复杂大田场景下基于改进YOLOv8的小麦幼苗期叶片数快速检测方法

[目的/意义]小麦叶片数是衡量植株生长状况、确定茎蘖动态、调节群体结构的重要指标之一。目前大田环境下小麦叶片计数主要依靠人工、耗时耗力,而现有的自动化检测计数方法的效率与精度难以满足实际应用需求。为提高小麦叶片数检测的准确性,设计了一种复杂大田环境下高效识别小麦叶尖的算法。[方法]本研究以手机和田间摄像头获取的可见光图像构建了两种典型光照条件下出苗期、分蘖期、越冬期等多个生长期的小麦叶片图像数据集。以YOLOv8为基础网络,融合坐标注意力机制降低背景环境的干扰,提高模型对小麦叶尖轮廓信息的提取能力;替换损失函数加快模型收敛速度;增加小目标检测层提高对小麦叶尖的识别效果,降低漏检率。设计了一种适用于叶尖小目标识别的深度学习网络,通过检测图像叶尖数量从而得出叶片数。[结果与讨论]本研究提出的方法对小麦叶尖的识别精确率和mAP0.5分别达到91.6%和85.1%,具有良好的检测效果。在复杂大田环境下该方法具有更好的适应能力,能够在不同光照条件下实现自适应检测,模型鲁棒性强。小麦幼苗期叶片检测漏检率低,说明该方法能够满足复杂大田场景下小麦叶尖识别的需求,提高了小麦叶片数检测的准确性。[结论]本研究可为复杂大田场景下小麦叶片数检测的研究提供参考,为小麦长势高质量评估提供技术支撑。

LU-ReNet植物叶片分割与计数模型

为完成一种植物叶片分割与计数模型LU-ReNet,利用Xception module和CoordConv改进模型编码器,通过改进的ReNet模型并参照Unet模型结构将CNN和RNN结合在一起。在CVPPP的A1、A2、A3基准数据集上,LU-ReNet模型取得了0.95的平均F1-score、95.54%的平均前景-背景Dice(FBD%)、0.95的平均召回率和1.91的平均计数差分绝对值(|Dic|)。在A2基准数据集上,该模型表现超越大部分最新算法。实验结果表明,该网络在拥有高分割准确率的同时具有良好的泛化能力。

基于多视角时间序列图像的植物叶片分割与特征提取

为了解决多种类植物在生长过程中不同时间点动态变化表型参数提取困难问题,提出了一种基于多视角时间序列图像和深度卷积神经网络Mask RCNN的植物茎叶实例分割方法,在拟南芥、玉米和酸浆属3种代表性植物上进行了实验。结果表明,训练得到的基于Mask-RCNN的植物分割模型对在不同生长时期的植物茎叶的识别精度(mAP_(0.5))大部分在70.0%以上,最高可以达到87.5%,模型通用性较好。同时,针对茎叶遮挡问题提出的基于多视角图像的跟踪算法,可进一步提高植物茎叶参数提取的准确率。本文提出的以茎叶为代表的植物器官分割和特征提取方法具有性能高效、成本低、通用性和扩展性好的优势,可为不同场景下植物全生长过程中的多表型参数提取提供参考。

Blade pitch control of straight-bladed vertical axis wind turbine

Collective pitch control and individual pitch control algorithms were present for straight-bladed vertical axis wind turbine to improve the self-starting capacity.Comparative analysis of straight-bladed vertical axis wind turbine(SB-VAWT) with or without pitch control was conducted from the aspects of aerodynamic force,flow structure and power coefficient.The computational fluid dynamics(CFD) prediction results show a significant increase in power coefficient for SB-VAWT with pitch control.According to the aerodynamic forces and total torque coefficient obtained at various tip speed ratios(TSRs),the results indicate that the blade pitch method can increase the power output and decrease the deformation of blade;especially,the total torque coefficient of blade pitch control at TSR 1.5 is about 2.5 times larger than that of fixed pitch case.Furthermore,experiment was carried out to verify the feasibility of pitch control methods.The results show that the present collective pitch control and individual pitch control methods can improve the self-starting capacity of SB-VAWT,and the former is much better and its proper operating TSRs ranges from 0.4 to 0.6.

Airfoil effects on efficiency of 2 MW horizontal axis wind turbine blades

Optimization of airfoil characteristics such as lift and drag is essential for high efficiency wind turbine blade design. In this research, effects of airfoil lift and drag on blade power coefficients were investigated by using of wind turbine blade design software, PROPID. Firstly, a wind turbine blade of 2MW class was designed with DU-serics airfoils in the inner part and with aNACA series airfoil as a main airfoil in the outer part. Lift distribution was set to have near L/D maximum at each span station. Then, lift and drag curves were modified to observe effect of L/D variation. Drag and lift change with constant L/D on blade power coefficient was also studied for sensitivity investigation. Each case was optimized with Newtonian iteration incorporated in PROPID. High design lift coefficient results in less chord length and twist angle to maintain same aerodynamic load level. And, power coefficient wasn＇t improved much with high L/D. During the process, optimal inputs such as lift distribution, design lift and induction factors were suggested. As results, it was found that L/D maximization was important to obtain high efficiency. For the L/D maximization, lift maximization was important to minimize structural weight, but decreasing drag didn＇t affect the blade shape.

A Straight-bladed Vertical Axis Wind Turbine with a Directed Guide Vane Row-Effect of Guide Vane Geometry on the Performance-

The objective of this study is to show the effect of guide vane geometry on the performance. In order to overcome the disadvantages of vertical axis wind turbine, a straight-bladed vertical axis wind turbine （S-VAWT） with a directed guide vane row has been proposed and tested by the authors. According to previous studies, it was clarified that the performance of the turbine can be improved by means of the directed guide vane row. However, the guide vane geometry of S-VAWT has not been optimized so far. In order to clarify the effect of guide vanegeometry, the effects of setting angle and gap between rotor blade and guide vane on power coefticlent and start- ing characteristic were investigated in the experiments. The experimental study of the proposed wind turbine was carried out by a wind tunnel. The wind tunnel with a diameter of 1.8m is open jet type. The wind velocity is 8 m/s in the experiments. The rotor has three straight blades with a profile of NACA0018 and a chord length of 100 mm, a diameter of 0.6 m and a blade height of 0.7 m. The guide vane row consists of 3 arc plates.

Blade Parameterization and Aerodynamic Design Optimization for a 3D Transonic Compressor Rotor

The present paper describes an optimization methodology for aerodynamic design of turbomachinery combined with a rapid 3D blade and grid generator （RAPID3DGRID）, a N.S. solver, a blade parameterization method （BPM）, a gradient-based parameterization-analyzing method （GPAM）, a response surface method （RSM） with zooming algorithm and a simple gradient method. By the use of blade parameterization method a transonic com- pressor rotor can be expressed by a set of polynomials, and then it enables us to transform coordinate-expressed blade data to parameter-expressed and then to reduce the number of parameters. With changing any one of the parameters and by applying grid generator and N.S. solver, we can obtain several groups of samples. Here only ten parameters were considered to search an optimized compressor rotor. As a result of optimization, the adiabatic efficiency was increased by 1.73%.

Analysis of Internal Cooling Geometry Variations in Gas Turbine Blades

The present investigation analyzes the effects of major geometrical modifications to the interior of a convectioncooled gas turbine rotor blade. The main focus lies on the flow of the leading edge channels and the impact on theheat transfer. An experimental approach is performed with flow visualization via paint injection into water. Alsonumerical calculations are carried out in two sets, on the one hand water calculations accompanying the experimentsand on the other hand conjugate heat transfer calculations under realistic engine conditions. The latter calculationsare still ongoing delivering preliminary results.Five geometry configurations are investigated, three of them with differing turbulator arrangements in the leadingedge channels. The operating point of the base configuration is set to Re = 50,000 at the inlet while for the modifiedgeometries the pressure ratio is held constant compared to the base.Among several investigated configurations one could be identified that leads to a heat transfer enhancement inone leading edge channel 7 % larger compared to the base.

Retrofit design of composite cooling structure of a turbine blade by fluid networks and conjugate heat transfer methods

This article discusses the development of the numerical methods of gas flow coupled with heat transfer,and introduces the fluid net-works method for rapid prediction of the performance of the composite cooling structures in turbine blade.The reliability of these methods is verified by comparing experimental data.For a HPT rotor blade,a rapid prediction on the internal cooling structures is first made by using the fluid network analysis,then an assessment of aerodynamic and heat transfer characteristics is conducted.Based on the network analysis results,three ways to improve the design of the cooling structures are tested,i.e.,adjusting the cooling gas flow mass ratios for different inner cooling cavities,reducing the flow resistances of the channel turning structures,and improving the local internal cooling structure geometries with high temperature distribution.Through the verification of full three-dimensional gas/solid/coolant conjugate heat transfer calculation,we conclude that the modified design can make the overall temperature distribution more even by significantly reducing the highest temperature of the blade surface,and reasonably matching the parameters of different coolant inlets.The results show that the proposed calculation methods can remarkably reduce the design cycle of complex turbine blade cooling structure.

Computational Investigation of Blade slotting on a High-Load Low-Pressure Turbine Profile at various Reynolds Numbers:Part Ⅰ——Slotting Scheme's Verification

Boundary layer separation and reattachment is often an unavoidable feature of low pressure (LP) turbine,one of the main causes of this phenomenon is the high altitude low Reynolds number experienced by the modern LP turbine stage in aero-engine.Although an excellent turbine airfoil design can avoid flow separation on certain extent,but within flight envelope,LP turbine's characteristic Reynolds number may varied greatly,so it will be still under the risk of the presence of separation bubble.In this two parts paper a new concept of slotted-blade was raised to testify the gain of the blade slotting.A high aerodynamic loading LP turbine blade IET-LPTA was under investigated with different Reynolds number.Computational results reveal that the blade slotting could be a way of choice to suppress separation bubble and reduce profile loss under the condition of low Reynolds number,although its position and geometry need to be further investigated.

Numerical Simulation of Ice Accretion Phenomena on Rotor Blade of Axial Blower

Ice accretion is the phenomenon that super-cooled water droplets impinge and accrete on a body. It is well known that ice accretion on blades and airfoils leads to performance degradation and severe accidents. For this reason, experimental investigations have been carried out using flight tests or icing tunnels. However, it is too expensive, dangerous, and difficult to set actual icing conditions. Hence, computational fluid dynamics is useful to predict ice accretion. A rotor blade is one of jet engine components where ice accretes. Therefore, the authors focus on the ice accretion on a rotor blade in this study. Three-dimensional icing phenomena on the rotor blade of a commercial axial blower are computed here, and ice accretion on the rotor blade is numerically investigated.