Aiming at the high angle of attack pull-up and multi-channel roll pull-up coupling problems of high maneuvering aircraft, this paper establishes the flight attitude control rate by means of unsteady flow numerical sol...Aiming at the high angle of attack pull-up and multi-channel roll pull-up coupling problems of high maneuvering aircraft, this paper establishes the flight attitude control rate by means of unsteady flow numerical solution, dynamic unstructured nested mesh assembly method and numerical solution method of flight mechanics equation. On this basis, a virtual flight simulation platform integrating pneumatics, motion and control is established. Based on this virtual flight simulation platform, F-16 aircraft is simulated by high angle of attack pull-up flight mode and multi-channel roll pull-up coupling flight mode. Finally, the influence of rudder on the yaw control channel is investigated. The results show that the numerical virtual flight simulation platform established in this paper has the ability to simulate maneuvering flight of aircraft.展开更多
An Arbitrary Lagrangian-Eulerian(ALE)approach with interface tracking is developed in this paper to simulate the supersonic parachute inflation.A two-way interaction between a nonlinear finite element method and a fin...An Arbitrary Lagrangian-Eulerian(ALE)approach with interface tracking is developed in this paper to simulate the supersonic parachute inflation.A two-way interaction between a nonlinear finite element method and a finite volume method is accomplished.In order to apply this interface tracking method to problems with instantaneous large deformation and self-contact,a new virtual structure contact method is proposed to leave room for the body-fitted mesh between the contact structural surfaces.In addition,the breakpoint due to the fluid mesh with negative volume is losslessly restarted by the conservative interpolation method.Based on this method,fluid and structural dynamic behaviors of a highly folded disk-gap-band parachute are obtained.Numerical results such as maximum Root Mean Square(RMS)drag,general canopy shape and the smallest canopy projected areas in the terminal descent state are in accordance with the wind tunnel test results.This analysis reveals the inflation law of the disk-gap-band parachute and provides a new numerical method for supersonic parachute design.展开更多
The effects of interface shape on stress wave distribution and attenuation were investiga- ted using finite element method （ FEM ）. The simulation results indicate that when the stress wave propagates from SiC ceram...The effects of interface shape on stress wave distribution and attenuation were investiga- ted using finite element method （ FEM ）. The simulation results indicate that when the stress wave propagates from SiC ceramic to A1 alloy, the tensile stress decreases and the attenuation coefficient of the stress wave increases with increasing central angle of the concave interface between SiC and A1. But for the convex interface, the tensile stress increases and attenuation coefficient decreases with increasing central angle. As the stress wave propagates from A1 alloy to SiC ceramic, the atten- uation coefficient of stress wave decreases with increasing the central angle of the concave interface. For the convex interface, the attenuation coefficient increases with increasing central angle.展开更多
研究质谱的离子传输气体动力学特征对理解和提升质谱仪器灵敏度具有重要意义。基于纳维-斯托克斯(NavierStokes)方程和直接蒙特卡洛(Direct Simulation Monte Carlo)方法联用,可以计算获得气体从大气压连续流到真空稀薄流的流场特征,进...研究质谱的离子传输气体动力学特征对理解和提升质谱仪器灵敏度具有重要意义。基于纳维-斯托克斯(NavierStokes)方程和直接蒙特卡洛(Direct Simulation Monte Carlo)方法联用,可以计算获得气体从大气压连续流到真空稀薄流的流场特征,进一步与电场仿真耦合,可以获得离子的传输与空间分布信息,评价离子光学器件性能。工作基于光电离质谱,构建了毛细管进样、光电离源和取样锥的组合结构模型,建立了离子传输跨流态多物理场仿真方法,得到了两种结构光电离源电极对离子传输效率的影响,并利用自制光电离飞行时间质谱装置验证了仿真方法的可靠性。工作为复杂流场和电场环境下质谱光电离源及离子传输装置设计提供了理论指导依据。展开更多
Temporal mode direct numerical simulation (DNS) has been done for a supersonic turbulent boundary layer on a flat plate with Mach number 4.5. It was found that the mean flow profile, the normal-wise distribution of tu...Temporal mode direct numerical simulation (DNS) has been done for a supersonic turbulent boundary layer on a flat plate with Mach number 4.5. It was found that the mean flow profile, the normal-wise distribution of turbulent Mach number and the root mean square (RMS) of the fluctuations of various variables, as well as the Reynolds stresses, bore similarity in nature, when the turbulence reached a fully developed state. But the compressibility effect was strong and must be considered. The strong Reynolds analogy (SRA) and the Morkovin hypothesis were no longer valid. From the end of transition to the fully developed state of turbulence, it was in the transient period, for which the similarity did not hold.展开更多
Fluorescence fluctuation spectroscopy (FFS) technique is capable of monitoring changes in concentration, mass, size and structure of fluorescent-labeled bio-molecules in microscopic volume and is suitable for measurin...Fluorescence fluctuation spectroscopy (FFS) technique is capable of monitoring changes in concentration, mass, size and structure of fluorescent-labeled bio-molecules in microscopic volume and is suitable for measuring biological interactions in living cells. FFS data may be affected by many experimental factors in complicated biological systems. Using a Monte Carlo approach, we generate fluorescence fluctuation data for different experimental systems. This approach helps to separate the contributions by different experimental factors in a complicated fluorescence fluctuation spectrum. It also helps to validate new theoretical models and new fitting formulations. We describe the algorithm of the simulation program and tests on its statistical performance. The program is then used successfully to study the effects of several experimental factors on FFS detection.展开更多
文摘Aiming at the high angle of attack pull-up and multi-channel roll pull-up coupling problems of high maneuvering aircraft, this paper establishes the flight attitude control rate by means of unsteady flow numerical solution, dynamic unstructured nested mesh assembly method and numerical solution method of flight mechanics equation. On this basis, a virtual flight simulation platform integrating pneumatics, motion and control is established. Based on this virtual flight simulation platform, F-16 aircraft is simulated by high angle of attack pull-up flight mode and multi-channel roll pull-up coupling flight mode. Finally, the influence of rudder on the yaw control channel is investigated. The results show that the numerical virtual flight simulation platform established in this paper has the ability to simulate maneuvering flight of aircraft.
基金co-supported by National Nature Sciences Foundation of China(Nos 11972192,11172137)A Project Funded by the Priority Academic Program Development of Jiangsu Higher Education Institutions(PAPD)。
文摘An Arbitrary Lagrangian-Eulerian(ALE)approach with interface tracking is developed in this paper to simulate the supersonic parachute inflation.A two-way interaction between a nonlinear finite element method and a finite volume method is accomplished.In order to apply this interface tracking method to problems with instantaneous large deformation and self-contact,a new virtual structure contact method is proposed to leave room for the body-fitted mesh between the contact structural surfaces.In addition,the breakpoint due to the fluid mesh with negative volume is losslessly restarted by the conservative interpolation method.Based on this method,fluid and structural dynamic behaviors of a highly folded disk-gap-band parachute are obtained.Numerical results such as maximum Root Mean Square(RMS)drag,general canopy shape and the smallest canopy projected areas in the terminal descent state are in accordance with the wind tunnel test results.This analysis reveals the inflation law of the disk-gap-band parachute and provides a new numerical method for supersonic parachute design.
基金Supported by the National Basic Research Program of China("973" Program)(613135)
文摘The effects of interface shape on stress wave distribution and attenuation were investiga- ted using finite element method （ FEM ）. The simulation results indicate that when the stress wave propagates from SiC ceramic to A1 alloy, the tensile stress decreases and the attenuation coefficient of the stress wave increases with increasing central angle of the concave interface between SiC and A1. But for the convex interface, the tensile stress increases and attenuation coefficient decreases with increasing central angle. As the stress wave propagates from A1 alloy to SiC ceramic, the atten- uation coefficient of stress wave decreases with increasing the central angle of the concave interface. For the convex interface, the attenuation coefficient increases with increasing central angle.
文摘研究质谱的离子传输气体动力学特征对理解和提升质谱仪器灵敏度具有重要意义。基于纳维-斯托克斯(NavierStokes)方程和直接蒙特卡洛(Direct Simulation Monte Carlo)方法联用,可以计算获得气体从大气压连续流到真空稀薄流的流场特征,进一步与电场仿真耦合,可以获得离子的传输与空间分布信息,评价离子光学器件性能。工作基于光电离质谱,构建了毛细管进样、光电离源和取样锥的组合结构模型,建立了离子传输跨流态多物理场仿真方法,得到了两种结构光电离源电极对离子传输效率的影响,并利用自制光电离飞行时间质谱装置验证了仿真方法的可靠性。工作为复杂流场和电场环境下质谱光电离源及离子传输装置设计提供了理论指导依据。
基金supported by the National Natural Science Foundation of China(Grant No.90205021)the Foundation for the Author of National Excellent Doctoral Dissertation of China(Grant No.200328)partially supported by Liu-Hui Center of Applied Mathematics,Nankai University and Tianjin University.
文摘Temporal mode direct numerical simulation (DNS) has been done for a supersonic turbulent boundary layer on a flat plate with Mach number 4.5. It was found that the mean flow profile, the normal-wise distribution of turbulent Mach number and the root mean square (RMS) of the fluctuations of various variables, as well as the Reynolds stresses, bore similarity in nature, when the turbulence reached a fully developed state. But the compressibility effect was strong and must be considered. The strong Reynolds analogy (SRA) and the Morkovin hypothesis were no longer valid. From the end of transition to the fully developed state of turbulence, it was in the transient period, for which the similarity did not hold.
基金supported by the National Natural Science Foundation of China(Grant Nos.19928408,60138010 and 10274039).
文摘Fluorescence fluctuation spectroscopy (FFS) technique is capable of monitoring changes in concentration, mass, size and structure of fluorescent-labeled bio-molecules in microscopic volume and is suitable for measuring biological interactions in living cells. FFS data may be affected by many experimental factors in complicated biological systems. Using a Monte Carlo approach, we generate fluorescence fluctuation data for different experimental systems. This approach helps to separate the contributions by different experimental factors in a complicated fluorescence fluctuation spectrum. It also helps to validate new theoretical models and new fitting formulations. We describe the algorithm of the simulation program and tests on its statistical performance. The program is then used successfully to study the effects of several experimental factors on FFS detection.
