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| 1 | A survey on numerical simulations of drag and heat reduction mechanism in supersonic/hypersonic flows显示文摘Along with the survey on experimental investigations drawing attention to the drag and heat reduction mechanism, the authors simultaneously focus on the recent advances of numerical simulations on the schemes applied to supersonic/hypersonic vehicles. The CFD study has evolved as an irreplaceable method in scheme evaluation and aircraft optimization. Similar to our previous experimental survey, the advances in drag and heat reduction schemes are reviewed by similar kinds of mechanism in this article, namely the forward-facing cavity, the opposing jet, the aerospike, the energy deposition and their combinational configurations. This review article puts an emphatic eye on the flow conditions, numerical methods, novel schemes and analytical conclusions given in the simulations. Further, the multi-objective design optimization concept has also been illustrated due to the observable advantages of using CFD over experimental method, especially those performances conducted in drag reduction and thermal protection practice, and this would possess reference value in the design of aircraft system. | Xiwan SUN Wei HUANG Min OU Ruirui ZHANG Shibin LI | 2019 | Chinese Journal of Aeronautics2019，32，4： | 12 |
| 2 | Bolt insertion damage and mechanical behaviors investigation of CFRP/CFRP interference fit bolted joints显示文摘Interference fit has advantages in improving fatigue behaviors of composite bolted joints,however, interference fit bolt insertion tends to cause damages in laminates weakening joint mechanical properties. Therefore, an experimental study was conducted to investigate bolt insertion damages of Carbon Fiber Reinforced Polymer(CFRP)/CFRP interference fit bolted joints.Mechanical behaviors of joints were also evaluated experimentally under both quasi-static loads and cyclic loads. Scanning Electron Microscope(SEM) and high-resolution X-ray micro-CT scan were used to examine micro damages in laminates. Damage and failure behaviors of joints were characterized. The results demonstrated that the hole entrance in upper laminate and the laminate boundary near the hole wall were the most critical regions for damages during bolt insertions. However, the influence of those damages on quasi-static failure loads and fatigue failure modes of joints was minimal. Delamination and matrix cracking occurred first in laminates following fiber and matrix fracture in quasi-static tensile tests. Interference fit could improve the fatigue resistance of the laminate hole, however, the bolt seemed to suffer a more critical local fatigue loading condition.This paper can contribute to composite structure designs, especially in understanding damage and failure behaviors of composite bolted joints. | Yangjie ZUO Ting YUE Ruisong JIANG Zengqiang CAO Liu YANG | 2022 | Chinese Journal of Aeronautics2022，35，9： | 3 |
| 3 | A novel surrogate modeling strategy of the mechanical properties of 3D braided composites显示文摘In this paper,a surrogate-based modeling methodology is developed and presented to predict the elastic properties of three dimensional(3 D)four-directional braided composites.Using this approach,the prediction process becomes feasible with only a limited number of training points.The surrogate models constructed using Finite Element(FE)method and Diffuse Approximation,reduce the computational time and cost for preparing experimental samples.In the FE model,multiscale method is applied to couple the computations of elastic properties at microscale and mesoscale.Subsequently,a parametric study is performed to analyze the effects of the three design parameters on the elastic properties.Satisfactory results are obtained via the surrogatebased modeling predictions,which are compared with the experimental measurements.Moreover,the predictions obtained from surrogate models concur well with the FE predictions.This study orients a new direction for predicting the mechanical properties based on surrogate models which can effectively reduce the sample preparation cost and computational efforts. | Zeyi LIU Yuliang HOU Qiaoli ZHAO Cheng LI | 2020 | Chinese Journal of Aeronautics2020，33，10： | 2 |
| 4 | Ultraviolet 3D digital image correlation applied for deformation measurement in thermal testing with infrared quartz lamps显示文摘In thermal-structural testing of hypersonic materials and structures,deformation measurement on the front surface of an object directly heated by quartz lamps is highly necessary and very challenging.This work describes a novel front-surface high-temperature deformation measurement technique,which adopts ultraviolet 3D digital image correlation(UV 3D-DIC)to observe and measure the high-temperature deformation fields on front surfaces directly heated by quartz lamps.Compared with existing blue light DIC techniques,the established UV 3D-DIC,which combines UV CCD camera,active UV illumination and bandpass filter imaging,can effectively suppress the strong disturbing light emitted by the quartz lamps and the heated sample itself during heating process.Two experiments were carried out to verify the robustness and accuracy of the developed technique:(1)direct observation of front surfaces of a hypersonic thermal structure sample heated from room temperature to 1050℃,and(2)front-surface thermal stain and coefficient of thermal expansion(CTE)measurement of an Inconel 718 sample up to 800℃.The well matched strain and CTE results with literature data show that UV 3D-DIC system is an effective technique for front-surface deformation measurement and has great potential in characterizing deformation response of hypersonic materials and structures subjected to transient aerodynamic heating. | Yali DONG Jiaqing ZHAO Bing PAN | 2020 | Chinese Journal of Aeronautics2020，33，3： | 2 |
| 5 | Numerical exploration on the thermal invasion characteristics of two typical gap-cavity structures subjected to hypersonic airflow显示文摘In this paper,numerical investigation of hypersonic gas flow over two typical gap-cavity structures is carried out using all-speed preconditioned density-based solver.Such structures filled with porous seal in the gap are often present at the joint locations of control surfaces of the hypersonic vehicles.Single-domain approach is adopted to integrate the governing equations for both porous and fluid regions.The basic thermal invasion characteristic is first illustrated using the maze gap-cavity structure without sealing.Then,the influence of seal filling depth on the thermal invasion characteristic is investigated for the structure with sealing.Finally,a comparison of thermal invasion characteristics between maze and straight gap-cavity structures is performed to examine the influence of gap bending.Results show that the main source of hot airflow invading into the gap is from the millimeter scale gas layer within the boundary layer.And the invasion characteristic presents approximate stationary behavior.A primary vortex occurs in the gap adjacent to the leeward wall,which is ascribed to the impinging effect between the separate boundary flow and the windward wall.This effect is also the main driving force of thermal invasion.A treatment of filling the seal in certain depth inside the gap can significantly reduce the thermal load of seal and maintain an acceptable level of the invading mass flow rate.Additionally,it is found that the gap bending exerts a limited block effect on the thermal invasion without sealing,and this effect can be ignored with sealing.These results can provide a reference for optimizing the seal gap-cavity structure configuration. | Zhenhuan LI Xinlin XIA Xiaolei LI Chuang SUN | 2020 | Chinese Journal of Aeronautics2020，33，6： | 1 |
| 6 | Investigation of stress distribution and damage behavior caused by forced installation of a composite bolted joint with a hole-location error显示文摘In this paper,the influence of forced installation caused by a hole-location error on the 3D stress distribution and damage of a composite bolted joint is investigated.An analytical model of stress distributed on composite holes is promoted,in view of non-uniform extrusion caused by forced installation.At first,non-uniform extrusion of the hole edge caused by forced installation is analyzed.According to the contact state,expression of hole deformation is given.Then,based on Hertz theory,the maximum extrusion load is obtained with help of deformation expression.By constructing an elastic foundation beam model,3D stress distributed on a hole could be analyzed according to the extrusion load.Then,stress distribution predicted by the above analytical method is compared with that provided by FE considering composite damage.Finally,a forced installation experiment is carried out to analyze the damage distribution of the joint.Results show that a central-symmetrically distributed stress is introduced by the hole-location error.With an increment of the error,strength of composite decreases due to extrusion damage.Therefore,stress presents a concave distribution on the hole.As the hole-location error exceeding 3%,stress decreases gradually due to failure of composite.Damage of holes does not exhibit a centrosymmetric distribution.Serious damage is mainly distributed on the entrance of the hole at the lower sheet. | Chinan LIU Yuan LI Yi CHENG An’an ZHAO Kunpeng DU Yue SHI Ximing LI Hui CHENG | 2024 | Chinese Journal of Aeronautics2024，37，1： | 0 |
| 7 | Micro-mechanical model for predicting the elasto-plastic behavior of composites based on secant formulation method显示文摘To predict the Elasto-Plastic Behaviors(EPBs)of aligned inclusions reinforced composites,this paper develops an interpolative Mori-Tanaka/Double-Inclusion(MT-DI)homogenization model with the secant formulation,and gives the numerical implementation algorithms of the developed MT-DI model with the secant formulation.The Finite Element(FE)homogenization method is implemented to provide the 'exact' EPBs of the composites and thus validate the MT-DI model with the secant formulation.The MT-DI model with the 2 nd-order secant formulation is validated to provide the more accurate predictions,while the MT-DI model with the 1 st-order secant formulation always gives the stiffer predictions.The results show that using the macro-stress and macrostrain as the inputs,the MT-DI model with the secant formulation gives the identical predictions.The predictions of the MT-DI model with the secant formulation vary between those of the MT and DI models with the secant formulation.Meanwhile,the MT-DI model with the secant formulation does not predict the accurate EPBs for the phases of the composites. | Junhao LIANG Xinhai HE Wenlong TIAN | 2021 | Chinese Journal of Aeronautics2021，34，1： | 0 |
| 8 | 多再入工况下一体化热防护系统拓扑优化设计显示文摘一体化热防护系统(integrated thermal protection system,ITPS)需要同时满足承载与隔热的需求.以波纹夹芯方案的ITPS为例,这需要其连接结构具有较高的力学性能与较低的热导率.而再入环境的工况恶劣,如何合理地设计连接结构是ITPS性能提升的关键.为解决这一问题,综合考虑了再入过程中气动热载荷最大时刻和气动压力载荷最大时刻对应的两种极端工况,以应变能和净传热速率的最小化作为目标函数,将质量作为约束条件,对ITPS的连接结构进行了拓扑优化.随后对拓扑优化得到的构型重新建模并进行了热力耦合分析.结果表明,拓扑优化得到的连接结构与文献中的初始波纹夹芯构型和单一工况下拓扑优化得到的构型相比,上面板的最大位移、下面板的温度和质量均有效降低.由于材料用量的减少和结构复杂度的增加,连接结构在应力水平上有所增加,但仍满足使用需求.这表明了考虑多再入工况的拓扑优化策略可以有效提升ITPS的刚度与隔热能力,缓解结构的热短路效应.随着增材制造等相关技术的发展,拓扑优化在ITPS的连接结构以及其他的热结构设计中具有广阔的前景. | 邓通相 匡格平 胡兆财 唐光武 杨强 高博 | 2023 | 应用数学和力学2023，44，11： | 0 |
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