由于跟踪过程目标不规则形变的影响,采用固定纵横比的尺度模型无法精确地估计目标的尺度.为解决该问题,本文提出基于纵横比自适应的相关滤波跟踪算法.基于fDSST(fast Discriminative Scale Space Tracking)算法,训练学习纵横比模型,更...由于跟踪过程目标不规则形变的影响,采用固定纵横比的尺度模型无法精确地估计目标的尺度.为解决该问题,本文提出基于纵横比自适应的相关滤波跟踪算法.基于fDSST(fast Discriminative Scale Space Tracking)算法,训练学习纵横比模型,更新目标的纵横比,获取更精确的目标尺度.在此基础上,本文设计了平滑修正方案以及学习率自适应机制,可以有效地缓解因目标出现遮挡导致的模型漂移问题.在OTB100、VOT2016和VOT2018数据集上与其他跟踪算法进行对比实验,结果表明本文算法改善了基准算法的性能,特别是在OTB100上的总体准确率和成功率比fDSST提高了9.6%和6.2%.展开更多
In the present study, the flow visualizations were performed around the NACA 0012 models which differ in aspect ratios. We discussed the effects of the aspect ratio in the test models. Additionally the unsteady, two-d...In the present study, the flow visualizations were performed around the NACA 0012 models which differ in aspect ratios. We discussed the effects of the aspect ratio in the test models. Additionally the unsteady, two-dimensional, compressible Euler equations were solved for the NACA 0012 airfoil. Experiments were performed utilizing the conventional gas driven shock tube as the intermittent transonic wind tunnel. The aspect ratios of the models are about 0.86 and 1.5, respectively. The Mach numbers M 2 are about 0.84. The Reynolds numbers of the present experimental conditions were constant that Re based on chord length is about 4.0×10 5 . The results are as follows: in different aspect ratios, the difference of the shock wave location is confirmed though the Mach number and Reynolds number are same. It indicates the different correction Mach number by the effects of the side wall boundary layer though the nominal Mach number measured the same value. Also, on the difference of shock wave location for the effects of the aspect ratio, the tend of CFD shows the qualitative agreement with the result of an experiment.展开更多
文摘由于跟踪过程目标不规则形变的影响,采用固定纵横比的尺度模型无法精确地估计目标的尺度.为解决该问题,本文提出基于纵横比自适应的相关滤波跟踪算法.基于fDSST(fast Discriminative Scale Space Tracking)算法,训练学习纵横比模型,更新目标的纵横比,获取更精确的目标尺度.在此基础上,本文设计了平滑修正方案以及学习率自适应机制,可以有效地缓解因目标出现遮挡导致的模型漂移问题.在OTB100、VOT2016和VOT2018数据集上与其他跟踪算法进行对比实验,结果表明本文算法改善了基准算法的性能,特别是在OTB100上的总体准确率和成功率比fDSST提高了9.6%和6.2%.
文摘In the present study, the flow visualizations were performed around the NACA 0012 models which differ in aspect ratios. We discussed the effects of the aspect ratio in the test models. Additionally the unsteady, two-dimensional, compressible Euler equations were solved for the NACA 0012 airfoil. Experiments were performed utilizing the conventional gas driven shock tube as the intermittent transonic wind tunnel. The aspect ratios of the models are about 0.86 and 1.5, respectively. The Mach numbers M 2 are about 0.84. The Reynolds numbers of the present experimental conditions were constant that Re based on chord length is about 4.0×10 5 . The results are as follows: in different aspect ratios, the difference of the shock wave location is confirmed though the Mach number and Reynolds number are same. It indicates the different correction Mach number by the effects of the side wall boundary layer though the nominal Mach number measured the same value. Also, on the difference of shock wave location for the effects of the aspect ratio, the tend of CFD shows the qualitative agreement with the result of an experiment.
