Chinese Academy of Aerospace Aerodynamics

Beijing, China

Chinese Academy of Aerospace Aerodynamics

Beijing, China

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Han H.,Beihang University | Han H.,Chinese Academy of Aerospace Aerodynamics | Lu Z.,Beihang University | Zhang J.Z.,Beihang University | Guo J.,Beihang University
Mechanics of Advanced Materials and Structures | Year: 2013

Taking the longitudinal deformation into consideration, a two-dimensional beam theory is proposed, and a new layered beam model is established subsequently for composite laminates with multiple through-the-width delaminations. The undelaminated portion is regarded as separate beams along the layer interfaces, and the interface continuities are satisfied using the generalized variational principle. Comparisons of the present analytical solutions with three-dimensional finite element results and classical beam model solutions are made to verify the accuracy and efficiency of the present model. The effects of the geometrical parameters of the delamination on the deflection and the energy release rate are discussed. © 2013 Copyright Taylor and Francis Group, LLC.


Liang F.,Chinese Academy of Aerospace Aerodynamics | Cong H.,Chinese Academy of Aerospace Aerodynamics | Ji Z.,Chinese Academy of Aerospace Aerodynamics | Zhao Y.,Beihang University
Proceedings of the 28th Chinese Control and Decision Conference, CCDC 2016 | Year: 2016

Halbach array has been widely applied to improve the magnetic and force performance of tubular linear motors for its attractive features. Conventionally, the Halbach permanent magnet (PM) array is mounted inside the windings to be the mover. Herein, the other kind of structure in which Halbach array is mounted outside the windings also draws our interest. The magnetic and force performances of the two kinds of motors are analyzed with Bessel functions and Lorenz Law. The analytical models of the magnetic field and the output force are then validated by the numerical simulations, respectively. Optimization analysis with a penalty function method is conducted as follows, and the magnetic and force performance of the two topologies are compared. The result of this paper can provide a basis for the generic motor designs. © 2016 IEEE.


Zhu Z.-B.,Chinese Academy of Aerospace Aerodynamics | Yuan X.-J.,Chinese Academy of Aerospace Aerodynamics | Chen L.,Chinese Academy of Aerospace Aerodynamics
Jisuan Lixue Xuebao/Chinese Journal of Computational Mechanics | Year: 2015

A high order parallel algorithm was developed for the simulation of supersonic complex multi-scale flows. The fifth-order upwind compact scheme based on finite volume method was utilized, and the characteristic limiter was used to prevent non-physical oscillations across discontinuity. The fifth WENO schemes were used in adjoining boundaries to achieve consistent precision order in the whole computing domain. Using zone decomposition method and message communicating interfaces, parallel calculation is carried out on MPI platform. The capability of the algorithm is demonstrated by solving supersonic test cases, and the parallel efficiency and speedup are analyzed. Then the algorithm is used for the simulation of supersonic transition and turbulence. The computed results reveal that the developed algorithm has the properties of high-order accuracy and high resolution. Besides, the computed flow fields are continuous in adjoining boundary, and the parallel computing efficiency is acceptable. The algorithm achieves admirable effect in the numerical simulation of supersonic turbulence. © 2015, Editorial Office of Chinese Journal of Computational Mechanics. All right reserved.


Zhang S.,CAS Institute of Mechanics | Yu X.,CAS Institute of Mechanics | Li F.,CAS Institute of Mechanics | Kang G.,Chinese Academy of Aerospace Aerodynamics | And 2 more authors.
Optics and Lasers in Engineering | Year: 2012

The quantitative local equivalence ratio measurements of premixed kerosene/air gas at elevated pressure by the laser induced breakdown spectroscopy (LIBS) technique were preformed in a high temperature test cell, which was designed and manufactured for simulated supersonic combustion state. According to in-situ experimental conditions in supersonic combustion, the correlations between the values of emission intensity ratio of H/O, H/N and the equivalence ratio of premixed kerosene/air mixture in different gas pressures was established. The dependence of the FWHM of H α on pressure of the mixture was also measured. Therefore, the laser diagnostic method for quantitative local equivalence ratio measurements of kerosene/air mixture by the LIBS technique in supersonic combustion was developed in laboratory. The fundamental data was prepared for on-line quantitative local equivalence ratio measurements of kerosene/air mixture in supersonic combustion experiments. © 2012 Elsevier Ltd. All rights reserved.


Hu X.Y.,TU Munich | Wang Q.,TU Munich | Wang Q.,Chinese Academy of Aerospace Aerodynamics | Adams N.A.,TU Munich
Journal of Computational Physics | Year: 2010

In this work, an adaptive central-upwind 6th-order weighted essentially non-oscillatory (WENO) scheme is developed. The scheme adapts between central and upwind schemes smoothly by a new weighting relation based on blending the smoothness indicators of the optimal higher order stencil and the lower order upwind stencils. The scheme achieves 6th-order accuracy in smooth regions of the solution by introducing a new reference smoothness indicator. A number of numerical examples suggest that the present scheme, while preserving the good shock-capturing properties of the classical WENO schemes, achieves very small numerical dissipation. © 2010 Elsevier Inc.


Ma Y.,Chinese Academy of Aerospace Aerodynamics | Liu X.-W.,Chinese Academy of Aerospace Aerodynamics | Ou P.,Chinese Academy of Aerospace Aerodynamics
Proceedings - 2015 7th International Conference on Intelligent Human-Machine Systems and Cybernetics, IHMSC 2015 | Year: 2015

Underwater glider is a new type of autonomous underwater vehicle driven by gravity. In order to study the relationship between the motion parameters and control variable of the underwater glider, solve the fluctuation problem of pitching angle and attack angle in the process of attitude changing, simulation via the software Mat lab is performed based on the kinematic equations of underwater glider in vertical plane. The results show that the longer the cycle of bary center adjusting, the smaller the fluctuating extent of the pitching angle. It seems that this fluctuation of underwater glider is not affected by the variation of buoyancy adjusting, and the fluctuation of attack angle may be affected by the time center location difference between these two adjusting cycles. © 2015 IEEE.


Liu X.,Chinese Academy of Aerospace Aerodynamics | Ma Y.,Chinese Academy of Aerospace Aerodynamics | Ou P.,Chinese Academy of Aerospace Aerodynamics
2015 IEEE 12th International Conference on Electronic Measurement and Instruments, ICEMI 2015 | Year: 2016

Underwater glider, as a combination product of buoy technology and underwater vehicle, has broad application prospect in marine scientific research, environmental monitoring, resource exploration and military reconnaissance etc, because of the advantages of low-noise, long range, long duration and cost-efficiency. The conceptual design, body construction design based on modularization integrative 2-DOF attitude adjustment mechanism design and buoyancy adjustment system design based on accurate measurement are introduced. Then the design of the low power control system for underwater glider is described in detail. © 2015 IEEE.


Pan H.,Chinese Academy of Aerospace Aerodynamics | Ma H.,Chinese Academy of Aerospace Aerodynamics | Shen Q.,Chinese Academy of Aerospace Aerodynamics
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | Year: 2011

With an aim to realize hypersonic inlet turbulent separation control, a study is made of the inlet shock wave/turbulent boundary layer interaction (SWTBLI). As a sample, a plane flat shock wave reflection flow is simulated by large eddy simulation (LES). Shock wave effect mechanism in Mach number 3.0 conditions is analyzed. In the process of unsteady LES, disturbances that are obtained by direct numerical simulation (DNS) are imposed on the initial laminar boundary layer circularly to achieve full turbulent boundary quickly. When full turbulent boundary is realized, an oblique shock wave is imposed on it to form the SWTBLI. The numerical results indicate that LES can simulate planar SWTBLI well. The separation extent of the shock wave interaction zone is consistent with the experiment data. Owing to the effect of shock wave compression, the thickness and strength of the boundary layer are reduced near the reflecting shock wave.


Pan H.,Chinese Academy of Aerospace Aerodynamics | Li J.,Chinese Academy of Aerospace Aerodynamics | Zhang X.,Chinese Academy of Aerospace Aerodynamics
Jisuan Wuli/Chinese Journal of Computational Physics | Year: 2013

In hypersonic/supersonic flow conditions, numerical simulations, experience relations and experiment analysis are made to study thermal-environment distribution characteristic around local-parts imposed by protuberance interacting body. Comparing flow characteristic structures in different shape, height, breadth etc, we found that interaction-zone size induced by high protuberance depend sensitively on effective breadth and short protuberance interaction-zone size depend on protuberance height. On the other hand, interaction-zone size is imposed by shade of lead edge, whether laminar or turbulence. Square-lead-surface and arc lead surface separation length ratio is 1 414. Sweepback affects separation length. A correlative line is built for size of separation imposed by sweepback.


Tian J.-W.,Chinese Academy of Aerospace Aerodynamics | Yuan X.-J.,Chinese Academy of Aerospace Aerodynamics
Jisuan Lixue Xuebao/Chinese Journal of Computational Mechanics | Year: 2015

The 3rd order accurate Runge-Kutta discontinuous Galerkin (RKDG) method is developed to simulate three dimensional complex flows, such as three dimensional forward step problem, three dimensional Riemann problem and ball Riemann problem. Numerical results show that RKDG method can capture shocks and contact discontinuities in few grid points successfully. Furthermore, the pressure distribution of z=0.4 plane in ball Riemann problem agrees well with the result in the reference by refined grids. This suggested that the RKDG method developed in this paper is not only able to qualitatively describe three-dimensional complex flows, but also can be used in quantitative three-dimensional complex flow field calculations. ©, 2015, Editorial Office of Chinese Journal of Computational Mechanics. All right reserved.

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