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Ablation behavior of Hf-Zr-modified silicon-based ceramic coatings prepared by polymer derived ceramics and gaseous silicon infiltration 认领 引用
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作者 Lingxiang GUO Yaojun DONG +4 位作者 Yuqi WANG Shiwei HUANG Laura FELDMANN Ralf RIEDEL Jia SUN 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2026年第5期561-573,共13页
To improve the ablation resistance of C/C composite at temperatures exceeding 2000℃,a(Hf-Zr)C-SiC Ultra-High Temperature Ceramic(UHTC)coating was prepared by Polymer Derived Ceramics(PDCs)and Gaseous Silicon Infiltra... To improve the ablation resistance of C/C composite at temperatures exceeding 2000℃,a(Hf-Zr)C-SiC Ultra-High Temperature Ceramic(UHTC)coating was prepared by Polymer Derived Ceramics(PDCs)and Gaseous Silicon Infiltration(GSI).The linear ablation rate of the coated C/C composites was as low as 0.27μm/s,maintaining a level as low as 10-4mm/s.This low Rl is attributed to the formation of a well-bonded double-layered oxide scale with high thermal stability,consisting of an exterior SiO2glass layer and an interior Hf-Zr-Si-O complex oxide layer.Meanwhile,the dissipation of the residual Si and the C phases relieves heat accumulation,ensuring that the recorded surface temperature remains below 2000℃,thereby enhancing the ablation resistance.Additionally,a cyclic evolution of linear ablation rate was found,due to the alternating dominant role of oxidation and mechanical denudation on the coating during ablation.This study provides theoretical and experimental support for the long-term anti-ablation design of highly dense UHTC coatings. 展开更多
关键词 Ablation resistance C/C composites Gaseous silicon infiltration Multi-component carbide Polymer derived ceramics
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Multi-scale design and optimization for solid-lattice hybrid structures and their application to aerospace vehicle components 认领 引用 被引量：42
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作者 Chuang WANG Jihong ZHU +5 位作者 Manqiao WU Jie HOU Han ZHOU Lu MENG Chenyang LI Weihong ZHANG 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2021年第5期386-398,共13页
By integrating topology optimization and lattice-based optimization,a novel multi-scale design method is proposed to create solid-lattice hybrid structures and thus to improve the mechanical performance as well as red... By integrating topology optimization and lattice-based optimization,a novel multi-scale design method is proposed to create solid-lattice hybrid structures and thus to improve the mechanical performance as well as reduce the structural weight.To achieve this purpose,a two-step procedure is developed to design and optimize the innovative structures.Initially,the classical topology optimization is utilized to find the optimal material layout and primary load carrying paths.Afterwards,the solid-lattice hybrid structures are reconstructed using the finite element mesh based modeling method.And lattice-based optimization is performed to obtain the optimal crosssection area of the lattice structures.Finally,two typical aerospace structures are optimized to demonstrate the effectiveness of the proposed optimization framework.The numerical results are quite encouraging since the solid-lattice hybrid structures obtained by the presented approach show remarkably improved performance when compared with traditional designs. 展开更多
关键词 Aerospace vehicle components Lattice-based optimization Multi-scale Solid-lattice hybrid structure Topology optimization
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Relative Attitude and Position Estimation for Spacecraft from Multiple Geometric Features 认领 引用
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作者 Jianying Wang Haizhao Liang +2 位作者 Hui Liu Dong Ye Zhaowei Sun 《Journal of Harbin Institute of Technology(New Series)》 CAS 2016年第2期87-96,共10页
This paper investigates the pose and motion estimation problem using single camera measurement for spacecraft. The leader spacecraft of three-dimensional shape is observed by a calibrated camera fixed on the follower ... This paper investigates the pose and motion estimation problem using single camera measurement for spacecraft. The leader spacecraft of three-dimensional shape is observed by a calibrated camera fixed on the follower spacecraft. Based on dual numbers,an integrated observation model is proposed based on a combination of multiple geometric features including points,lines and circles,which can improve the robustness and accuracy of the estimation algorithm. A six-degree-of-freedom relative motion model is proposed by using the dual quaternion representation,in which the rotation-translation coupling effect due to the points deviating from the center of the mass is described. Employing the proposed observation model and dynamics model,an Extended Kalman Filter is presented to estimate the relative state between the two spacecraft. Numerical simulations are performed to evaluate the proposed approaches,showing the convergence of relative estimation errors and superior estimation performance. 展开更多
关键词 dual quaternion coupled dynamics vision-based estimation Kalman filtering
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Fluid-structure coupling characteristics of membrane under supersonic conditions 认领 引用
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作者 Zexuan YANG Jiandong HUANG +3 位作者 Chao YANG Yifan WANG Zhigang WU Bing Feng NG 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2026年第2期283-300,共18页
In order to enable wing morphing(e.g.change in camber or folds)without incurring additional weight to the aircraft,lightweight flexible materials such as membrane are needed.However,the research on fluid-structure cou... In order to enable wing morphing(e.g.change in camber or folds)without incurring additional weight to the aircraft,lightweight flexible materials such as membrane are needed.However,the research on fluid-structure coupling of membranes has mainly focused on parachutes in low-speed conditions,while that in supersonic flow conditions is lacking.Here,the degraded shell method is proposed to study membrane deformation by using shell element,which is more effective than using membrane elements directly.A fluid-structure interaction computational framework is proposed,whereby the aerodynamic module is composed of either the piston theory or computational fluid dynamics.A rectangular membrane of length 0.4 m and width 0.6 m is investigated in supersonic conditions.The characteristics of the limit cycle and steady deformation are analyzed,considering the effects of angle of attack and dynamic pressure.It is found that the structural response exhibits significant differences under various angles of attack.Furthermore,initial relaxation of membrane has significant influence on the structural deformation.Finally,the aeroelastic scaling method for membrane structures is derived,providing guidance for the design of wind tunnel models.This study provides a theoretical foundation for the analysis and application of membrane structures under supersonic conditions in future research. 展开更多
关键词 Aeroelasticity Fluid-structure interaction Initial relaxation Limit cycle oscillation Membranes Similarity criterion
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Influence of strain rate on grain refinement and texture evolution under complex shear stress conditions 认领 引用 被引量：3
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作者 Zhaocan Li Guoqin Wu +4 位作者 Jianmin Yu Jiebing Wang Jingjing Han Huiyong Cui Zhimin Zhang 《Journal of Magnesium and Alloys》 SCIE EI CAS CSCD 2023年第7期2558-2584,共27页
The effects of different complex shear stress conditions on grain refinement and texture evolution of Mg-13Gd-4Y-2Zn-0.5Zr alloy were investigated.With increasing strain rate,the average grain size of compression-shea... The effects of different complex shear stress conditions on grain refinement and texture evolution of Mg-13Gd-4Y-2Zn-0.5Zr alloy were investigated.With increasing strain rate,the average grain size of compression-shear(CS)and compression-torsion(CT)samples are decreased,and the grain size of dynamic recrystallization(DRX)grains is also decreased.This is because that the precipitation number ofβphases is increased,and the hindering effect on grain growth can be significantly enhanced.The DRX fractions of CS and CT samples are decreased with increased strain rate.The low DRX fraction at high strain rate is related to the insufficient time for grains to nucleate.The DRX process can be promoted by the PSN mechanism of second phases,and the grain growth can be restricted by the pinning effect.At the same time,the texture strength is enhanced as the strain rate increased.Besides,the kinking degree of lamellar long-period stacking ordered(LPSO)phases is increased.Under complex shear stress conditions,non-basal slip,especially pyramidal slip,is easily activated and the texture is deflected greatly.Compared with the CS samples,CT samples have smaller average grain size,higher DRX fraction,and lower texture strength for a certain strain rate.This is because that the equivalent stress of the CT sample is larger,the stress triaxiality is smaller,so more serious dislocations are piled up near grain boundaries and second phases.At the same time,since CT sample was sheared with torsion,the dislocation movement path can be called“rotational dislocation accumulation”,and the longer distribution path of the CT sample is generated,so more sub-grains and low-angle grain boundaries(LAGBs)are formed.Compared with the CS sample,more huge-angle grain boundaries(HAGBs)and DRX grains are formed from grain boundary to grain interior,so better grain refinement effect is achieved. 展开更多
关键词 Simple shear Compression-shear Compression-torsion Grain refinement Texture evolution ASB
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Efficient Inverse Analysis for Solving a Coupled Conduction,Convection and Radiation Problem Involving Non⁃gray Participating Media 认领 引用 被引量：2
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作者 HE Zheng CAO Zhenkun +2 位作者 CHENG Xiang CUI Miao LIU Kun 《Transactions of Nanjing University of Aeronautics and Astronautics》 EI CSCD 2024年第5期621-631,共11页
The presence of non-gray radiative properties in a reheating furnace’s medium that absorbs,emits,and involves non-gray creates more complex radiative heat transfer problems.Furthermore,it adds difficulty to solving t... The presence of non-gray radiative properties in a reheating furnace’s medium that absorbs,emits,and involves non-gray creates more complex radiative heat transfer problems.Furthermore,it adds difficulty to solving the coupled conduction,convection,and radiation problem,leading to suboptimal efficiency that fails to meet real-time control demands.To overcome this difficulty,comparable gray radiative properties of non-gray media are proposed and estimated by solving an inverse problem.However,the required iteration numbers by using a least-squares method are too many and resulted in a very low inverse efficiency.It is necessary to present an efficient method for the equivalence.The Levenberg-Marquardt algorithm is utilized to solve the inverse problem of coupled heat transfer,and the gray-equivalent radiative characteristics are successfully recovered.It is our intention that the issue of low inverse efficiency,which has been observed when the least-squares method is employed,will be resolved.To enhance the performance of the Levenberg-Marquardt algorithm,a modification is implemented for determining the damping factor.Detailed investigations are also conducted to evaluate its accuracy,stability of convergence,efficiency,and robustness of the algorithm.Subsequently,a comparison is made between the results achieved using each method. 展开更多
关键词 inverse problem coupled heat transfer problem Levenberg-Marquardt algorithm
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Comparison of Acoustic Emission Characteristics for C/SiC Composite Component Under Combination of Heating and Mechanical Loading 认领 引用 被引量：1
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作者 Zhi-Yong Tan Chang-Wan Min +2 位作者 Hong-Wei Wu Yu-Hai Qian Mei-Shuan Li 《Acta Metallurgica Sinica(English Letters)》 SCIE EI CAS CSCD 2017年第10期992-998,共7页
The acoustic emission（AE） characteristics of C/SiC composite component under various conditions were compared, with the purpose of identifying the possible damage and failure mechanism. During the process of the sin... The acoustic emission（AE） characteristics of C/SiC composite component under various conditions were compared, with the purpose of identifying the possible damage and failure mechanism. During the process of the single mechanical loading, the highest amplitude of the AE signal was less than 85 dB and the main damage forms of matrix cracking and interface debonding were involved. For the heating process, high-energy AE signals with an amplitude more than 85 dB were detected and fiber fracture mechanism was determined as well due to the thermal stress caused by the mismatch of the thermal expansion coefficient between the reinforced fiber and matrix. During the combination process of the heating and mechanical loading, it was concluded that the degree of damage was much severer than the simple superposition of damage produced by the individual mechanical loading and the individual heating process. 展开更多
关键词 C/SiC composite Damage and failure Heating Mechanical loading Acoustic emission
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Study of plasma-based stable and ultrawideband electromagnetic wave absorption for stealth application 认领 引用 被引量：1
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作者 Xuyang CHEN Fangfang SHEN +2 位作者 Yanming LIU Wei AI Xiaoping LI 《Plasma Science and Technology》 SCIE EI CAS CSCD 2018年第6期78-88,共11页
A plasma-based stable,ultra-wideband electromagnetic（EM） wave absorber structure is studied in this paper for stealth applications.The stability is maintained by a multi-layer structure with several plasma layers an... A plasma-based stable,ultra-wideband electromagnetic（EM） wave absorber structure is studied in this paper for stealth applications.The stability is maintained by a multi-layer structure with several plasma layers and dielectric layers distributed alternately.The plasma in each plasma layer is designed to be uniform,whereas it has a discrete nonuniform distribution from the overall view of the structure.The nonuniform distribution of the plasma is the key to obtaining ultra-wideband wave absorption.A discrete Epstein distribution model is put forward to constrain the nonuniform electron density of the plasma layers,by which the wave absorption range is extended to the ultra-wideband.Then,the scattering matrix method（SMM） is employed to analyze the electromagnetic reflection and absorption of the absorber structure.In the simulation,the validation of the proposed structure and model in ultra-wideband EM wave absorption is first illustrated by comparing the nonuniform plasma model with the uniform case.Then,the influence of various parameters on the EM wave reflection of the plasma are simulated and analyzed in detail,verifying the EM wave absorption performance of the absorber.The proposed structure and model are expected to be superior in some realistic applications,such as supersonic aircraft. 展开更多
关键词 plasma stealth ultra wideband Epstein profile scattering matrix method（SMM） electromagnetic（EM） wave absorption stable wave absorption
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Exploration on the Frontiers of Flexible and Deformable Cross-Domain Intelligent Flight 认领 引用 被引量：8
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作者 BAO Weimin LüXiaozhou +4 位作者 BAI Guanghui LI Xiaoping LIU Yanmin BAI Bowen SHI Yaoguang 《Aerospace China》 2021年第1期5-11,共7页
As human aeronautic and aerospace technology continues to prosper and the aerial flight space domain further expands,traditional fixed-shape air vehicles have been confronted with difficulties in satisfying complex mi... As human aeronautic and aerospace technology continues to prosper and the aerial flight space domain further expands,traditional fixed-shape air vehicles have been confronted with difficulties in satisfying complex missions in cross-domain scenarios.Owing to their flexible and deformable appearance,morphing air vehicles are expected to realize cross-domain intelligent flight,thus emerging as the most subversive strategic development trend and research focus in aeronautic and aerospace fields.This paper primarily reviews the research background and challenges of flexible and deformable cross-domain intelligent flight,proposing a corresponding research framework and mode as well as exploring the scientific issues and state-of-the-art solutions,where key research progress is introduced.The explorations covered in this paper also provide ideas and directions for the study of deformable cross-domain intelligent flight,which has critical scientific significance in promoting the study itself. 展开更多
关键词 cross-domain flight flexible intelligent deformable configuration
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Nonlinear flow control mechanism of two flexible flaps with fluid-structure interaction 认领 引用
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作者 Jiakun Han Chao Dong +1 位作者 Jian Zhang Gang Chen 《Acta Mechanica Sinica》 SCIE EI CAS CSCD 2025年第2期116-131,共16页
The flow control at low Reynolds numbers is one of the most promising technologies in the field of aerodynamics,and it is also an important source of the innovation for novel aircraft.In this study,a new way of nonlin... The flow control at low Reynolds numbers is one of the most promising technologies in the field of aerodynamics,and it is also an important source of the innovation for novel aircraft.In this study,a new way of nonlinear flow control by interaction between two flexible flaps is proposed,and their flow control mechanism is studied employing the self-constructed immersed boundary-lattice Boltzmann-finite element method(IB-LB-FEM).The effects of the difference in material properties and flap length between the two flexible flaps on the nonlinear flow control of the airfoil are discussed.It is suggested that the relationship between the deformation of the two flexible flaps and the evolution of the vortex under the fluid-structure interaction(FSI).It is shown that the upstream flexible flap plays a key role in the flow control of the two flexible flaps.The FSI effect of the upstream flexible flap will change the unsteady flow behind it and affect the deformation of the downstream flexible flap.Two flexible flaps with different material properties and different lengths will change their own FSI characteristics by the induced vortex,effectively suppressing the flow separation on the airfoil’s upper surface.The interaction of two flexible flaps plays an extremely important role in improving the autonomy and adjustability of flow control.The numerical results will provide a theoretical basis and technical guidance for the development and application of a new flap passive control technology. 展开更多
关键词 Nonlinear flow control Flexible flap Fluid-structure interaction Flow separation IB-LB-FEM
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Flexibly regulated electrochemiluminescence of all-inorganic perovskite CsPbBr3quantum dots through electron bridge to across interfaces between polar and non-polar solvents 认领 引用
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作者 Nan Hao Yu Qiu +4 位作者 Jinwen Lu Xu Han Yaqi Li Jing Qian Kun Wang 《Chinese Chemical Letters》 SCIE CAS CSCD 2021年第9期2861-2864,共4页
All-inorganic perovskite quantum dots(QDs)have attracted great interests due to its outstanding properties.But their poor stability in polar solvents seriously hampered wide applications in analytical chemistry.In thi... All-inorganic perovskite quantum dots(QDs)have attracted great interests due to its outstanding properties.But their poor stability in polar solvents seriously hampered wide applications in analytical chemistry.In this work,strong,stable and flexibly regulated the electrochemiluminescence(ECL)emission form CsPbBr(_3)QDs was successfully obtained and applied in the analysis of polar solvents through the unique structure of closed bipolar electrode(BPE).To demonstrate the feasibility,it was successfully used in the detection of tetracycline(Tc)aqueous solution.CsPbBr(_3)QDs was immersed into organic solution in anode microcell of closed BPE while Tc aqueous solution was added into cathode microcell.The two microcells were physically separated and would not interfere with each other.But the bio-recognition event between aptamer and Tc in cathode microcell would induce the ECL signal change in anode microcell through the electrons conducted by BPE as the bridge.The ECL emission can be flexibly regulated by environmental factors of both polar and non-polar solvents and the interface status of the BPE.Compared with traditional methods to overcome the intrinsic instability in polar medium,the reported method does not need any further surface modifications,has no limitations on the targets and can provide wide development space for further deep research,which may open a new direction for the ECL sensing of CsPbBr(_3)QDs. 展开更多
关键词 Electrochemiluminescence Perovskite Quantum dots Closed bipolar electrode Tetracycline
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Shedding vortex simulation method based on viscous compensation technology research 认领 引用
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作者 Hao Zhou Lei Wang +1 位作者 Zhang-Feng Huang Jing-Zhi Ren 《Chinese Physics B》 SCIE EI CAS CSCD 2022年第4期414-425,共12页
Owing to the influence of the viscosity of the flow field,the strength of the shedding vortex decreases gradually in the process of backward propagation.Large-scale vortexes constantly break up,forming smaller vortexe... Owing to the influence of the viscosity of the flow field,the strength of the shedding vortex decreases gradually in the process of backward propagation.Large-scale vortexes constantly break up,forming smaller vortexes.In engineering,when numerical simulation of vortex evolution process is carried out,a large grid is needed to be arranged in the area of outflow field far from the boundary layer in order to ensure the calculation efficiency.As a result,small scale vortexes at the far end of the flow field cannot be captured by the sparse grid in this region,resulting in the dissipation or even disappearance of vortexes.In this paper,the effect of grid scale is quantified and compared with the viscous effect through theoretical derivation.The theoretical relationship between the mesh viscosity and the original viscosity of the flow field is established,and the viscosity term in the turbulence model is modified.This method proves to be able to effectively improve the intensity of small-scale shedding vortexes at the far end of the flow field under the condition of sparse grid.The error between the simulation results and the results obtained by using fine mesh is greatly reduced,the calculation time is shortened,and the high-precision and efficient simulation of the flow field is realized. 展开更多
关键词 shedding vortex viscosity analysis numerical dissipation turbulence models
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Preparation Process and Optimization Design for Composites Rudderpost in the Long-Time High Temperature Environment 认领 引用
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作者 Li Jing Changwan Min +3 位作者 Geliang Sun Bin Fu Min Chen Zhanwei Cao 《Journal of Materials Science and Chemical Engineering》 2017年第1期69-75,共7页
Rudder is an important part for the glider aircraft. In order to satisfy the long-time high-velocity for the near-space vehicle in the atmosphere, the light- weight, high-stiffness and high-strength all-composites rud... Rudder is an important part for the glider aircraft. In order to satisfy the long-time high-velocity for the near-space vehicle in the atmosphere, the light- weight, high-stiffness and high-strength all-composites rudderpost is required urgently to be prepared. The all-composites rudderpost can keep high rudder efficiency in the high temperature environment. Based on the technique require-ment of high-performance composites rudder, a 3D C/SiC rudderpost was manufactured by the CVI-CMC-SiC [1] processes. It was found during rudderpost testing that the high-temperature mechanical properties decreased and had large discretization. The analysis of the failure mechanisms was conducted by FTA method to recognize the failure modes and main reasons for rudderpost abnormal fracture and to reproduce the fracture phenomenon, which could guide production company to modify their preparation process control. Then the modified processes were proved to be validated. And the stability and reliability of the production performances were improved. 展开更多
关键词 Rudderpost Preparation Process FTA Optimization Design Optimization Manufacture
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Simulation on Pyrolysis Products of Thermoset Phenolic Resin with Different Chemical Structure and Experimental Validation 认领 引用
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作者 Honglin Hu Lu Zhang +5 位作者 Liang Liu Liqin Jiang Na Huang Zhiyu Chen Ruilian Yu Zhizhong Meng 《材料科学与工程（中英文A版）》 2019年第4期162-168,共7页
The simulation on pyrolysis products of pure PF resin with different chemical structure was investigated and validated by pyrolysis gas-chromatography mass spectrometry(Py-GC/MS).The simulation of pyrolysis products o... The simulation on pyrolysis products of pure PF resin with different chemical structure was investigated and validated by pyrolysis gas-chromatography mass spectrometry(Py-GC/MS).The simulation of pyrolysis products of phenolic resin with different chemical structure was investigated by AMBER(Assisted Model Building with Energy Refinement)force field.The content of pyrolysis products phenol and cresol decreases with the increase of F/P(formaldehyde/phenol)value.The content of pyrolysis products dimethylphenol and trimethylphenol increases with the enhancement of F/P value.The crosslink density of phenolic mixture can be measured by the content of pyrolysis products dimethylphenol and trimethylphenol.Consequently,the results of simulation were validated by the Py-GC/MS experiment. 展开更多
关键词 Simulation pyrolysis products phenolic resin crosslink density
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Experimental investigation on aero-heating of rudder shaft within laminar/turbulent hypersonic boundary layers 认领 引用 被引量：16
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作者 Qiang LI Liang NIE +3 位作者 Kouli ZHANG Yu LI Suyu CHEN Guangsheng ZHU 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2019年第5期1215-1221,共7页
The aero-heating of the rudder shaft region of a hypersonic vehicle is very harsh, as the peak heat flux in this region can be even higher than that at the stagnation point. Therefore, studying the aero-heating of the... The aero-heating of the rudder shaft region of a hypersonic vehicle is very harsh, as the peak heat flux in this region can be even higher than that at the stagnation point. Therefore, studying the aero-heating of the rudder shaft is of great significance for designing the thermal protection system of the hypersonic vehicle. In the wind tunnel test of the aero-heating effect, we find that with the increase of the angle of attack of the lifting body model, the increasement of the heat flux of the rudder shaft is larger under laminar flow conditions than that under turbulent flow conditions. To understand this, we design a wind tunnel experiment to study the effect of laminarurbulent hypersonic boundary layers on the heat flux of the rudder shaft under the same wind tunnel freestream conditions. The experiment is carried out in the ?2 m shock tunnel(FD-14 A) affiliated to the China Aerodynamics Research and Development Center(CARDC). The laminar boundary layer on the model is triggered to a turbulent one by using vortex generators, which are 2 mm-high diamonds. The aero-heating of the rudder shaft(with the rudder) and the protuberance(without the rudder) are studied in both hypersonic laminar and turbulent boundary layers under the same freestream condition. The nominal Mach numbers are 10 and 12, and the unit Reynolds numbers are2.4 × 10~6 m-1 and 2.1 × 10~6 m-1. The angle of attack of the model is 20°, and the deflection angle of the rudder and the protuberance is 10°. The heat flux on the model surface is measured by thin film heat flux sensors, and the heat flux distribution along the center line of the lifting body model suggests that forced transition is achieved in the upstream of the rudder. The test results of the rudder shaft and the protuberance show that the heat flux of the rudder shaft is lower in the turbulent flow than that in the laminar flow, but the heat flux of the protuberance is the other way around,i.e., lower in the laminar flow than in the turbulent flow. The wind tunnel test results is also validated by numerical simulations. Our analysis suggests that this phenomenon is due to the difference of boundary layer velocities caused by different thickness of boundary layer between laminar and turbulent flows, as well as the restricted flow within the rudder gap. When the turbulent boundary layer is more than three times thicker than that of the laminar boundary layer, the heat flux of the rudder shaft under the laminar flow condition is higher than that under the turbulent flow condition. Discovery of this phenomenon has great importance for guiding the design of the thermal protection system for the rudder shaft of hypersonic vehicles. 展开更多
关键词 Heat flux Hypersonic boundary layer Rudder Shock tunnel Transition Vortex generator
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Progress in flight tests of hypersonic boundary layer transition 认领 引用 被引量：23
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作者 Guohua Tu Jianqiang Chen +7 位作者 Xianxu Yuan Qingtao Yang Maochang Duan Qiang Yang Yi Duan Xi Chen Bingbing Wan Xinghao Xiang 《Acta Mechanica Sinica》 SCIE EI CAS CSCD 2021年第11期1589-1609,I0001,共21页
Boundary layer transition(BLT)can cause a sharp rise in heat flux and skin friction,which can seriously affect the flight performance and safety of hypersonic flight vehicles.Therefore,the mechanism,prediction and con... Boundary layer transition(BLT)can cause a sharp rise in heat flux and skin friction,which can seriously affect the flight performance and safety of hypersonic flight vehicles.Therefore,the mechanism,prediction and control of transition have become important issues that must be dealt with for the development of advanced flight vehicles,and it is also a research hotspot of particular interest to major aerospace countries.Compared to other transition research approaches,model flight tests can better present the transition problems under real flight conditions,thus have been carried out extensively over the past 30 years.The United States,Germany,France,Australia,and other countries have carried out transition research based on flight tests,such as the Pegasus wing-glove crossflow transition and the Hypersonic Boundary Layer Transition(HyBOLT)transition control flight test of the United States,the joint research project of the Hypersonic International Flight Research and Experimentation-1(HIFiRE-1)circular cone and the HIFiRE-5 elliptic cone transition flight tests between the United States and Australia,the flight test of compression surface transition of the scramjet forebody(LEA)in France and so on.Although these flight tests suffered various setbacks,they still obtained valuable transition data.Recently,the United States is carrying out the concave-surface transition flight tests of Hypersonic Boundary Layer Transition(BOLT)and BOLT-II.Since its first model flight test mission for verification purpose launched successfully in 2015,several hypersonic BLT flight tests have been conducted by China Aerodynamics Research and Development Center(CARDC).The flight tests have measured valid transition data under flight conditions,obtained the transition front and its dynamical variation on blunt cones at various angles of attack and a lifting body Hypersonic Transition Research Vehicle(HyTRV).The crossflow traveling waves in high-altitude flight were measured for the first time,and our understanding of hypersonic BLT has been greatly improved. 展开更多
关键词 Hypersonic flow Boundary layer transition Flight test MF-1 HyTRV
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Integrated optimization design of smart morphing wing for accurate shape control 认领 引用 被引量：23
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作者 Xiaojun GU Kaike YANG +3 位作者 Manqiao WU Yahui ZHANG Jihong ZHU Weihong ZHANG 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2021年第1期135-147,共13页
Smart morphing wing, which is equipped with smart materials and able to change structural geometry adaptively, can further improve aerodynamic efficiency of aircraft. This paper presents a new integrated layout and to... Smart morphing wing, which is equipped with smart materials and able to change structural geometry adaptively, can further improve aerodynamic efficiency of aircraft. This paper presents a new integrated layout and topology optimization design for morphing wing driven by shape memory alloys(SMAs). By simultaneously optimizing the layout of smart actuators and topology of wing substrate, the ultimately determined configuration can achieve smooth, continuous and accurate geometric shape changes. In addition, aerodynamic analysis is carried out to compare smart morphing wing with traditional hinged airfoil. Finally, the optimized smart wing structure is constructed and tested to demonstrate and verify the morphing functionality. Application setbacks are also pointed out for further investigation. 展开更多
关键词 Layout optimization Morphing wing Shape memory alloy Shape morphing Topology optimization
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Non-intrusive reduced-order model for predicting transonic flow with varying geometries 认领 引用 被引量：9
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作者 Zhiwei SUN Chen WANG +4 位作者 Yu ZHENG Junqiang BAI Zheng LI Qiang XIA Qiujun FU 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2020年第2期508-519,共12页
A Non-Intrusive Reduced-Order Model(NIROM)based on Proper Orthogonal Decomposition(POD)has been proposed for predicting the flow fields of transonic airfoils with geometry parameters.To provide a better reduced-order ... A Non-Intrusive Reduced-Order Model(NIROM)based on Proper Orthogonal Decomposition(POD)has been proposed for predicting the flow fields of transonic airfoils with geometry parameters.To provide a better reduced-order subspace to approximate the real flow field,a domain decomposition method has been used to separate the hard-to-predict regions from the full field and POD has been adopted in the regions individually.An Artificial Neural Network(ANN)has replaced the Radial Basis Function(RBF)to interpolate the coefficients of the POD modes,aiming at improving the approximation accuracy of the NIROM for non-samples.When predicting the flow fields of transonic airfoils,the proposed NIROM has demonstrated a high performance. 展开更多
关键词 Artificial Neural Network Domain decomposition Geometric parameters Non-Intrusive Reduced-Order Model Proper Orthogonal Decomposition Transonic flow
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Numerical analysis on combustion characteristics of hybrid rocket motor with star-tube segmented grain 认领 引用 被引量：6
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作者 Chengen LI Zongwei WANG +4 位作者 Jin YANG Jinpeng JIANG Fan GONG Zhu LIU Yu SUN 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2023年第12期102-112,共11页
A method of star-tube combined segmented grain is proposed to improve the combustion performance of hybrid rocket motor.The star-tube combined segmented grain consists of a single-port star part and a single-port tube... A method of star-tube combined segmented grain is proposed to improve the combustion performance of hybrid rocket motor.The star-tube combined segmented grain consists of a single-port star part and a single-port tube part.A mid-chamber forms between the fore-grain and the aft-grain for better mixing effect.The single-port feature gives hybrid rocket motor several advantages,such as simple structure,high reliability,and variable combinations.This paper is mainly aimed at studying the combustion characteristics of hybrid rocket motor with star-tube segmented grain through three-dimensional steady simulations.Combustion performance of the motors with different segmented grain combinations,including fore-tube/aft-tube,fore-tube/aftstar,fore-star/aft-star and fore-star/aft-tube,is contrastively analyzed.The motor in this paper adopts polyethylene and 90%hydrogen peroxide as the propellants.Simulations reveal that segmented grain with different-type grain combinations could greatly change the flow field in the second half of the combustion chamber.Transformation of the flow field is beneficial to the mixing between the fuel and the oxidizer,and it could increase the fuel regression rate and the combustion efficiency.The turbulence effect of tube aft-grain is better than that of star aft-grain.Among the four segmented grain combinations,the combination of star fore-grain and tube aft-grain is the preferred method with optimal overall performance.This grain configuration could increase the regression rate of tube aft-grain to surpass that of star aft-grain in other combinations.Besides,hybrid rocket motor with this grain configuration achieves the highest combustion efficiency. 展开更多
关键词 Combustion performance Flow fields Fluid-solid coulping Hybrid rocket motor Star-tube segmented grain
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Scalability of 3D deterministic particle transport on the Intel MIC architecture 认领 引用 被引量：4
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作者 王庆林 刘杰 +1 位作者 龚春叶 邢座程 《Nuclear Science and Techniques》 SCIE CAS CSCD 2015年第5期88-97,共10页
The key to large-scale parallel solutions of deterministic particle transport problem is single-node computation performance. Hence, single-node computation is often parallelized on multi-core or many-core computer ar... The key to large-scale parallel solutions of deterministic particle transport problem is single-node computation performance. Hence, single-node computation is often parallelized on multi-core or many-core computer architectures. However, the number of on-chip cores grows quickly with the scale-down of feature size in semiconductor technology. In this paper, we present a scalability investigation of one energy group time-independent deterministic discrete ordinates neutron transport in 3D Cartesian geometry(Sweep3D) on Intel's Many Integrated Core(MIC) architecture, which can provide up to 62 cores with four hardware threads per core now and will own up to 72 in the future. The parallel programming model, Open MP, and vector intrinsic functions are used to exploit thread parallelism and vector parallelism for the discrete ordinates method, respectively. The results on a 57-core MIC coprocessor show that the implementation of Sweep3 D on MIC has good scalability in performance. In addition, the application of the Roofline model to assess the implementation and performance comparison between MIC and Tesla K20 C Graphics Processing Unit(GPU) are also reported. 展开更多
关键词 计算机体系结构 可扩展性 粒子输运 三维几何 英特尔 麦克风 离散坐标法 计算性能
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