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三维编织复合材料结构多尺度力学特性
Multi-Scale Mechanical Properties of Three-Dimensional Braided Composite Structures
罗海波;王谦;杨燕初;邬军;李涛;冯涛;何小辉;龚文韬; LUO Haibo;WANG Qian;YANG Yanchu;WU Jun;LI Tao;FENG Tao;HE Xiaohui;GONG Wentao;为了给临近空间工程应用提供依据,对三维编织预埋刺辊连接圆管结构进行了力学性能探索。首先,对三维编织单胞细观结构进行设计和分析,得到弹性模量和泊松比等基本力学参数。然后,对三维五向(3D5D)编织预埋刺辊连接复合材料圆管进行拉伸和压缩力学性能测试,分析影响承载力学性能的结构设计参数,讨论编织角、编织厚度和编织构型对圆管承载能力的影响因素。最后,通过损伤形貌分析圆管结构的失效机制,并利用扫描电镜观测并分析微观结构损伤机理。结果表明:在同样外径情况下,3D5D编织比三维全五向编织的拉伸失效载荷大;在同样编织构型和外径情况下,圆管壁越厚,压缩失效载荷越大。ϕ30t3-C圆管获得了最大的压缩失效载荷,损伤形貌表现为刺辊接头滑脱失效;ϕ30t2.5-T和ϕ25t3-T圆管均获得了较大的拉伸失效载荷,平均超过120 kN,失效形貌表现为刺辊接头拉脱与圆管端部纤维胀裂;ϕ30t3-T圆管拉伸平均失效载荷超过105 kN。研究结果可为临近空间浮空器结构轻质高强承载设计和飞行应用提供重要的科学依据。
The mechanical properties of three-dimensional(3D)braided pre-embedded licker-in connecting tubular structures were investigated to provide a basis for near-space engineering applications.First, the meso-structure of a 3D braided unit cell was designed and analyzed to obtain fundamental mechanical parameters, such as elastic modulus and Poisson's ratio. Subsequently, tensile and compressive mechanical tests were conducted on 3D five-directional(3D5D)braided composite tubes with pre-embedded licker-in connections. The structural design parameters influencing load-bearing performance were analyzed, including the effects of the braiding angle, thickness, and configuration on the tube's load capacity.Finally, the failure mechanisms of the tubular structures were examined through damage morphology analysis, and macroscopic structural damage mechanisms were investigated using scanning electron microscopy.The results indicate that under the same outer diameter, 3D5D braided tubes exhibit higher tensile failure loads than 3D5D fully braided tubes. For tubes with identical braiding configurations and outer diameter,the wall thickness enhances compressive failure load, with the φ30t3-C tube achieving the highest compressive failure load and the failure mode being manifested as licker-in joint slippage. Meanwhile, both the-φ25t3-T and φ30t2.5-T tubes demonstrate high failure loads, with average tensile loads exceeding 120 kN and the failure mode involves licker-in joint pull-out and fiber bursting at the tube ends. The φ 30t3-T tube exhibits an average tensile failure load of over 105 kN. The findings serve as an important sci-entific reference for light-weight, high-strength load-bearing design and flight applications of near-space aerostats.
协同区域导航的临地伪卫星网络几何构型规划
Ground-and Nearspace-Based Pseudolites Network Geometry Configuration Planning in Regional Navigation by Cooperation
曲艺;王生;冯慧;罗海波;刘强;李崔春; QU Yi;WANG Sheng;FENG Hui;LUO Haibo;LIU Qiang;LI Cuichun;为改善地基伪卫星和气球伪卫星开展协同区域导航应用的服务性能,提出一种临地协同伪卫星网络几何构型规划方法。首先,针对临地协同区域导航应用场景,设计了基于几何精度因子和水平精度因子的伪卫星网络几何构型性能评价指标;其次,分析了气球伪卫星的运动学特征和临近空间的环境风场特征,构建了主动调节飞行高度和利用环境风场的气球伪卫星轨迹调节策略;最后,提出了基于正余弦算法的伪卫星网络几何构型规划算法,讨论了规划算法的约束条件并开展了仿真验证。结果表明:所提算法能够充分利用环境风场随时空条件变化的特点,合理规划气球伪卫星的飞行轨迹,延长其服务时间,从而改善临地协同伪卫星网络的几何精度因子和水平精度因子,进而优化伪卫星网络的导航服务性能,为气球伪卫星在导航领域的应用提供了技术参考。
A nearspace-based cooperation pseudolite network geometry configuration planning algorithm was proposed to improve the regional navigation service performance provided by the cooperation of ground-and high altitude balloon(HAB)-based pseudolites. First, a pseudolite network geometry configuration performance indicator was designed based on geometric and horizontal dilations of precision in application scenarios of regional navigation by nearspace-based cooperation. Subsequently, the kinematic characteristics of HAB-based pseudolites and environmental wind field characteristics of nearspace were analyzed, and a HAB-based pseudolite trajectory adjustment strategy of actively changing flight altitudes and utilizing environmental wind field was constructed. Finally, a pseudolite network geometry configuration planning algorithm based on sine-cosine algorithm was proposed, with its constraints discussed and verified through simulations. The simulation results show that the proposed algorithm can effectively exploit the variation of environmental wind field with spatio-temporal conditions, and reasonably plan the flight trajectory of HAB-based pseudolites, thereby extending the service duration. It improves the geometric and horizontal accuracy factors of nearspace-based cooperation pseudolite networks, thereby optimizing the navigation service performance of pseudolite networks and providing technical references for the application of HAB-based pseudolites in navigation.
考虑渐进损伤的复合材料加筋圆柱壳后屈曲优化设计
Post-Buckling Optimization of Composite-Stiffened Cylindrical Shells Incorporating Progressive Damage
王悦;王志祥;李道奎; WANG Yue;WANG Zhixiang;LI Daokui;为探究轴压载荷下复合材料加筋圆柱壳结构的承载潜力和失效模式,开展了考虑渐进损伤的复合材料加筋圆柱壳结构后屈曲分析及优化设计。首先,基于显式动力学方法和Hashin失效准则,分析了复合材料加筋圆柱壳结构的极限载荷和失效模式。在此基础上,分析了蒙皮铺层顺序对3种典型复合材料加筋圆柱壳结构的极限载荷影响规律。进一步采用序列近似优化方法,分别获得了3种典型复合材料加筋圆柱壳优化结构。结果表明:轴压载荷下,复合材料横置六边形加筋圆柱壳结构在承载能力和承载效率方面均展现出显著优势,相比初始设计,其提升幅度分别为37.5%和31.8%;与其他2种构型相比,复合材料横置六边形加筋圆柱壳结构极限载荷分别提高10.6%和4.4%;轴压载荷下,纤维/基体相继损伤失效是加筋圆柱壳压溃破坏的主要机理。因此,需综合考虑材料损伤和结构稳定性进行后屈曲分析,获取复合材料加筋圆柱壳结构的极限载荷。
To explore the load-bearing potential and failure modes of composite-stiffened cylindrical shells under axial compression, post-buckling analysis and optimization design were conducted by incorporating progressive damage. The ultimate load and failure modes were analyzed using the explicit dynamics method and Hashin failure criterion. On this basis, the influence of skin layup sequence on the ultimate load of three typical composite stiffened cylindrical shells was investigated. Furthermore, the sequential approximate optimization method was adopted to obtain the optimized structures of the three typical composite-stiffened cylindrical shells. The results demonstrate that under axial compression, the composite transverse hexagonal stiffened cylindrical shell structure shows significant advantages in both load-bearing capacity and efficiency, with improvements of 37.5% and 31.8%, respectively, compared with the initial design, and an increase in ultimate load by 10.6% and 4.4%, respectively,with respect to the other two configurations. Under axial compression, the sequential damage and failure of fibers and matrices are the main mechanisms of crushing failure of stiffened cylindrical shells. Therefore, post-buckling analysis should be carried out by comprehensively considering material damage and structural stability to obtain the ultimate load of composite-stiffened cylindrical shells.
耐烧蚀高熵涂层制备、评估与优化设计研究进展
Research Progress on the Preparation, Evaluation, and Optimal Design of Ablation-Resistant High-Entropy Coatings
李慧东;袁晓静;刘浩宇;姜楠;张敏;许东升;罗伟蓬; LI Huidong;YUAN Xiaojing;LIU Haoyu;JIANG Nan;ZHANG Min;XU Dongsheng;LUO Weipeng;航天装备关键部件须经受高温高载及复杂环境的严苛考验,其热端部件的可靠服役性能一直是航天领域研究的热点问题之一。超高温高速气流冲刷、高能武器威胁造成的烧蚀等极端条件下,热防护涂层须具备稳定的高温服役能力。近年来,高熵材料凭借优异的机械性能、热稳定性和化学稳定性,备受航天材料领域关注。针对高超音速飞行器在长航时飞行中对典型结构件的耐烧蚀需求,分析了耐烧蚀高熵涂层设计、制备与评估进展;重点分析了多组元高熵材料的组分优选策略和热防护涂层的先进制备工艺,并探讨了其性能调控机制,为高性能耐烧蚀高熵涂层的制备与性能提升提供了参考。
The reliable service performance of hot-end components has long been a research focus in the aerospace field, as key components of aerospace equipment are subjected to rigorous tests under complex conditions involving high thermal and loads. Under extreme enviroments, such as high-thermal and high-speed gas flow erosion, and ablation caused by high-energy weapons, thermal protective coatings are required to maintain stable high-thermal service capabilities. In recent years, high-entropy materials, characterized by excellent mechanical properties, thermal and chemical stabilities, have attracted significant attention in the aerospace material field. Accordingly, the design, preparation, and evaluation progress of ablation-resistant high-entropy coatings were reviewed to address the need for ablation-resistant components of hypersonic vehicles in long-duration flights. The optimization strategies for multi-component high-entropy materials and advanced preparation processes for thermal protective coatings were analyzed, and the performance control machanisms were explored, providing support for the preparation and performance enhancement of high-performance ablation-resistant high-entropy coatings.
基于耗散伪应变能的NEPE固体推进剂疲劳损伤演化模型
Fatigue Damage Evolution Model for NEPE Solid Propellant Based on Dissipated Pseudo-Strain Energy
吴凡几;张文沁;张大鹏;雷勇军; WU Fanji;ZHANG Wenqin;ZHANG Dapeng;LEI Yongjun;针对长时间公路运输后高能硝酸酯增塑聚醚(nitrate ester plasticized polyether,NEPE)固体推进剂的疲劳损伤表征问题,开展了应力控制模式下的循环拉伸试验,采用耗散伪应变能作为NEPE固体推进剂疲劳损伤过程的损伤因子,将疲劳损伤演化过程视作是蠕变损伤、拉压疲劳损伤及断裂损伤进程的叠加,构建了NEPE固体推进剂疲劳损伤演化模型并开展参数分析。结果表明:NEPE固体推进剂在应力控制的循环载荷作用下会表现出明显的应变落后于应力的滞后特征,并伴随着能量耗散现象,所定义的损伤因子可以有效量化其损伤演化过程;疲劳损伤演化模型可以精确表征NEPE固体推进剂在循环加载时的损伤衰减增长、稳态增长和加速增长3个阶段;加载最大应力对疲劳损伤演化起决定性作用,加载最大应力降低时,损伤演化的主导因素会逐渐由蠕变损伤向拉压疲劳损伤转变。
Cyclic tensile tests were conducted under stress-controlled conditions to address the issue of fatigue damage characterization in high-energy nitrate ester plasticized polyether(NEPE)solid propellants after long-term highway transportation. The dissipated pseudo-strain energy was adopted as the damage factor for the fatigue damage process of NEPE solid propellants. The fatigue damage evolution process was regarded as a superposition of the damages from creep, tensile-compressive fatigue, and fracture. A fatigue damage evolution model for NEPE solid propellants was constructed, and parameter analyses were conducted. The results indicate that NEPE solid propellants exhibit a significant stress-strain hysteresis characteristic, with strain lagging behind stress under stress-controlled cyclic loading, accompanied by energy dissipation phenomena. The defined damage factor can effectively quantify the damage evolution process. The fatigue damage evolution model can precisely characterize the three growth stages of NEPE solid propellants under cyclic loading, namely decay, steady-state, and accelerated growth. The maximum loading stress plays a decisive role in fatigue damage evolution. When the maximum loading stress decreases, the dominant factor in damage evolution gradually shifts from creep damage to tensile-compressive fatigue damage.