摘要：Sept.22^(nd)-25^(th),2014,Suzhou,ChinaThe 11^(th)International Workshop on Piezoelectric Materials and Applications in Actuators&the 9^(th)Energy Harvesting Workshop(IWPMA&EHW2014)was held successfully at Suzhou Grand Metropark Hotel,China,during Sept.22^(nd)to Sept.25^(th),2014.Prof.Chunsheng Zhao from Nanjing University of Aeronautics and Astronautics(NUAA),Member of the Chinese Academy of Sciences,acted as the chairman of the conference.
摘要：As one of the earliest institutes exploiting unmanned aerial vehicles(UAVs)in China,the UAV Research Institute of NUAA begins to develop UAVs in 1958.Since 1968,the institute has been officially undertaking research activities for government projects.In 1979,the UAV Research laboratory was initially established,being the No.362 Institute of the Ministry of Aviation,then it was reconstructed and entitled the'UAV Research Institute'in 2000.Being one of the most important research and development bases of small and
摘要：Transactions of Nanjing University of Aeronautics and Astronautics(TNUAA)is a quarterly journal facing international academic community.Emphasizing prompt and effective dissemination of key data and new scientific insights,TNUAA offers prompt publication of new experimental and theoretical papers bearing on applications to all branches of aeronautics,astronautics and civil aviation.
摘要：Wavelet transform is used to analyze the scaling rule of temperature data (passive scalar) in Rayleigh Bénard convection flow from two aspects. By utilizing the method of extended self similarity (ESS), one can find the obtained scaling exponent agrees well with the one obtained from the temperature data in a experiment of wind tunnel. And then we propose a newly defined formula based on wavelet transform, and can determine the scaling exponent ξ(q) of temperature data. The obtained results demonstrate that we can correctly extract ξ(q) by using the method which is named as wavelet transform maximum modulus (WTMM).
摘要：Transactions of Nanjing University of Aeronautics and Astronautics(TNUAA)is a quarterly journal facing international academic community.Emphasizing prompt and effective dissemination of key data and new scientific insights,TNUAA offers prompt publication of new experimental and theoretical papers bearing on applications to all branches of aeronautics,astronautics and civil aviation.TNUAA is currently indexed by Ei Compendex(USA),Scopus(Holland),Mathematical Review(USA),
摘要：As an important part of the State Key Laboratory of Mechanics and Control of Mechanical Structures in Nanjing University of Aeronautics and Astronautics,the Structural Health Monitoring and Prognostics(SHM&P;)Research Group was the first and only team in China who initiated the SHM study for aerospace engineering in early 1990’s,and has held a leading position in this new and exciting field since then.Currently,SHM&P; Research Group is led by Dr.Yuan Shenfang,a Changjiang Chair Professor,the winner of both
摘要：An air source heat pump(ASHP)with refrigerant injection is proposed for the air conditioning system of electric vehicles(EVs),especially for efficient heating in cold winter,when there is no wasted heat of engines.The simulation model is built with the framework of two-phase fluid network,where the compressor is separated as two compressors and the economizer is treated as two heat exchangers in the injection path and the main refrigerant path.With the validated simulation model,the heating performance is analyzed,and the results show that the coefficient of performance(COP)of ASHP with refrigerant injection is higher than 1.4 and the discharge temperature is less than 100℃ when the outdoor temperature is-20℃.The above performance ensures that the air conditioning system and EVs can operate normally with high efficiency even in the cold winter,which is much helpful for the practicability of EVs.
摘要：A non-resonant piezoelectric linear motor with a flexible driving end,which has an extensive working frequency range and good operation stability,is studied theoretically and experimentally.Based on the microscopic vibration characteristics of the motor stator,the longitudinal vibration model is established for the whole motor system.According to the Coulomb friction model and the motor vibration model,the friction mechanism of the nonresonant piezoelectric linear motor is investigated by dynamical analysis of the whole motor system.Furthermore,the vibration characteristics and mechanical output characteristics of the stator are simulated and experimentally studied on the basis of the friction drive mechanism model.Finally,both the simulation and experimental results show that this kind of motor remain stable in the frequency domain from 2.2 kHz to 3.5 kHz and that when the pre-stress is 4 Nand the driving voltage is 90 V,the maximum velocity of the motor is above 4 mm/s and the maximum thrust is nearly 0.5 N.
摘要：The dynamic response performance of a large,cylindrical,fluid-filled steel container under high-speed impact is evaluated through fluid-structure interaction analysis using arbitrary Lagrange-Eulerian(ALE)method.The ALE method is adopted to accurately calculate the structural behavior induced by the internal liquid impact of the container.The stress and strain results obtained from the finite element analysis are in line with the experimental shell impact data.The influences of drop angle,drop height,and flow impact frequency are discussed.Calculation results indicate that the impact stress and damage of the container increase with drop height.However,the amplitude of the oscillation and the impact stress increase when the container and flow impact resonance occur at a certain drop height.The impact stress shows a nonlinear relationship with drop angle.
摘要：Under the condition of thermal anti-icing,the liquid water on the leading edge of the airfoil that would flow to the downstream non-protective zone will produce ridge ice,thus endangering flight safety.Based on the existing three-dimensional(3 D)icing model which considers the water film flow on the ice layer,an icing model with thermal boundary condition is introduced.With the boundary conditions of none anti-icing and thermal anti-icing,glaze ice accretion and ridge ice accretion are simulated on a simplified airfoil of unmanned aerial vehicle(UAV),and then the lift coefficient and drag coefficient are calculated and compared with the smooth airfoil under the same conditions.The results show that the lift-drag ratio obviously decreases after glaze ice occurred on the leading edge under the condition of none anti-icing;and that after setting the condition of anti-icing heat flux in the impingement area,the glaze ice on the leading edge becomes thinner and the ridge ice occurs in the non-protective zone,so the airfoil with this icing characteristic gets a lower lift-drag ratio.
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