Mechanism analysis of hysteretic aerodynamic characteristics on variable-sweep wings

Variable-sweep wings have large shape-changing capabilities and wide flight envelops,which are considered as one of the most promising directions for intelligent morphing UAVs.Aerodynamic investigations always focus on several static states in the varying sweep process,which ignore the unsteady aerodynamic characteristics.However,deviations to static aerodynamic forces are inevitably caused by dynamic sweep motion.In this work,first,unsteady aerodynamic characteristics on a typical variable-sweep UAV with large aspect ratio were analyzed.Then,deep mechanism of unsteady aerodynamic characteristics in the varying sweep process was studied.Finally,numerical simulation method integrated with structured moving overset grids was applied to solve the unsteady fluid of varying sweep process.The simulation results of a sweep forward-backward circle show a distinct dynamic hysteresis loop surrounding the static data for the aerodynamic forces.Compared with the static lift coefficients,at the same sweep angles,dynamic lift coefficient in sweep forward process are all smaller,while dynamic sweep backward lift coefficient are all larger.In addition,dynamic deviations to static lift coefficient are positively related with the varying sweep speeds.Mechanism study on the unsteady aerodynamic characteristics indicates that three key factors lead to the dynamic hysteresis loop in varying sweep process.They are the effects of additional velocity caused by varying sweep motion,the effects of flow hysteresis and viscosity.The additional velocity induced by sweep motion affects the transversal flow direction along the wing and the effective angle of attack at the airfoil profile.The physical properties of flow,the hysteresis and viscosity affect the unsteady aerodynamic characteristics by flow separation and induced vortexes.

Development and formation of wing cuticle based on transcriptomic analysis in Locusta migratoria during metamorphosis

Wings are an important flight organ of insects.Wing development is a complex process controlled by a series of genes.The flightless wing pad transforms into a mature wing with the function of migratory flight during the nymphto-adult metamorphosis.However,the mechanism of wing morphogenesis in locusts is still unclear.This study analyzed the microstructures of the locust wing pads at pre-eclosion and the wings after eclosion and performed the comparative transcriptome analysis.RNA-seq identified 25,334 unigenesand 3,430 differentially expressed genes(DEGs)(1,907 up-regulated and 1,523 down-regulated).The DEGs mainly included cuticle development(LmACPs),chitin metabolism(Lm Idgf4),lipid metabolism-related genes,cell adhesion(Integrin),zinc finger transcription factors(LmSalm,LmZF593 andLmZF521),and others.Functional analysis based on RNA interference and hematoxylin and eosin(H&E)staining showed that the three genes encoded zinc finger transcription factors are essential for forming wing cuticle and maintaining morphology in Locusta migratoria.Finally,the study found that the LmSalm regulates the expression of LmACPs in the wing pads at pre-eclosion,and LmZF593 and LmZF521 regulate the expression of LmIntegrin/LmIdgf4/LmHMT420 in the wings after eclosion.This study revealed that the molecular regulatory axis controls wing morphology in nymphal and adult stages of locusts,offering a theoretical basis for the study of wing development mechanisms in hemimetabolous insects.

Wings-FDY一步法生产ITY的工艺研究

通过设备改造及工艺优化,成功实现了ITY在Wings-FDY设备上一步法生产。研究结果表明:风压设定为30 Pa,调整纺丝/卷绕上油比例为6:4,预热辊温度51℃,定型辊温度124℃,拉伸倍数3.2,卷绕速度3550 m/min时,ITY 148dtex/108f纺况稳定,物理指标均匀,满足客户定制化的产品需求。

Structural design and modal behaviors analysis of a new swept baffled inflatable wing

Inflatable wing has significant application value in the design of loitering munitions because of its advantages such as lightweight and foldability.However,due to the flexible characteristics,aeroelastic behaviors of inflatable wings such as flutter are nonnegligible in flight.By designing a certain angle between the inflatable beam and the wing span,the structural dynamic and even the aeroelastic performance of the inflatable wing can be effectively improved.Based on the analysis of the mechanical and geometric characteristics of the inflatable structure,a new inflatable wing with sweep arranged inflatable beams is proposed,and the main design variables and methods are analyzed.For purpose of investigating the aeroelastic performance of the swept baffled inflatable wing,the modal behaviors by considering the wet mode are studied.In consideration of the deficiencies of the traditional wet modal analysis method,by introducing the influence on the additional stiffness of flow field,an added massstiffness method is proposed in this paper,and the advantages are verified by ground vibration experiments.On this basis,the effects of baffles sweep angle,pressure,and boundary conditions on the modal parameters and aeroelastic performance of inflatable wing are analyzed.The results show that the aeroelastic performance of the inflatable wing can be designed by changing the baffles sweep angle,which is enlightened for the aeroelastic tailoring design on inflatable wings.

Quantitative analysis of the morphing wing mechanism of raptors:Morphing kinematics of Falco peregrinus wing

Raptors are getting more attention from researchers because of their excellent flight abilities.And the excellent wing morphing ability is critical for raptors to achieve high maneuvering flight,which can be a good bionic inspiration for unmanned aerial vehicles(UAV)design.However,morphing wing motions of Falco peregrinus with multi postures cannot be consulted since such a motion database was nonexistent.This study aimed to provide data reference for future research in wing morphing kinetics.We used the computed tomography(CT)approach to obtain nine critical postures of the Falco peregrinus wing skeleton,followed with motion analysis of each joint and bone.Based on the obtained motion database,a six-bar kinematic model was proposed to regenerate wing motions with a high fidelity.

Damage assessment of aircraft wing subjected to blast wave with finite element method and artificial neural network tool

Damage assessment of the wing under blast wave is essential to the vulnerability reduction design of aircraft. This paper introduces a critical relative distance prediction method of aircraft wing damage based on the back-propagation artificial neural network(BP-ANN), which is trained by finite element simulation results. Moreover, the finite element method(FEM) for wing blast damage simulation has been validated by ground explosion tests and further used for damage mode determination and damage characteristics analysis. The analysis results indicate that the wing is more likely to be damaged when the root is struck from vertical directions than others for a small charge. With the increase of TNT equivalent charge, the main damage mode of the wing gradually changes from the local skin tearing to overall structural deformation and the overpressure threshold of wing damage decreases rapidly. Compared to the FEM-based damage assessment, the BP-ANN-based method can predict the wing damage under a random blast wave with an average relative error of 4.78%. The proposed method and conclusions can be used as a reference for damage assessment under blast wave and low-vulnerability design of aircraft structures.

In-flight deformation measurement for high-aspect-ratio wing based on 3D speckle correlation

In order to get an effective solution of the in-flight wing deformation measurement for high-wing aircrafts with high-aspect-ratio,a method based on three-dimensional(3D)speckle correlation technique is proposed.Firstly,an in-flight wing deformation measurement system with two sets of conjugate cameras is designed based on structural characteristics and test requirements of high-wing aircrafts with large-aspect-ratio.Secondly,the in-flight wing deformation measurement method based on 3D speckle correlation technique is introduced including three aspects:measuring system and wing datum calibration,speckle image matching and 3D reconstruction,and wing deformation analysis.Fi-nally,ground simulation test of dynamic deformation measurement of a scaled model wing and flight test of dynamic deformation measurement of a large transport wing are carried out.The test results show that the measuring accuracy of single point coordinate in ground simulation test is better than 0.1 mm/m,in the airborne vibration environment,the static single-point positioning accuracy is bet-ter than 5 mm,and the in-flight wing deformation measurement data is well received by the flight test engineers.This method can satisfy the requirements of stability,reliability,high precision,non-con-tact and full-field measurement for dynamic deformation measurement of aircraft wing with high-as-pect-ratio.

WiNG节点仪器应用简介

WiNG节点仪器是Sercel公司的第三代节点仪器产品,具有轻便、续航时间长、无线实时质控、数据下载与充电一体化、数据管理软件操作简单、桩号自动拟合、RFID标签等特点;其无线质控有近距离的点对点直连,用于获取详细的节点运行状态数据、运行测试、查看噪音等,和通过接力回传实现远距离节点站状态结果信息获取。2022年底国内首次引进该节点仪器系统并在中石化山东某三维地震勘探工区实施了大规模应用,取得了良好的应用效果。本文结合实际应用介绍了WiNG节点仪器的功能特点。

Decomposition of Mathematical Programming Models for Aircraft Wing Design Facilitating the Use of Dynamic Programming Approach

Aircraft designers strive to achieve optimal weight-reliability tradeoffs while designing an aircraft. Since aircraft wing skins account for more than fifty percent of their structural weight, aircraft wings must be designed with utmost care and attention in terms of material types and thickness configurations. In particular, the selection of thickness at each location of the aircraft wing skin is the most consequential task for aircraft designers. To accomplish this, we present discrete mathematical programming models to obtain optimal thicknesses either to minimize weight or to maximize reliability. We present theoretical results for the decomposition of these discrete mathematical programming models to reduce computer memory requirements and facilitate the use of dynamic programming for design purposes. In particular, a decomposed version of the weight minimization problem is solved for an aircraft wing with thirty locations (or panels) and fourteen thickness choices for each location to yield an optimal minimum weight design.

Structural Design and Analysis of Small Flapping Wing Aircraft Based on the Crank Slider Mechanism

In this project,the miniaturization of the aircraft was realized under the premise of strong maneuverability,high concealability,and driving a certain load,and the flight mode and structural characteristics of birds were imitated.A small bionic flapping wing aircraft was built.The flapping of the wing was realized by the crank slider mechanism,and the sizes of each part were calculated according to the bionics formula.The wingspan was 360.37 mm,the body width was 22 mm,the body length was 300 mm,the wing area was 0.05 m^(2),the flapping amplitude was 71°.ADAMS software was used to simulate the dynamics of the designed aircraft,and the variation of flapping amplitude and angular velocity during the movement of the aircraft was obtained,which verified the feasibility of the mechanism.The prototype aircraft was made for flight test,and the designed bionic flapping wing aircraft achieved the expected effect.It provides a theoretical basis and data support for the design and manufacture of small flapping wing aircraft.

集体记忆与历史重述——左翼作家的“左翼文学”回忆

左翼作家对“左翼文学”的回忆蔚为大观,构成现代中国不容忽略而又意味深远的文化景观。其重构历史的强烈意图,与当下政治生态、社会现实之间的深层互动,使其足以作为实践中国现代文学研究“记忆的转向”的典型样本。左翼作家通过个人史、“左联”史和左翼文学史的叙述,完成形象重塑、身份认同、重构历史、接续传统等多种意图,充分体现话语生产与意识形态之间的紧密关系。“左翼文学”回忆对社会框架十分依赖,呈现出明显的“集体记忆”特征,打上了社会主导思想和主流意识形态的深深印记,但“个体记忆”又常常逸出“社会框架”,对集体记忆构成冲击与反抗,使得左翼作家的回忆呈现出微妙的张力。然而无论如何,左翼作家的“左翼文学”回忆都在很大程度上重构了中国现代文学史,深度影响了我们对左翼文学的认知。

Wings-plus设备生产全消光FDY工艺探讨

在大容量聚酯熔体直纺生产线上进行设备技术改造,在熔体输送管道上通过在线添加注射设备将全消光母粒注射进入熔体,并在动态混合器中混合均匀,得到全消光聚酯熔体,采用巴马格的Wings-plus FDY生产设备的一步拉伸工艺生产全消光FDY纤维。该方法成本投入小,得到的全消光纤维物理指标可以满足中高端客户需求。

Navigating Temporal and Spatial Dimensions:Unveiling the Fictional Essence and Authenticity in the Narrative of The Rise and Fall of Wing Shing Street

The novel The Rise and Fall of Wing Shing Street delves into the reality of Hong Kong residents deeply attuned to spatial awareness but detached from temporal significance,entangling emotions surrounding time and space.Through narrative interruption and extension,the author portrays the genuine struggles of Hong Kong inhabitants-juxtaposing the blurred boundaries of time and space and the inherent rootlessness of reality within a fictionalized framework.Emphasizing the 20th-century human condition,wherein spatial awareness overshadows temporal understanding,the novel underscores the consequences:a loss of history and cultural identity.With a fresh perspective,the narrative explores the interplay of time and space,accentuating both the fictitious and authentic dimensions.This prompts readers to reconsider their history,culture,and the current moment,ultimately highlighting the pivotal role of temporal awareness.

一种小型火工机构的输出计算及其验证

针对某折叠翼展开机构的小型化难题,研究了一种小型火工机构。利用内弹道理论建立了该火工机构的输出理论模型,通过理论模型计算和优化了机构参数,并用有限元法校验了计算结果。测试结果表明:该原型机具备了小型特点,其输出角度达到了128.5°。在逆风和顺风负载下,该火工机构的工作时间均小于200 ms,其最大角速度不大于3 000 (°)/s,试验数据证实该火工机构具备缓冲作用,理论计算结果和试验数据基本一致。研究成果可作为薄型折叠翼的一种设计方法,为薄型折叠翼的工程应用奠定技术基础。

变形翼舵技术在导弹领域的应用需求及技术发展路线

采用变形翼舵技术可解决导弹对发射平台尺寸强约束问题,改善导弹升阻比及弹道末段机动性能,实现飞行全程气动外形最优,适应多任务作战需求。对国内外变形翼舵技术发展进行了概述,介绍了变形翼舵方案组成,分析了导弹对变形翼舵技术的需求,提出了单次阶跃变形、往复伸缩变形、柔性连续变形三阶段技术发展路线以及各阶段的关键技术,为变形翼舵技术在导弹武器领域的深入研究及应用提供了参考。

高压管汇由壬翼形螺母的失效原因

页岩气压裂施工中,某高压管汇由壬翼形螺母在服役期间发生断裂,从失效由壬翼形螺母断口位置取样,进行宏观、微观观察,断口能谱分析,硬度测试及金相检验等,并利用ABAQUS软件对由壬翼形螺母进行力学分析,揭示其失效机理。结果表明:螺母内径存在多点疲劳源,断口中央有明显贝纹线且被红褐色(Fe_(2)O_(3))、黄绿色(FeCl_(2))腐蚀产物覆盖;微观断口表面存在球状氧化物,能谱分析表明其含有一定量的Ca、Si元素,螺母原材料中存在较多C类和D类非金属氧化物;硬度和金相组织均达到工艺要求;有限元分析所得产生应力集中的部位与实际断裂位置一致,即靠近母由壬螺纹顶端处,且最大应力为910 MPa,超出材料屈服强度。故由壬翼形螺母失效机理为腐蚀疲劳断裂。最后,提出了相应的改进措施。

四川地区精细化降水预报融合订正试验及检验

精细化定量降水网格预报是天气预报业务的重点和难点,基于西南区域智能数值网格模式预报系统(Southwest China WRF-based Intelligent Numeric Grid forecast System,SWC-WINGS)1 km×1 km分辨率的小时降水预报,利用时间滞后和概率匹配方法开展融合订正试验,再利用中国气象局多源融合降水系统(CMA Multi-source Precipitation Analysis System,CMPAS)三源融合降水实况格点数据,对2022年7—8月四川地区的小时降水预报融合订正结果进行检验,并在四川盆地西部一次短时强降水天气过程中进行应用,结果表明:(1)时间滞后集合降水预报相较于模式降水预报,存在小量级预报过度,大量级预报过于保守的问题;(2)时间滞后结合概率匹配的降水预报融合订正方法有效提升了各量级降水预报的TS评分,尤其1~2 h预报时效提升显著,小时雨量超过0.1 mm、5 mm、10 mm和20 mm量级的TS评分平均提升率分别为7.2%、17.2%、28.3%和36.3%;(3)一次短时强降水天气过程的应用结果表明,时间滞后结合概率匹配的融合订正方法对模式小时降水预报有较好的改进效果,尤其对大量级降水预报有较强的订正能力。

扑翼机器人机载视觉避障系统设计

扑翼机器人是一种高仿生度的飞行器,它可以执行军事侦察和民用监测任务。在执行这些任务时,避障是一种确保扑翼机器人安全的必要功能。本文设计了一种基于单目视觉的扑翼机器人自主避障系统,其中所有图像的处理计算均使用机载处理器实现。在这个系统中,机载处理器的质量被减至48 g,以便于扑翼机器人可以携带它稳定飞行。该系统的工作流程可以分为以下几步:首先,图像采集模块获取周围环境的视频图像;然后,机载处理器通过处理扑翼机器人第一视角的光流信息来计算方向舵角度和转弯方向;最后,飞控板接收计算结果并控制扑翼机器人避开障碍物。地面站对扑翼机器人飞行过程进行实时监测,实验结果验证了本文所设计的避障系统的有效性。

创新教育背景下工业设计专业“一体两翼四驱动”教学模式研究

近年来,国家倡导素质教育,提倡在高等院校加大实践能力和创新能力的培养,各高校不断进行教学模式改革和创新,取得了一定成效,但仍没能摆脱传统观念和教学模式的束缚。为适应行业发展趋势和需求,坚持以人为本的教育理念,紧跟时代步伐,引入“一体两翼四驱动”教学模式,开展“一体两翼四驱动”协同育人改革实践,以培养高素质创新复合型人才为主要目的,增强学生实践能力和创新能力,从根本上提升人才培养质量,以满足高速发展的社会需求,为高校人才培养模式变革提供参考依据。

基于网络药理学探索鬼箭羽治疗糖尿病的机制

目的 通过网络药理学预测鬼箭羽治疗糖尿病的作用机制。方法 鬼箭羽药物成分靶点来自中药系统药理学数据库及分析平台(TCMSP)。用基因数据库查询相应基因,利用Cytoscape软件构建网络图。采用基因本体论(GO)功能富集分析和京都基因与基因组百科全书(KEGG)通路富集分析,预测鬼箭羽治疗糖尿病的作用机制及潜在靶点。结果 “药物-化合物-靶点-疾病”网络图包含了21种活性成分和154个交叉靶点,主要靶点包括视网膜母细胞瘤基因1(RB1)、细胞周期蛋白D1(CCND1)、丝氨酸/苏氨酸激酶(AKT1)和丝裂原活化蛋白激酶(MAPK)。通过GO功能富集分析,共获得了20个项目(P<0.05)。KEGG通路富集分析筛选了13条信号通路(P<0.05),其中的脂质和动脉粥样硬化、流体剪切应力与动脉粥样硬化、高级糖基化终末产物-受体(AGE-RAGE)信号通路,对糖尿病有作用。结论 鬼箭羽的活性成分可通过作用于RB1、CCND1、AKT1、MAPK1、MAPK3等多个靶点来调节胰岛素的分泌,从而对糖尿病发挥治疗作用。