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Track-before-detect for bistatic radar based on pseudo-spectrum 基于伪频谱的双基地雷达探测前跟踪
IF 5.7 1区 工程技术 Q1 ENGINEERING, AEROSPACE Pub Date : 2024-01-01 DOI: 10.1016/j.cja.2023.08.021
Tao HAN , Gongjian ZHOU

Track-Before-Detect (TBD) is an efficient method to detect dim targets for radars. Conventional TBD usually follows an approximate motion model of the target, which may cause an inaccurate integration of the target energy. A TBD technique on basis of pseudo-spectrum in mixed coordinates adopting an accurate motion model for bistatic radar system is developed in this paper. The predicted position in bistatic polar plane is derived according to a nonlinear function that exactly describes the constant Cartesian velocity motion. Then around the predicted position, a pseudo-spectrum is formulated and its samples are accumulated to the integration frame for energy integration. The evolution of the state and the procedure of accumulation of the target energy are derived elaborately. The superior performance of the proposed method is demonstrated by some simulations.

先跟踪后检测(TBD)是雷达探测昏暗目标的一种有效方法。传统的 TBD 通常遵循目标的近似运动模型,这可能会导致目标能量积分不准确。本文开发了一种基于混合坐标伪频谱的 TBD 技术,该技术采用了双稳态雷达系统的精确运动模型。根据精确描述笛卡尔匀速运动的非线性函数,得出双稳态极坐标面上的预测位置。然后,围绕预测位置制定伪频谱,并将其样本累积到积分框架进行能量积分。对状态的演变和目标能量的积累过程进行了详细推导。通过一些模拟,证明了所提方法的优越性能。
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引用次数: 0
An aircraft brake control algorithm with torque compensation based on RBF neural network 基于RBF神经网络的转矩补偿飞机制动控制算法
IF 5.7 1区 工程技术 Q1 ENGINEERING, AEROSPACE Pub Date : 2024-01-01 DOI: 10.1016/j.cja.2023.06.010
Ning BAI , Xiaochao LIU , Juefei LI , Zhuangzhuang WANG , Pengyuan QI , Yaoxing SHANG , Zongxia JIAO

The wheel brake system of an aircraft is the key to ensure its safe landing and rejected takeoff. A wheel’s slip state is determined by the brake torque and ground adhesion torque, both of which have a large degree of uncertainty. It is this nature that brings upon the challenge of obtaining high deceleration rate for aircraft brake control. To overcome the disturbances caused by the above uncertainties, a braking control law is designed, which consists of two parts: runway surface recognition and wheel’s slip state tracking. In runway surface recognition, the identification rules balancing safety and braking efficiency are defined, and the actual identification process is realized through recursive least square method with forgetting factors. In slip state tracking, the LuGre model with parameter adaptation and a brake torque compensation method based on RBF neural network are proposed, and their convergence are proven. The effectiveness of our control law is verified through simulation and ground experiment. Especially in the experiments on the ground inertial test bench, compared to the improved pressure-biased-modulation (PBM) anti-skid algorithm, fewer wheel slips occur, and the average deceleration rate is increased by 5.78%, which makes it a control strategy with potential for engineering applications.

飞机的机轮制动系统是确保飞机安全着陆和拒绝起飞的关键。机轮的滑移状态由制动力矩和地面附着力矩决定,而这两个力矩都具有很大的不确定性。正是这一特性给飞机制动控制带来了获得高减速率的挑战。为了克服上述不确定性带来的干扰,设计了一种制动控制法则,它由两部分组成:跑道表面识别和机轮滑移状态跟踪。在跑道表面识别中,定义了平衡安全性和制动效率的识别规则,实际识别过程通过带有遗忘因子的递归最小二乘法实现。在滑移状态跟踪方面,提出了参数自适应的 LuGre 模型和基于 RBF 神经网络的制动扭矩补偿方法,并证明了它们的收敛性。通过仿真和地面实验验证了我们的控制法则的有效性。特别是在地面惯性试验台实验中,与改进的压力偏置调制(PBM)防滑算法相比,车轮打滑现象减少,平均减速率提高了 5.78%,是一种具有工程应用潜力的控制策略。
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引用次数: 0
Design and calibration of spoke piezoelectric six-dimensional force/torque sensor for space manipulator 空间机械臂轮辐式压电六维力/扭矩传感器的设计与标定
IF 5.7 1区 工程技术 Q1 ENGINEERING, AEROSPACE Pub Date : 2024-01-01 DOI: 10.1016/j.cja.2023.03.012
Yingjun LI, Guicong WANG, Shuai ZHANG, Yuanqin ZHOU, Hongyu LI, Zhenguang QI

The large manipulator outside the space cabin is a multi-degree of freedom actuator for space operations. In order to realize the automatic control and flexible operation of the space manipulator, a novel spoke structure piezoelectric six-dimensional force/torque sensor with redundancy ability, high stiffness and good decoupling performance is innovatively proposed. Based on the deformation coordination relationship, the redundancy measurement mechanism is revealed. The mathematical models of the sensor with and without branch fault are established respectively. The finite element model is established to verify the feasibility of structure and redundancy measuring principle of the sensor. Depending on the theoretical analysis and simulation analysis, the prototype of the sensor is developed. Static and dynamic calibration experiments are carried out. The actual output voltage signal of the six-dimensional force/torque sensor is collected to establish the equation between the standard input applied load and the actual output voltage signal. Based on ant colony optimized BP algorithm, performance indexes of the sensor with and without branch fault are analyzed respectively. The experimental results show that the spoke piezoelectric six-dimensional force/torque sensor with the eight-point support structure has good accuracy and reliability. Meanwhile, it has strong decoupling characteristic that can effectively shield the coupling between dimensions. The nonlinear errors and maximum interference errors of decoupled data with and without branch faults are less than 1% and 2%, respectively. The natural frequency of the six-dimensional force sensor can reach 2856.45 Hz and has good dynamic characteristics. The research content lays a theoretical and experimental foundation for the design, development and application of the new six-dimensional force/torque sensors with redundancy. Meanwhile, it will significantly improve the research level in this field, and provide a strong guarantee for the smooth implementation of force feedback control of the space station manipulator project.

太空舱外的大型机械手是用于太空操作的多自由度执行器。为实现空间机械手的自动控制和灵活操作,创新性地提出了一种冗余能力强、刚度高、解耦性能好的新型辐条结构压电六维力/力矩传感器。基于变形协调关系,揭示了冗余测量机理。分别建立了有分支故障和无分支故障传感器的数学模型。建立了有限元模型,验证了传感器结构和冗余测量原理的可行性。在理论分析和仿真分析的基础上,研制出传感器的原型。进行了静态和动态校准实验。采集六维力/力矩传感器的实际输出电压信号,建立标准输入负载与实际输出电压信号之间的方程。基于蚁群优化 BP 算法,分别分析了有分支故障和无分支故障传感器的性能指标。实验结果表明,采用八点支撑结构的辐条式压电六维力/力矩传感器具有良好的精度和可靠性。同时,它具有很强的去耦特性,能有效屏蔽尺寸间的耦合。有分支故障和无分支故障的解耦数据的非线性误差和最大干扰误差分别小于 1%和 2%。六维力传感器的固有频率可达 2856.45 Hz,具有良好的动态特性。研究内容为设计、开发和应用新型冗余六维力/力矩传感器奠定了理论和实验基础。同时,将显著提高该领域的研究水平,为空间站机械手项目力反馈控制的顺利实施提供有力保障。
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引用次数: 0
A low-power Bluetooth-based wireless sensor network and its global confliction-solving impact localization method 基于蓝牙的低功耗无线传感器网络及其全局冲突求解冲击定位方法
IF 5.7 1区 工程技术 Q1 ENGINEERING, AEROSPACE Pub Date : 2024-01-01 DOI: 10.1016/j.cja.2023.05.004
Yuanjia WANG , Lei QIU , Qiyun XU , Liming SHI

During the whole service lifetime of aircraft structures with composite materials, impacts are inevitable and can usually cause severe but barely visible damages. Since the occurrences of impact are random and unpredictable, it is a hotspot direction to develop an online impact monitoring system that can meet strict limitations of aerospace applications including small size, light weight, and low power consumption. Piezoelectric (PZT) sensor, being able to generate impact response signals with no external power and cover a large-scale structure with only a small amount of them, is a promising choice. Meanwhile, for real systems, networks with multiple nodes are normally required to monitor large-scale structures in a global way to identify any impact localization confliction, yet the existing studies are mostly evaluated with single nodes instead of networks. Therefore, in this paper, based on a new low-power node designed, a Bluetooth-based digital impact monitoring PZT sensor network is proposed for the first time with its global confliction-solving impact localization method. Evaluations of the system as a network are researched and analyzed on a complex real aircraft wing box for a global confliction-solving impact localization, showing a satisfying high accuracy.

在复合材料飞机结构的整个使用寿命期间,撞击是不可避免的,通常会造成严重但几乎不可见的损坏。由于撞击的发生具有随机性和不可预测性,因此开发一种能够满足航空航天应用的严格限制(包括体积小、重量轻和低功耗)的在线撞击监测系统是一个热点方向。压电(PZT)传感器无需外接电源即可产生冲击响应信号,且只需少量传感器即可覆盖大型结构,是一个很有前景的选择。同时,在实际系统中,通常需要由多个节点组成的网络对大型结构进行全局监控,以识别任何撞击定位冲突,但现有研究大多以单个节点而非网络进行评估。因此,本文基于新设计的低功耗节点,首次提出了基于蓝牙的数字冲击监测 PZT 传感器网络及其全局冲突解决冲击定位方法。在一个复杂的真实飞机翼盒上研究和分析了该系统作为一个网络进行全局冲突解决冲击定位的评估,显示出令人满意的高精度。
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引用次数: 0
makeTwin: A reference architecture for digital twin software platform makeTwin:数字孪生软件平台的参考体系结构
IF 5.7 1区 工程技术 Q1 ENGINEERING, AEROSPACE Pub Date : 2024-01-01 DOI: 10.1016/j.cja.2023.05.002
Fei TAO , Xuemin SUN , Jiangfeng CHENG , Yonghuai ZHU , Weiran LIU , Yong WANG , Hui XU , Tianliang HU , Xiaojun LIU , Tingyu LIU , Zheng SUN , Jun XU , Jinsong BAO , Feng XIANG , Xiaohui JIN

Digital twin is currently undergoing a significant transformation from the conceptual and theoretical research phase to the implementation and application phase. However, a universally adaptable research and development platform for digital twin is critically needed to meet the development requirements. Specifically, a publicly accessible simulation, testing, and validation platform which can support digital twin model building, data processing, algorithm design, configuration, etc., is urgently required for researchers. Furthermore, for developers from the industry, a low-code development platform that can offer a customizable suite of functions such as model creation, data management, protocol configuration, and visualization is urgently needed. Meanwhile, for enterprise users, there is a lack of an application management platform that can be configured and migrated for various application scenarios, functions, and modes. Therefore, based on the system research of digital twin theories and key technologies by the authors (such as the five-dimension digital twin model, digital twin modeling and digital twin data theory, digital twin standards, and so on), a digital twin software platform reference architecture, namely makeTwin, is proposed and designed, as well as its ten core functions. The workflow of the makeTwin and the interaction mechanisms among its core functions are described. Finally, a digital twin application system for a chemical fiber textile shop floor (CFTS) which was developed according to makeTwin, is introduced, which validates the proposed reference architecture.

数字孪生目前正在经历从概念和理论研究阶段到实施和应用阶段的重大转变。然而,数字孪生亟需一个具有普遍适应性的研发平台来满足发展要求。具体来说,研究人员迫切需要一个可公开访问的模拟、测试和验证平台,该平台可支持数字孪生模型构建、数据处理、算法设计和配置等。此外,对于行业开发人员来说,迫切需要一个低代码开发平台,以提供可定制的功能套件,如模型创建、数据管理、协议配置和可视化。同时,对于企业用户来说,缺乏一个可以针对不同应用场景、功能和模式进行配置和迁移的应用管理平台。因此,基于作者对数字孪生理论和关键技术的系统研究(如五维数字孪生模型、数字孪生建模与数字孪生数据理论、数字孪生标准等),提出并设计了数字孪生软件平台参考架构,即 makeTwin,以及其十大核心功能。介绍了 makeTwin 的工作流程及其核心功能之间的交互机制。最后,介绍了根据 makeTwin 开发的化纤纺织车间(CFTS)数字孪生应用系统,验证了所提出的参考架构。
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引用次数: 4
Inhibiting plastic tensile instability of non-symmetric thin-walled shell component via increasing regional metal inflow based on heterogeneous pressure-carrying medium 基于非均质载压介质增加区域金属流入抑制非对称薄壁壳构件塑性拉伸失稳
IF 5.7 1区 工程技术 Q1 ENGINEERING, AEROSPACE Pub Date : 2024-01-01 DOI: 10.1016/j.cja.2023.05.014
Nan XIANG , Yiquan SHU , Pengyi WANG , Menghan YANG , Haoran WANG , Tao HUANG , Junqing GUO , Fuxiao CHEN

Heterogeneous pressure-carrying medium was employed to establish a differentiated pressure field on sheet metal in flexible die forming process in this work, which aimed at matching the non-symmetric shape of target component and improving metal inflow to avoid local tensile instability. Specifically, metal inflow corresponding to the differentiated pressure field was analytically evaluated. Forming of a typical non-symmetric shell component was experimentally and numerically studied based on the proposed method. Compared with forming processes based on the uniform pressure, difference of metal inflow in two sides of the non-symmetric component increased from 2.16 mm to 3.36 mm and metal inflow in critical region increased by 11.9% when differentiated pressure field (taking heterogeneous elastomer #4–3 for example) was employed. The resultant maximum thinning ratio decreased by 4.2% and the uniformity of shell thickness increased by 16.9%. With the decrease of Shore hardness of elastomer in the formed region, stress path in the ready-to-form region transferred towards the bi-axial tension stress state, i.e., stress ratio (α) increased. And, stress triaxiality (η) in characteristic regions were regulated appropriately, which decreased the risk of tensile instability. It was attributed to the decreased normal pressure and frictional resistance at sheet/elastomer interface in the formed region.

本研究采用异质载压介质,在柔性模塑成型工艺中对金属板材建立差异化压力场,旨在匹配目标部件的非对称形状,改善金属流入量,避免局部拉伸不稳定性。具体而言,我们对与分化压力场相对应的金属流入量进行了分析评估。根据所提出的方法,对典型非对称壳体部件的成形进行了实验和数值研究。与基于均匀压力的成形过程相比,采用分压场(以异质弹性体 #4-3 为例)时,非对称部件两侧的金属流入量差值从 2.16 mm 增加到 3.36 mm,临界区的金属流入量增加了 11.9%。因此,最大减薄率降低了 4.2%,壳体厚度的均匀性提高了 16.9%。随着成型区域弹性体邵氏硬度的降低,准备成型区域的应力路径向双轴拉伸应力状态转移,即应力比 (α)增加。特征区域的应力三轴性(η)得到了适当的调节,从而降低了拉伸不稳定性的风险。这归因于成型区域板材/弹性体界面的法向压力和摩擦阻力减小。
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引用次数: 0
Mechanical properties of multi-scale germanium specimens from space solar cells under electron irradiation 空间太阳能电池多尺度锗样品在电子辐照下的力学性能
IF 5.7 1区 工程技术 Q1 ENGINEERING, AEROSPACE Pub Date : 2024-01-01 DOI: 10.1016/j.cja.2023.05.006
Jian QIU , Maliya HEINI , Jusha MA , Wenjia HAN , Xunchun WANG , Jun YIN , Yan SHI , Cunfa GAO

During long-term service in space, Gallium Arsenide (GaAs) solar cells are directly exposed to electron irradiation which usually causes a dramatic decrease in their performance. In the multilayer structure of solar cells, the germanium (Ge) layer occupies the majority of the thickness as the substrate. Due to the intrinsic brittleness of semiconductor material, there exist various defects during the preparation and assembly of solar cells, the influences of which tend to be intensified by the irradiation effect. In this work, first, Ge specimens for mechanical tests were prepared at scales from microscopic to macroscopic. Then, after different doses of electron irradiation, the mechanical properties of the Ge specimens were investigated. The experimental results demonstrate that electron irradiation has an obvious effect on the mechanical property variation of Ge in diverse scales. The four-point bending test indicates that the elastic modulus, fracture strength, and maximum displacement of the Ge specimens all increase, and reach the maximum value at the irradiation dose of 1 × 1015 e/cm2. The micrometer scale cantilever and nanoindentation tests present similar trends for Ge specimens after irradiation. Atomic Force Microscope (AFM) also observed the change in surface roughness. Finally, a fitting model was established to characterize the relation between modulus change and electron irradiation dose.

砷化镓(GaAs)太阳能电池在太空中长期使用时,会直接受到电子辐照,这通常会导致其性能急剧下降。在太阳能电池的多层结构中,锗(Ge)层作为衬底占据了大部分厚度。由于半导体材料本身的脆性,在太阳能电池的制备和组装过程中存在各种缺陷,而辐照效应往往会加剧这些缺陷的影响。在这项工作中,首先制备了从微观到宏观尺度的机械测试用 Ge 试样。然后,经过不同剂量的电子辐照,对 Ge 试样的机械性能进行了研究。实验结果表明,电子辐照对不同尺度的 Ge 力学性能变化有明显的影响。四点弯曲试验表明,Ge 试样的弹性模量、断裂强度和最大位移均有所增加,并在辐照剂量为 1 × 1015 e/cm2 时达到最大值。微米尺度悬臂和纳米压痕测试也显示出辐照后 Ge 试样的类似趋势。原子力显微镜(AFM)也观察到了表面粗糙度的变化。最后,建立了一个拟合模型来描述模量变化与电子辐照剂量之间的关系。
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引用次数: 0
Gear walk instability caused by brake-disc friction characteristics 制动盘摩擦特性导致齿轮行走不稳定
IF 5.7 1区 工程技术 Q1 ENGINEERING, AEROSPACE Pub Date : 2023-12-13 DOI: 10.1016/j.cja.2023.12.011
Xiaoqiong DU , Bin LI , Wen CAI , Linyin LUO

A multi-body dynamic rigid-flexible coupling model of landing gear is established to study the gear walk instability caused by the friction characteristics of the brake disc. After validating the model with the experimental results, the influence of the landing gear structure and braking system parameters on gear walk is further investigated. Among the above factors, the slope of the graph for the friction coefficient of the brake disc and the relative velocity of brake stators and rotors is the most influential factor on gear walk instability. Phase trajectory analysis verifies that gear walk occurs when the coupling of multiple factors causes the system to exhibit an equivalent negative damping trend. To consider a more realistic braking case, a back propagation neural network method is employed to describe the nonlinear behavior of the friction coefficient of the brake disc. With the realistic nonlinear model of the friction coefficient, the maximum error in predicting the braking torque is less than 10% and the effect of the brake disc temperature on gear walk is performed. The results reveal that a more negative friction slope may contribute to a more severe unstable gear walk, and reducing the braking pressure is an effective approach to avoid gear walk, which provides help for future braking system design.

建立了起落架多体动态刚柔耦合模型,以研究制动盘摩擦特性引起的齿轮行走不稳定性。在用实验结果验证模型后,进一步研究了起落架结构和制动系统参数对齿轮行走的影响。在上述因素中,制动盘摩擦系数与制动定子和转子相对速度的曲线斜率是对齿轮行走不稳定性影响最大的因素。相位轨迹分析证实,当多个因素的耦合导致系统呈现等效负阻尼趋势时,就会发生齿轮走行。为了考虑更现实的制动情况,采用了反向传播神经网络方法来描述制动盘摩擦系数的非线性行为。利用摩擦系数的现实非线性模型,预测制动扭矩的最大误差小于 10%,并研究了制动盘温度对齿轮行走的影响。结果表明,更负的摩擦斜率可能会导致更严重的不稳定走档,而降低制动压力是避免走档的有效方法,这为未来的制动系统设计提供了帮助。
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引用次数: 0
Semi-supervised remote sensing image scene classification with prototype-based consistency 基于原型一致性的半监督遥感图像场景分类
IF 5.7 1区 工程技术 Q1 ENGINEERING, AEROSPACE Pub Date : 2023-12-13 DOI: 10.1016/j.cja.2023.12.012
Yang LI, Zhang LI, Zi WANG, Kun WANG, Qifeng YU

Deep learning significantly improves the accuracy of remote sensing image scene classification, benefiting from the large-scale datasets. However, annotating the remote sensing images is time-consuming and even tough for experts. Deep neural networks trained using a few labeled samples usually generalize less to new unseen images. In this paper, we propose a semi-supervised approach for remote sensing image scene classification based on the prototype-based consistency, by exploring massive unlabeled images. To this end, we, first, propose a feature enhancement module to extract discriminative features. This is achieved by focusing the model on the foreground areas. Then, the prototype-based classifier is introduced to the framework, which is used to acquire consistent feature representations. We conduct a series of experiments on NWPU-RESISC45 and Aerial Image Dataset (AID). Our method improves the State-Of-The-Art (SOTA) method on NWPU-RESISC45 from 92.03% to 93.08% and on AID from 94.25% to 95.24% in terms of accuracy.

深度学习能显著提高遥感图像场景分类的准确性,并从大规模数据集中获益。然而,对遥感图像进行标注非常耗时,甚至对专家来说也很困难。使用少量标注样本训练的深度神经网络通常对新的未见图像的泛化程度较低。在本文中,我们提出了一种基于原型一致性的半监督遥感图像场景分类方法,通过探索大量未标记图像来实现。为此,我们首先提出了一个特征增强模块来提取辨别特征。这是通过将模型聚焦于前景区域来实现的。然后,在框架中引入基于原型的分类器,用于获取一致的特征表征。我们在 NWPU-RESISC45 和航空图像数据集 (AID) 上进行了一系列实验。我们的方法在 NWPU-RESISC45 上的准确率从 92.03% 提高到 93.08%,在 AID 上的准确率从 94.25% 提高到 95.24%。
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引用次数: 0
Gust response of an elasto-flexible morphing wing using fluid–structure interaction simulations 利用流固相互作用模拟弹性变形翼的阵风响应
IF 5.7 1区 工程技术 Q1 ENGINEERING, AEROSPACE Pub Date : 2023-12-13 DOI: 10.1016/j.cja.2023.12.017
Jonathan PFLÜGER, Christian BREITSAMTER

Small and micro unmanned aircraft are the focus of scientific interest due to their wide range of applications. They often operate in a highly unstable flight environment where the application of new morphing wing technologies offers the opportunity to improve flight characteristics. The investigated concept comprises port and starboard adjustable wings, and an adaptive elasto-flexible membrane serves as the lifting surface. The focus is on the benefits of the deforming membrane during the impact of a one-minus-cosine type gust. At a low Reynolds number of Re = 264000, the morphing wing model is investigated numerically by unsteady fluid–structure interaction simulations. First, the numerical results are validated by experimental data from force and moment, flow field, and deformation measurements. Second, with the rigid wing as the baseline, the flexible case is investigated, focusing on the advantages of the elastic membrane. For all configurations studied, the maximum amplitude of the lift coefficient under gust load shows good agreement between the experimental and numerical results. During the decay of the gust, they differ more the higher the aspect ratio of the wing. When considering the flow field, the main differences are due to the separation behavior on the upper side of the wing. The flow reattaches earlier in the experiments than in the simulations, which explains the higher lift values observed in the former. Only at one intermediate configuration does the lift amplitude of the rigid configuration exceeds that of the flexible by about 12%, with the elastic membrane resulting in a smaller and more uniform peak load, which is also evident in the wing loading and hence in the root bending moment.

小型和微型无人驾驶飞机应用广泛,是科学界关注的焦点。它们通常在高度不稳定的飞行环境中工作,而新型变形机翼技术的应用为改善其飞行特性提供了机会。所研究的概念包括左舷和右舷可调机翼,以及作为升力面的自适应弹性薄膜。重点是变形膜在一减余弦型阵风影响下的益处。在 Re = 264000 的低雷诺数条件下,通过非稳定流固耦合模拟对变形翼模型进行了数值研究。首先,通过力和力矩、流场和变形测量的实验数据验证了数值结果。其次,以刚性机翼为基准,研究了柔性情况,重点关注弹性膜的优势。对于所研究的所有配置,阵风载荷下升力系数的最大振幅在实验结果和数值结果之间显示出良好的一致性。在阵风衰减期间,机翼长宽比越大,两者的差异越大。在考虑流场时,主要差异是由于机翼上侧的分离行为造成的。实验中的气流比模拟中的气流更早重新附着,这也是前者升力值更高的原因。只有在一个中间构型上,刚性构型的升力振幅比弹性构型高出约 12%,弹性膜产生的峰值载荷更小、更均匀,这在机翼载荷中也很明显,因此在根部弯矩中也很明显。
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引用次数: 0
期刊
Chinese Journal of Aeronautics
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