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| 1 | 激光金属沉积TA15钛合金工字梁疲劳性能研究显示文摘激光金属沉积(LMD)是一种应用广泛的金属增材制造技术,可以快速成形复杂的结构件。以TA15钛合金粉末为原材料,采用激光金属沉积技术成形了TA15工字梁缩比件,进行了LMD TA15钛合金工字梁试样的疲劳试验和失效分析,研究了LMD TA15钛合金材料和结构的疲劳性能。对4件试样在应力比为0.06,载荷峰值为80%静力破坏载荷的交变载荷下进行四点弯曲疲劳试验,受成形缺陷影响,试样出现混合失效模式:两件试样无明显缺陷,裂纹形态为受拉缘条角裂纹,两件试样为内部气孔缺陷诱发失效,裂纹形态为受拉缘条半椭圆裂纹。起裂位置与缺陷和应力水平有关,存在明显的差异。为阐明试样疲劳失效行为,进行了有限元分析,获得起裂位置的应力水平,分析了缺陷和应力水平对疲劳寿命的影响。结果表明,缺陷是影响试样疲劳性能的主导因素,缺陷降低疲劳寿命50%以上,对于无明显缺陷试样,试样的疲劳行为受到应力水平控制。 | 吴斌 唐鼎承 贺小帆 王天帅 张鑫 李玉海 | 2022 | 稀有金属2022，46，5： | 5 |
| 2 | 增材制造三维点阵结构设计、优化与性能表征方法研究进展显示文摘增材制造技术与三维点阵结构技术是航空航天装备结构实现轻量化与多功能化的重要途径。针对增材制造三维点阵结构及其设计方法进行概述,重点介绍了增材制造三维点阵结构工程应用、轻质多功能三维点阵结构构型设计方法、三维点阵结构多尺度计算方法与拓扑优化方法、增材制造三维点阵结构性能评价表征方法等方面的研究现状与进展,对增材制造三维点阵结构在材料–结构–功能一体化设计方面的发展趋势进行了展望。 | 段晟昱 王潘丁 刘畅 赵则昂 周浩 张啸雨 雷红帅 郭旭 方岱宁 | 2022 | 航空制造技术2022，65，14： | 4 |
| 3 | In-situ observation and finite element analysis of fretting fatigue crack propagation behavior in 1045 steel显示文摘In this paper fretting fatigue crack behavior in 1045 steel is studied by in-situ observation and finite element analysis.in-situ fretting fatigue experiments are conducted to capture real-time fretting fatigue crack formation and propagation process.The fretting fatigue tests under different load conditions are carried out,then the lifetime and fracture surface are obtained.The crack propagation rates under different loading conditions are measured by in-situ observations.With in-situ observation,crack initiation location and direction are analyzed.Finite element model is used to calculate J-integral which then is applied to fitting with experimental crack growth rate,and establishing crack growth rate model.From fitted S-N curve,it turns out that smaller load ratio leads to higher lifetime.Crack initiates slightly below the point equivalent to line contact of the contact surface in different test conditions,and crack direction shows no obvious relationship with load parameters.The established crack growth rate model well agrees with the test results. | Qinan HAN Xusheng LEI Yue SU Shaoshi RUI Xianfeng MA Haitao CUI Huiji SHI | 2021 | Chinese Journal of Aeronautics2021，34，11： | 1 |
| 4 | A fatigue damage-cumulative model in peridynamics显示文摘While the present structural integrity evaluation method is based on the philosophy of assumed similitude, Fatigue and Damage Tolerance(F&DT) evaluations for next generation of air-vehicles require high-fidelity physical models within cyberspace. To serve the needs of F&DT evaluation in digital twin paradigm, a fatigue damage-cumulative model within peridynamic framework is proposed in this paper. Based on the concept of fatigue element block and damage accumulation law in form of Coffin-Manson relationship, the proposed model applies to both fatigue crack initiation and fatigue crack growth;fatigue crack growth rates under constant-amplitude and simple variable-amplitude block loading cases can be well predicted for three common structural materials without inputs of Paris law parameters. Additionally, the proposed model can also be easily extended to a probabilistic version;for verification, multiple-site-damage problems are simulated and the statistic nature of fatigue process in experiments can be well captured. In the end, main features of the proposed model are summarized, and distinctions from the other models are discussed. There may be a potential for the peridynamic damage-cumulative model proposed in this work to numerically predict fatigue problems in digital twin paradigm for future generations of aerospace vehicles. | Binchao LIU Rui BAO Fucheng SUI | 2021 | Chinese Journal of Aeronautics2021，34，2： | 1 |
| 5 | 基于双峰对数正态分布模型的DED-TA15钛合金DFR值估计方法显示文摘有效评价增材制造金属材料的疲劳强度,是增材制造技术应用于可重复使用飞行器主承力结构的关键。以DED-TA15钛合金为研究对象,基于3种应力水平下标准圆棒试件的成组疲劳试验结果,建立了描述DED-TA15钛合金疲劳寿命分布的双峰对数正态分布模型,采用EM算法,建立了双峰对数正态分布的参数估计方法;采用Bootstrap方法给出了指定置信度和可靠度要求的疲劳寿命计算方法。在军机DFR方法的基础上,给出了适用于DED-TA15钛合金的DFR值计算方法。与传统单峰对数正态分布相比,双峰对数正态分布更精确的描述了疲劳寿命分布,提高了高可靠度和高置信度要求下的疲劳寿命,DFR值也有所提高。该方法降低了因描述模型不精确导致的对设计许用应力的过度限制,有效的提高DED-TA15钛合金的使用潜力。 | 王天帅 贺小帆 王金宇 李玉海 | 2022 | 航空学报2022，43，3： | 1 |
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