanics,Southwest Jiaotong University,Chengdu 610031,China | 1996 | Journal of Modern Transportation1996，13，2： | 0 |
| 17 | Aero-Elastic Flutter Characteristics of Laminated Composite Panel Embedded with Shape Memory Alloy Wires显示文摘The effects of shape memory alloy( SMA) wires on the natural frequency,flutter boundary and amplitude of limit cycle oscillation( LCO) of a laminated composite panel are investigated. The classical plate theory as well as von-Karman strain-displacement relation are used to formulate the nonlinear dynamic model of the smart laminated panel. The aerodynamic loadings are simulated by the third order piston theory. The thermomechanical behavior of SMA wires is estimated according to one-dimensional Brinson SMA model. The effects of SMA wires temperature,pre-strain,volume fraction and orientation on flutter boundary and amplitude of LCO of the panel are analyzed in detail. | Dengqing Cao Chonghui Shao Yuqian Xu Hai Zhao | 2017 | Journal of Harbin Institute of Technology(New Series)2017，24，5： | 0 |
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