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| 1 | CFD calculations on the unsteady aerodynamic characteristics of a tilt-rotor in a conversion mode显示文摘In order to calculate the unsteady aerodynamic characteristics of a tilt-rotor in a conversion mode, a virtual blade model(VBM) and an real blade model(RBM) are established respectively. A new multi-layer moving-embedded grid technique is proposed to reduce the numerical dissipation of the tilt-rotor wake in a conversion mode. In this method, a grid system generated abound the rotor accounts for rigid blade motions, and a new searching scheme named adaptive inverse map(AIM) is established to search corresponding donor elements in the present movingembedded grid system to translate information among the different computational zones. A dual-time method is employed to fulfill unsteady calculations on the flowfield of the tilt-rotor,and a second-order centered difference scheme considering artificial viscosity is used to calculate the flux. In order to improve the computing efficiency, the single program multiple data(SPMD)model parallel acceleration technology is adopted, according to the characteristic of the current grid system. The lift and drag coefficients of an NACA0012 airfoil, the dynamic pressure distributions below a typical rotor plane, and the sectional pressure distributions on a three-bladed Branum–Tung tilt-rotor in hover flight are calculated respectively, and the present VBM and RBM are validated by comparing the calculated results with available experimental data. Then, unsteady aerodynamic forces and flowfields of an XV-15 tilt-rotor in different modes, such as a fixed conversion mode at different tilt angles(15°, 30°, 60°) and a whole conversion mode which converses from 0° to90°, are numerically simulated by the VBM and RBM respectively. By analyses and comparisons on the simulated results of unsteady aerodynamic forces of the tilt-rotor in different modes, some meaningful conclusions about distorted blade-tip vortex distribution and unsteady aerodynamic force variation in a conversion mode are obtained, and these investigation results could provide a good foundation for tilt-rotor aircraft design in the future. | Li Peng Zhao Qijun Zhu Qiuxian | 2015 | Chinese Journal of Aeronautics2015，28，6： | 15 |
| 2 | Experimental investigations for parametric effects of dual synthetic jets on delaying stall of a thick airfoil显示文摘A promising strategy of synthetic jet arrays(SJA) control for NACA0021 airfoil in preventing flow separation and delaying stall is investigated. Through aerodynamic forces, flowfield and velocity profiles measurements, it indicates that the synthetic jet(SJ) could enlarge the mixing of the shear layer and then enhance the stability of boundary layer, resulting in scope reduction of the flow separation zone. Furthermore, the control effects of dual jet arrays positioned at 15%c(Actuator 1) and 40%c(Actuator 2) respectively are systematically investigated with different jet parameters, such as two typical relative phase angles and various incline angles of the jet. The jet closer to the leading edge of airfoil is more advantageous in delaying the stall of airfoil, and overall,the flow control performances of jet arrays are better than those of single actuator. At the angle of attack(Ao A) just approaching and larger than the stall Ao A, jet array with 180° phase difference could increase the lift coefficient more significantly and prevent flow separation. When momentum coefficient of the jet arrays is small, a larger jet angle of Actuator 2 is more effective in improving the maximum lift coefficient of airfoil. With a larger momentum coefficient of jet array, a smaller jet angle of Actuator 2 is more effective. | Zhao Guoqing Zhao Qijun Gu Yunsong Chen Xi | 2016 | Chinese Journal of Aeronautics2016，29，2： | 14 |
| 3 | Integrated optimization analyses of aerodynamic/stealth characteristics of helicopter rotor based on surrogate model显示文摘Based on computational fluid dynamics(CFD)method,electromagnetic high-frequency method and surrogate model optimization techniques,an integration design method about aerodynamic/stealth has been established for helicopter rotor.The developed integration design method is composed of three modules:integrated grids generation(the moving-embedded grids for CFD solver and the blade grids for radar cross section(RCS)solver are generated by solving Poisson equations and folding approach),aerodynamic/stealth solver(the aerodynamic characteristics are simulated by CFD method based upon Navier–Stokes equations and Spalart–Allmaras(S–A)turbulence model),and the stealth characteristics are calculated by using a panel edge method combining the method of physical optics(PO),equivalent currents(MEC)and quasi-stationary(MQS),and integrated optimization analysis(based upon the surrogate model optimization technique with full factorial design(FFD)and radial basis function(RBF)),an integrated optimization analyses on aerodynamic/stealth characteristics of rotor are conducted.Firstly,the scattering characteristics of the rotor with different blade-tip swept and twist angles have been carried out,then time–frequency domain grayscale with strong scattering regions of rotor have been given.Meanwhile,the effects of swept-tip and twist angles on the aerodynamic characteristic of rotor have been performed.Furthermore,by choosing suitable object function and constraint condition,the compromised design about swept and twist combinations of rotor with high aerodynamic performances and low scattering characteristics has been given at last. | Jiang Xiangwen Zhao Qijun Zhao Guoqing Li Peng | 2015 | Chinese Journal of Aeronautics2015，28，3： | 12 |
| 4 | Dihydroartemisinin regulates the immune system by promotion of CD8^+T lymphocytes and suppression of B cell responses显示文摘Artemisia annua is an anti-fever herbal medicine first described in traditional Chinese medicine 1,000 years ago.Artemisinin,the extract of A.annua,and its derivatives(dihydroartemisinin(DHA),artemether,and artesunate)have been used for the treatment of malaria with substantial efficacy.Recently,DHA has also been tested for the treatment of lupus erythematosus,indicating that it may function to balance the immune response in immunocompromised individuals.In the present study,the regulatory effect of artemisinin on the murine immune system was systematically investigated in mice infected with two different protozoan parasites(Toxoplasma gondii and Plasmodium berghei).Our results revealed that the mouse spleen index significantly increased(spleen enlargement)in the healthy mice after DHA administration primarily due to the generation of an extra number of lymphocytes and CD8^+T lymphocytes in both the spleen and circulation.DHA could increase the proportion of T helper cells and CD8^+T cells,as well as decrease the number of splenic and circulatory B cells.Further,DHA could reduce the production of proinflammatory cytokines.Our study revealed that apart from their anti-parasitic activity,artemisinin and its derivatives can also actively modulate the immune system to directly benefit the host. | Ting Zhang Yiwei Zhang Ning Jiang Xu Zhao Xiaoyu Sang Na Yang Ying Feng Ran Chen Qijun Chen | 2020 | Science China(Life Sciences)2020，63，5： | 12 |
| 5 | Parametric analyses on dynamic stall control of rotor airfoil via synthetic jet显示文摘The effects of synthetic jet control on unsteady dynamic stall over rotor airfoil are investigated numerically. A moving-embedded grid method and an Unsteady Reynolds Averaged Navier-Stokes(URANS) solver coupled with k-x Shear Stress Transport(SST) turbulence model are established for predicting the complex flowfields of oscillatory airfoil under jet control. Additionally, a velocity boundary condition modeled by sinusoidal function has been developed to fulfill the perturbation effect of periodic jet. The validity of present CFD method is evaluated by comparisons of the calculated results of baseline dynamic stall case for rotor airfoil and jet control case for VR-7 B airfoil with experimental data. Then, parametric analyses are conducted emphatically for an OA212 rotor airfoil to investigate the effects of jet control parameters(jet location, dimensionless frequency, momentum coefficient, jet angle, jet type and dual-jet) on dynamic stall characteristics of rotor airfoil. It is demonstrated by the calculated results that efficiency of jet control could be improved with specific momentum coefficient and jet angle when the jet is located near separation point of rotor airfoil. Furthermore, the dual-jet could improve control efficiency more obviously on dynamic stall of rotor airfoil with respect to the unique jet, and the influence laws of dual-jet's angles and momentum coefficients on control effects are similar to those of the unique jet. Finally,unsteady aerodynamic characteristics of rotor via synthetic jet which is located on the upper surface of rotor blade in forward flight are calculated, and as a result, the aerodynamic characteristics of rotor are improved compared with the baseline. The results indicate that synthetic jet has the capability in improving aerodynamic characteristics of rotor. | Qijun ZHAO Yiyang MA Guoqing ZHAO | 2017 | Chinese Journal of Aeronautics2017，30，6： | 10 |
| 6 | Parametric analyses for synthetic jet control on separation and stall over rotor airfoil显示文摘Numerical simulations are performed to investigate the effects of synthetic jet control on separation and stall over rotor airfoils. The preconditioned and unsteady Reynolds-averaged Navier–Stokes equations coupled with a k x shear stream transport turbulence model are employed to accomplish the flowfield simulation of rotor airfoils under jet control. Additionally,a velocity boundary condition modeled by a sinusoidal function is developed to fulfill the perturbation effect of periodic jets. The validity of the present CFD procedure is evaluated by the simulated results of an isolated synthetic jet and the jet control case for airfoil NACA0015. Then, parametric analyses are conducted specifically for an OA213 rotor airfoil to investigate the effects of jet parameters(forcing frequency, jet location and momentum coefficient, jet direction, and distribution of jet arrays) on the control effect of the aerodynamic characteristics of a rotor airfoil. Preliminary results indicate that the efficiency of jet control can be improved with specific frequencies(the best lift-drag ratio at F+= 2.0) and jet angles(40 or 75) when the jets are located near the separation point of the rotor airfoil. Furthermore, as a result of a suitable combination of jet arrays, the lift coefficient of the airfoil can be improved by nearly 100%, and the corresponding drag coefficient decreased by26.5% in comparison with the single point control case. | Zhao Guoqing Zhao Qijun | 2014 | Chinese Journal of Aeronautics2014，27，5： | 10 |
| 7 | A New Single-blade Based Hybrid CFD Method for Hovering and Forward-flight Rotor Computation显示文摘A hybrid Euler/full potential/Lagrangian wake method,based on single-blade simulation,for predicting unsteady aerodynamic flow around helicopter rotors in hover and forward flight has been developed.In this method,an Euler solver is used to model the near wake evolution and transonic flow phenomena in the vicinity of the blade,and a full potential equation(FPE) is used to model the isentropic potential flow region far away from the rotor,while the wake effects of other blades and the far wake are incorporated into the flow solution as an induced inflow distribution using a Lagrangian based wake analysis.To further reduce the execution time,the computational fluid dynamics(CFD) solution and rotor wake analysis(including induced velocity up-date) are conducted parallelly,and a load balancing strategy is employed to account for the information exchange between two solvers.By the developed method,several hover and forward-flight cases on Caradonna-Tung and Helishape 7A rotors are per-formed.Good agreements of the loadings on blade surface with available measured data demonstrate the validation of the method.Also,the CPU time required for different computation runs is compared in the paper,and the results show that the pre-sent hybrid method is superior to conventional CFD method in time cost,and will be more efficient with the number of blades increasing. | SHI Yongjie ZHAO Qijun FAN Feng XU Guohua | 2011 | Chinese Journal of Aeronautics2011，24，2： | 9 |
| 8 | Robust Navier-Stokes method for predicting unsteady flowfield and aerodynamic characteristics of helicopter rotor显示文摘A robust unsteady rotor flowfield solver CLORNS code is established to predict the complex unsteady aerodynamic characteristics of rotor flowfield. In order to handle the difficult problem about grid generation around rotor with complex aerodynamic shape in this CFD code,a parameterized grid generated method is established, and the moving-embedded grids are constructed by several proposed universal methods. In this work, the unsteady Reynolds-Averaged Navier-Stokes(RANS) equations with Spalart-Allmaras are selected as the governing equations to predict the unsteady flowfield of helicopter rotor. The discretization of convective fluxes is accomplished by employing the second-order central difference scheme, third-order MUSCL-Roe scheme, and fifth-order WENO-Roe scheme. Aimed at simulating the unsteady aerodynamic characteristics of helicopter rotor, the dual-time scheme with implicit LU-SGS scheme is employed to accomplish the temporal discretization. In order to improve the computational efficiency of holecells and donor elements searching of the moving-embedded grid technology, the ‘‘disturbance diffraction method' and ‘‘minimum distance scheme of donor elements method' are established in this work. To improve the computational efficiency, Message Passing Interface(MPI) parallel method based on subdivision of grid, local preconditioning method and Full Approximation Storage(FAS) multi-grid method are combined in this code. By comparison of the numerical results simulated by CLORNS code with test data, it is illustrated that the present code could simulate the aerodynamic loads and aerodynamic noise characteristics of helicopter rotor accurately. | Qijun ZHAO Guoqing ZHAO Bo WANG Qing WANG Yongjie SHI Guohua XU | 2018 | Chinese Journal of Aeronautics2018，31，2： | 9 |
| 9 | Aerodynamic shape optimization for alleviating dynamic stall characteristics of helicopter rotor airfoil显示文摘In order to alleviate the dynamic stall effects in helicopter rotor, the sequential quadratic programming(SQP) method is employed to optimize the characteristics of airfoil under dynamic stall conditions based on the SC1095 airfoil. The geometry of airfoil is parameterized by the class-shape-transformation(CST) method, and the C-topology body-fitted mesh is then automatically generated around the airfoil by solving the Poisson equations. Based on the grid generation technology, the unsteady Reynolds-averaged Navier-Stokes(RANS) equations are chosen as the governing equations for predicting airfoil flow field and the highly-efficient implicit scheme of lower–upper symmetric Gauss–Seidel(LU-SGS) is adopted for temporal discretization. To capture the dynamic stall phenomenon of the rotor more accurately, the Spalart–Allmaras turbulence model is employed to close the RANS equations. The optimized airfoil with a larger leading edge radius and camber is obtained. The leading edge vortex and trailing edge separation of the optimized airfoil under unsteady conditions are obviously weakened, and the dynamic stall characteristics of optimized airfoil at different Mach numbers, reduced frequencies and angles of attack are also obviously improved compared with the baseline SC1095 airfoil. It is demonstrated that the optimized method is effective and the optimized airfoil is suitable as the helicopter rotor airfoil. | Wang Qing Zhao Qijun Wu Qi | 2015 | Chinese Journal of Aeronautics2015，28，2： | 8 |
| 10 | Numerical analysis on noise of rotor with unconventional blade tips based on CFD/Kirchhoff method显示文摘A solver is developed aiming at efficiently predicting rotor noise in hover and forward flight. In this solver, the nonlinear near-field solutions are calculated by a hybrid approach which includes the Navier-Stokes and Euler equations based on a moving-embedded grid system and adaptive grid methodology. A combination of the third-order upwind scheme and flux-difference splitting scheme, instead of the second-order center-difference scheme which may cause larger wake dissipation, has been employed in the present computational fluid dynamics (CFD) method. The sound pressure data in the near field can be calculated directly by solving the Navier-Stokes equations, and the sound propagation can be predicted by the Kirchhoff method. A harmonic expansion approach is presented for rotor far-field noise prediction, which gives an analytical expression for the integral function in the Kirchhoff formula. As a result, the interpolation process is simplified and the efficiency and accuracy of the interpolation are improved. Then, the high-speed impulsive (HIS) noise of a helicopter rotor at different tip Mach numbers and on different observers is calculated and analyzed in hover and forward flight, which shows a highly directional characteristic of the rotor HIS noise with a maximum value in the rotor plane, and the HSI noise weakens rapidly with the increasing of the directivity angle. In order to investigate the effects of the rotor blade-tip shape on its aeroacoustic characteristics, four kinds of blade tips are designed and their noise characteristics have been simulated. At last, a new unconventional CLOR-II blade tip has been designed, and the noise characteristics of the presented CLOR-II model rotor have been simulated and measured compared to the reference rotors with a rectangular or swept-back platform blade tip. The results demonstrate that the unconventional CLOR-II blade tip can significantly reduce the HSI noise of a rotor. | Wang Bo Zhao Qijun Xu Guohua Ye Liang Wang Junyi | 2013 | Chinese Journal of Aeronautics2013，26，3： | 8 |
| 11 | Experiments on unsteady vortex flowfield of typical rotor airfoils under dynamic stall conditions显示文摘A new experiment for airfoil dynamic stall is conducted by employing the advanced particle image velocimetry(PIV) technology in an open-return wind tunnel. The aim of this experimental investigation is to demonstrate the influences of different motion parameters on the convection velocity, position and strength of leading edge vortex(LEV) of airfoil under different dynamic stall conditions. Two different typical rotor airfoils, OA209 and SC1095, are measured at different free stream velocities, oscillation frequencies, and angles of attack. It is demonstrated by the measured data that the airfoil with larger leading edge radius could notably decrease the strength of LEV. The angle of attack(Ao A) of airfoil can obviously influence the dynamic stall characteristics of airfoil,and the LEV would be effectively inhibited by decreasing the mean pitch angle. In addition, the convection velocity of LEV is estimated in this measurement, and the results demonstrate that the influence of airfoil shape on convection velocity of LEV is limited, but the convection velocity of LEV would be increased by enlarging the oscillation frequency. Meanwhile, the convection velocity of LEV is a time variant value, and this value would increase as the LEV convects to the trailing edge of airfoil. | Wang Qing Zhao Qijun | 2016 | Chinese Journal of Aeronautics2016，29，2： | 4 |
| 12 | Optic and catalytic properties of gold nanoparticles tuned by homopolymers显示文摘Gold nanoparticles (GNs) are prepared through in situ reduction using NaBH4 in the presence of homopolymer PDMAEMA. The sizes of the GNs can be adjusted by alternating the molar ratio of gold to DMAEMA. Pure PDMAEMA aqueous solution shows a phase-transition at 50℃ at pH 10 and 25℃ at pH 14, while PDMAEMA-supported GNs aqueous solution shows a phase-transition at 47℃ at pH 10 because of the increasing hydrophobic property resulting from GNs. Due to the pH and tempera-ture-responsible characteristics of PDMAEMA, the resulting PDMAEMA-supported GNs exhibit pH adjustable temperature-responsive characteristics in optic and catalytic aspects. Under an acidic condi-tion (pH 2), the GNs show unchanged surface Plasmon absorbance with a peak of 518 nm in a tem-perature range from 20 to 65℃. Under a basic condition (pH 10), the GNs first show the same absorb-ance with a peak at 518 nm in a temperature range from 20 to 40℃, and then the absorbance red shifts from 518 to 545 nm as temperature increases from 40 to 65℃. When the GNs are used as catalysts to catalyze the reduction of p-nitrophenol, the catalytic activity can be adjusted by changing the permeation of reactants in the PDMAEMA layer at low and high temperatures, respectively. | CHEN Xi ZHAO DongYun ZHAO LiZhi AN YingLi MA RuJiang SHI LinQi HE QiJun CHEN Li | 2009 | Science China Chemistry2009，52，9： | 3 |
| 13 | An adaptive integration surface for predicting transonic rotor noise in hovering and forward flights显示文摘In this paper, a new permeable adaptive integration surface is developed in order to evaluate transonic rotor noise in accordance with FW-H_pds equations(Ffowcs Williams-Hawkings equations with penetrable data surface). Firstly, a nonlinear near-field solution is computed on the basis of Navier-Stokes equations, which is developed on moving-embedded grid methodology.The solution calculated through the present CFD method is used as the input for acoustic calculations by FW-H_pds equations. Then, two criteria for constructing integration surfaces are established based on the analysis of the quadrupole source strength and the nonlinear characteristic.A new surface is determined adaptively by the pressure gradient or density in a given flowfield,eschewing the uncertainties associated with determining cylinder-shaped integration surfaces. For varying hover cases, transonic noises are simulated with new integration surfaces for a UH-1 model rotor. Furthermore, numerical results of the new integration surface derived from the density perturbation value conform better to experimental data than results derived from the pressure gradient.Finally, the integration surface given by jrqj being 0.1, which is an applicable criterion obtained from hover cases, is used to predict transonic rotor noise in forward flight. The computational accuracy of the new integration surface method has been validated in predicting transonic rotor noise of an AH-1 model rotor at different advance ratios. | Siyu CHEN Qijun ZHAO Yiyang MA | 2019 | Chinese Journal of Aeronautics2019，32，9： | 2 |
| 14 | Surface decoration of Halloysite nanotubes with POSS for fire-safe thermoplastic polyurethane nanocomposites显示文摘Halloysite nanotubes(HNTs)have been considered as a promising flame retardant fillers for polymers.In this work,the polyhedral oligomericsilsesquioxane(POSS)containing amino group was covalently grafted on the surface of HNTs with 3-(2,3-epoxypropoxy)propytrimethoxysilane as a chemical bridge.The POSS modified HNTs(HNTs-POSS)dispersed uniformly in the thermoplastic polyurethane(TPU)matrix and endowed TPU nanocomposites with enhanced tensile properties and fire safety.Cone calorimeter tests revealed that the introduction of 2 wt%HNTs-POSS to TPU matrix remarkably reduced the peak of heat release rate(PHRR)and total heat release(THR)by 60.0%and 18.3%,respectively.In addition,the peak CO production rate and total smoke release(TSR)could be significantly suppressed by the addition of HNTsPOSS.The well dispersed HNTs in combination with the ceramified silicon network from the thermal decomposition of POSS contributed to the formation of a continuous and compact char layer,exhibiting a tortuous effect by inhibiting heat diffusion and evaporation of volatile gaseous.In addition,the released crystal water from HNTs could dilute the combustible volatiles and then decline the combustion intensity.The tensile tests demonstrated that introduction of 2 wt%HNTs-POSS would enhance the maximum stress of TPU nanocomposite with a slight decrease of elongation at break.The combination of HNTs and POSS through the construction of effective interfacial interactions provides a feasible way to effectively enhance the fire safety of TPU nanocomposites without scarifying ductility. | Wei Wu Wanjing Zhao Xianjing Gong Qijun Sun Xianwu Cao Yujun Su Bin Yu Robert K.Y.Li Roy A.L.Vellaisamy | 2022 | Journal of Materials Science & Technology2022，，6： | 2 |
| 15 | Numerical Optimization on Aerodynamic/Stealth Characteristics of Airfoil Based on CFD/CEM Coupling Method显示文摘Based on computational fluid dynamics(CFD)/computational electromagnetics method(CEM)coupling method and surrogate model optimization techniques,an integration design method about aerodynamic/stealth characteristics of airfoil is established.The O-type body-fitted and orthogonal grid around airfoil is first generated by using the Poisson equations,in which the points per wave and the normal range satisfy the aerodynamic and electromagnetic calculation accuracy requirement.Then the aerodynamic performance of airfoil is calculated by solving the Navier-Stokes(N-S)equations with Baldwin-Lomax(B-L)turbulence model.The stealth characteristics of airfoil are simulated by using finite volume time domain(FVTD)method based on the Maxwell′s equations,Steger-Warming flux splitting and the third-order MUSCL scheme.In addition,based upon the surrogate model optimization technique with full factorial design(FFD)and radial basis function(RBF),an integration design about aerodynamic/stealth characteristics of rotor airfoil is conducted by employing the CFD/CEM coupling method.The aerodynamic/stealth characteristics of NACA series airfoils with different maximum thickness and camber combinations are discussed.Finally,by choosing suitable lift-to-drag ratio and radar cross section(RCS)amplitudes of rotor airfoil in four important scattering regions as the objective function and constraint,the compromised airfoil with high lift-to-drag ratio and low scattering characteristics is designed via systemic and comprehensive analyses. | Jiang Xiangwen Zhao Qijun Zhao Guoqing Meng Chen | 2016 | Transactions of Nanjing University of Aeronautics and Astronautics2016，33，3： | 2 |
| 16 | Precise methods for conducted EMI modeling,analysis,and prediction显示文摘Focusing on the state-of-the-art conducted EMI prediction, this paper presents a noise source lumped circuit modeling and identification method, an EMI modeling method based on multiple slope approximation of switching transitions, and dou-ble Fourier integral method modeling PWM conversion units to achieve an accurate modeling of EMI noise source. Meanwhile, a new sensitivity analysis method, a general coupling model for steel ground loops, and a partial element equivalent circuit method are proposed to identify and characterize conducted EMI coupling paths. The EMI noise and propagation modeling provide an accurate prediction of conducted EMI in the entire frequency range (0―10 MHz) with good practicability and generality. Finally a new measurement approach is presented to identify the surface current of large dimensional metal shell. The proposed analytical modeling methodology is verified by experimental results. | MA WeiMing ZHAO ZhiHua MENG Jin PAN QiJun ZHANG Lei | 2008 | Science China(Technological Sciences)2008，51，6： | 2 |
| 17 | Ultra-strong phosphorescence with 48% quantum yield from grinding treated thermal annealed carbon dots and boric acid composite显示文摘Metal-free room-temperature phosphorescence(RTP)materials are of great significance for many applications;however,they usually exhibit low efficiency and weak intensity.This article reports a new strategy for the preparation of a high-efficiency and strong RTP materials from crystalline thermal-annealed carbon dots(CDs)and boric acid(BA)composite(g-t-CD@BA)through grinding-induced amorphous to crystallization transition.Amorphous thermal-annealed CDs and BA composite(t-CD@BA)is prepared following a thermal melting and super-cooling route,where the CDs are fully dispersed in molten BA liquid and uniformly frozen in an amorphous thermal annealed BA matrix after super-cooling to room temperature.Upon grinding treatment,the fracture and fragmentation caused by grinding promote the transformation of the high-energy amorphous state to the lower energy crystalline counterparts.As a result,the CDs are uniformly in situ embedded in the BA crystal matrix.This method affords maximum uniform embedding of the CDs in the BA crystals,decreases nonradiative decay,and promotes intersystem crossing by restraining the free vibration of the CDs,thus producing strong RTP materials with the highest reported phosphorescence quantum yield(48%).Remarkably,RTP from g-t-CD@BA powder is strong enough to illuminate items with a delay time exceeding 9 s. | Qijun Li Zhenxiao Zhao Shuai Meng Yuchen Li Yunyang Zhao Bohan Zhang Zikang Tang Jing Tan Songnan Qu | 2022 | SmartMat2022，3，2： | 2 |
| 18 | An analytical study of parametric e~fects on rotor-vortex interac- tion noise显示文摘 | Shi Yongjie Zhao Qijun Xu Guohua | 2011 | Proceedings of the Institution of Me- chanical Engineers Part G-Journal of Aerospace En- gineering2011，225，3： | 1 |
| 19 | Neuropeptide Y protects cerebral cortical neurons by regulating microglial immune function显示文摘Neuropeptide Y has been shown to inhibit the immunological activity of reactive microglia in the rat cerebral cortex, to reduce N-methyl-D-aspartate current(INMDA) in cortical neurons, and protect neurons. In this study, after primary cultured microglia from the cerebral cortex of rats were treated with lipopolysaccharide, interleukin-1β and tumor necrosis factor-α levels in the cell culture medium increased, and mRNA expression of these cytokines also increased. After primary cultured cortical neurons were incubated with the lipopolysaccharide-treated microglial conditioned medium, peak INMDA in neurons increased. These effects of lipopolysaccharide were suppressed by neuropeptide Y. After addition of the neuropeptide Y Y1 receptor antagonist BIBP3226, the effects of neuropeptide Y completely disappeared. These results suggest that neuropeptide Y prevents excessive production of interleukin-1β and tumor necrosis factor-α by inhibiting microglial reactivity. This reduces INMDA in rat cortical neurons, preventing excitotoxicity, thereby protecting neurons. | Qijun Li Changzheng Dong Wenling Li Wei Bu Jiang Wu Wenqing Zhao | 2014 | Neural Regeneration Research2014，9，9： | 1 |
| 20 | A haplotype map of genomic variations and genome-wide association studies of agronomic traits in foxtail millet(Setaria italica)显示文摘 | Guanqing Jia Xuehui Huang Hui Zhi Yan Zhao QiangZhao Wenjun Li Yang Chai Lifang Yang Kunyan Liu Hengyun Lu Chuanrang Zhu Yiqi Lu Congcong Zhou Danlin Fan Qijun Weng Yunli Guo Tao Huang LeiZhang Tingting Lu Qi Feng Hangfei Hao HongkuanLiu Ping Lu Ning Zhang Yuhui Li Erhu Guo ShujunWang Suying Wang Jinrong Liu Wenfei Zhang GuoqiuChen Baojin Zhang Wei Li Yongfang Wang HaiquanLi Baohua Zhao Jiayang Li Xianmin Diao Bin HanJia | 2013 | Nature Genetics2013，45，8： | 1 |
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