Beijing Electromechanical Engineering Institute

Beijing, China

Beijing Electromechanical Engineering Institute

Beijing, China
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Qiao Y.,Hefei University | Chen H.B.,Hefei University | Luo J.L.,Beijing Electromechanical Engineering Institute
Journal of Vibroengineering | Year: 2013

The radiation efficiencies of cylindrical and conical shells were investigated by using the statistical modal energy distribution analysis (SmEdA) and integrated FEM-SmEdA approaches. In cylindrical shell, three analytical algorithms were carried out, including SmEdA and two conventional approaches, i.e. the wave approach and the statistical energy analysis (SEA), and the results were compared with a former experimental one. SmEdA showed closest results with the experimental one, owing to its precise estimation of the coupling loss factors (CLF) which were further used to calculate the radiation efficiency. Furthermore, based on the analytical SmEdA, an integrated FEM-SmEdA algorithm is proposed. This hybrid method provided similar shell radiation efficiency for cylindrical shell, indicating its applicability in the analysis of complicated structures. © VIBROENGINEERING.


Guo P.,China Academy of Launch Vehicle Technology | Liu J.,China Academy of Launch Vehicle Technology | Zhang M.,Beijing Electromechanical Engineering Institute | Yang H.Q.,China Academy of Launch Vehicle Technology
Proceedings of the International Astronautical Congress, IAC | Year: 2014

Hypersonic Reusable Space Vehicle (HRSV) is a kind of reusable space vehicle which can quickly access to the space, maneuver in-orbit, reenter the atmosphere and finally land on the earth ground. Because HRSV has to quickly access to the space and return, its dynamic environment is quite different from the one of traditional launch vehicle, manned spacecraft and recoverable satellite. The internal pressure design should be considered for the safety of vehicle structure. Combining the CFD and quasi one dimensional isentropic flow design methods, the effects of passive gas inflation/deflation system on the internal pressure and pressure loading are studied. The results reveal that the maximum peak value of flight pressure loading induced by the internal and external pressure will appear when the flight height and speed violently change, and the space vehicle structure should be further designed according to the internal pressure and pressure loading results. Copyright © 2014 by the International Astronautical Federation. All rights reserved.


Li Q.,Yantai Naval Aeronautical and Astronautical University | Li Q.,Beijing Electromechanical Engineering Institute | Qu G.,Beijing Electromechanical Engineering Institute | Li Z.,Beijing Electromechanical Engineering Institute
IET Conference Publications | Year: 2013

Because of the particularity of matching optical image to synthetic aperture radar image, this paper proposes an image matching algorithm for matching optical image to SAR image. This algorithm is based on Histograms of Oriented Gradient(HOG) descriptors. Firstly, we do the image preprocessing to extract prominent features. Secondly, we use the HOG descriptors as the feature space of the image matching and choose normalization cross correlation(NCC) as the measure standard of the feature matching. The experimental results show that the algorithm not only increases the probability of matching after using the effective gradient operator and feature dimensions, but also has robustness to different image regions.


Jing L.,Beijing Electromechanical Engineering Institute | Jing L.,Beijing Institute of Technology | Chang X.,Beijing Institute of Technology | Shao-Ning Z.,Beijing Electromechanical Engineering Institute | Shao-Ning Z.,Beijing Institute of Technology
Communications in Computer and Information Science | Year: 2016

Low-Level wind shear is one kind of atmospheric disturbance which can bring the most serious damages for aircraft. This paper presents the physical characteristics, temporal and spatial scale, and air flow of the micro-downburst which is the most dangerous wind shear. Combined with characteristics of the flight environment and mission course, simplified fluid dynamic model of the micro-downburst was built by setting different intensity vortex pairs at a certain height, to simulate the flight control process when the aircraft encounters the micro-downburst during gliding and examine its dynamic performance. Thus it provides a reliable method for control design of aircraft which flying at the adverse atmospheric disturbances. © Springer Science+Business Media Singapore 2016.


Zhang B.,Nanjing University of Aeronautics and Astronautics | Chen H.,Nanjing University of Aeronautics and Astronautics | He X.,Nanjing University of Aeronautics and Astronautics | Chen Y.,Beijing Electromechanical Engineering Institute | And 2 more authors.
Nanjing Hangkong Hangtian Daxue Xuebao/Journal of Nanjing University of Aeronautics and Astronautics | Year: 2012

A vibration experimental system of a cylindric aluminium beam with magneto-rheological(MR) dampers is established. The influence of the MR damper on the structure vibration behaviour is studied, and the vibration reduction is researched. The frequency response functions of the beam with and without the MR dampers under different control voltage are compared. The beam is excited by sine signals and a random signal respectively and the responses are measured with the MR dampers working in different conditions. The research result shows that the MR damper changes the vibration characteristic of the beam only in a narrow frequency domain, and the vibration reduction performance of the MR damper is significant in the low frequency domain but not so effective in the high frequency domain.


Zhang Q.,Beijing Electromechanical Engineering Institute | Ran J.,Beijing Electromechanical Engineering Institute | Hou Y.,Beijing Electromechanical Engineering Institute
Xitong Fangzhen Xuebao / Journal of System Simulation | Year: 2015

UAV is widely applied to a variety of areas, for the huge advantages of remote controlling flight trajectory, iterant recovery and flexible mission payloads flight. The routine design methods for aerocraft control system cannot supply desire of UAV high accuracy flying and replying diversified compositive disturb. System composition and departmental function of UAV flight control system were introduced. An online interaction simulation method of UAV flight control system was advanced. The principle and principle of online interaction simulation were analyzed. The key techniques of constituting fiducial simulation model, real time updating and revising simulation model, on-line detecting a mass of data, were researched which needed resolving by online interaction simulation method. Distinguishing exception and auto-warning for UAV flight were achieved, providing technique support to achieve assistant decision-making and intelligent control function of UAV. ©, 2015, Chinese Association for System Simulation. All right reserved.


Li J.,Beijing Electromechanical Engineering Institute | Zhang S.,Beijing Electromechanical Engineering Institute | Han J.,Beijing Electromechanical Engineering Institute
Communications in Computer and Information Science | Year: 2012

The natural environment affects and restricts the performance of high tech vehicle and platform. Research shows that modeling and simulation technology of natural environment influence on the design, development and application of modern vehicle all round. The environmental effect on vehicle is analyzed, and the research scheme and the key technology breakthrough in the process of study are introduced. The simulation result indicates that this kind of research method has advanced in technology. © 2012 Springer-Verlag.


Wang J.,Hefei University of Technology | Wang J.,Army Officer Academy of PLA | Chen H.-B.,Hefei University of Technology | Wang J.,Beijing Electromechanical Engineering Institute
Zhendong yu Chongji/Journal of Vibration and Shock | Year: 2013

A new impulsive load identification method in time domain was proposed. With this method, the dynamic loads were assumed to be linear functions within a time-step and the precise time-integration method was used. In this new algorithm, a precise load identification model was constructed, it was not based on a recursion-chain computational format, it was not sensitive to initial values and it had no error cumulation. Furthermore, the TSVD regularization technique was used to overcome the influences of ill-conditioned matrix and measuring noise. Numerical examples showed the effectiveness of the proposed algorithm.


Diao G.,Beijing Electromechanical Engineering Institute | Ni H.,Beijing Electromechanical Engineering Institute | Qi Y.,Beijing Electromechanical Engineering Institute | Lu J.,Beijing Electromechanical Engineering Institute
Communications in Computer and Information Science | Year: 2016

A radio frequency (RF) simulation technique based on high frequency hybrid method is proposed for complex target. Firstly, the radar cross section (RCS) of the target is obtained by vector addition of facets scattering field and wedges scattering field that are calculated respectively by physical optics (PO) method and physical theory of diffraction (PTD). Then, scattering centers of the target are extracted based on multi scattering center theory, and the radar echo signal is simulated through radio frequency simulation system (RFSS). This technique could improve the fidelity of radar signal simulation and the confidence of RF simulation test. At last, simulation results validate the technique. © Springer Science+Business Media Singapore 2016.


Wang Y.,Dalian University | Bai F.,hiSoft | Wang J.,Beijing Electromechanical Engineering Institute
ICIC Express Letters, Part B: Applications | Year: 2010

The query algorithms for basic nearest neighbor in static environment and an index structure - Time-Parameterized R tree (TPR tree) are introduced in this paper. A concept named influence time is proposed here, which is used in nearest neighbor query algorithm for moving object. The minimum distance calculation in two dimensions and multiple dimensions is discussed. ICIC International © 2010.

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