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    Lightweighting of aerospace and aeronautical equipment: Challenges and perspectives
    Weihong ZHANG, Changhong TANG
    Acta Aeronautica et Astronautica Sinica    2024, 45 (5): 529965-529965.   DOI: 10.7527/S1000-6893.2023.29965
    Abstract760)   HTML90)    PDF(pc) (2009KB)(810)       Save

    Lightweight is a substantial theme in the research and development of aerospace and aeronautical equipment due to its decisive impact on the comprehensive performance and operational efficiency of the equipment. Over the past decades, a handful of innovative optimization design approaches, emerging high-performance materials, and revolutionary manufacturing technologies have been uninterruptedly developed, and the level of lightweighting in aerospace and aeronautical equipment has been significantly advanced. However, the increasing demands for comprehensive performance and multifunctionality of the next generation of equipment present serious challenges to existing lightweight design and manufacturing technologies. Therefore, with a particular emphasis on the layout design, electromechanical system design, materials and structures, high-performance manufacturing and assembly, this paper analyzes the posed challenges and future perspectives.

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    Review and prospect of research on scramjet
    Xiaoyong LIU, Mingfu WANG, Jianwen LIU, Xin REN, Xuan ZHANG
    Acta Aeronautica et Astronautica Sinica    2024, 45 (5): 529878-529878.   DOI: 10.7527/S1000-6893.2023.29878
    Abstract230)   HTML8)    PDF(pc) (6036KB)(402)       Save

    Since the 1950s, scramjet has been regarded as a goal of the hypersonic propulsion system in the aerospace field, and extensive research work has been conducted in both theory and practical technology. At the beginning of the 21st century, the United States made a series of technological breakthroughs close to practical applications, pushing the research and application of the scramjet technology to a new stage. This paper briefly describes the working principle of the scramjet, discusses the difficulties and latest progress in key technologies such as dual-mode working process, hypersonic compression flow, supersonic combustion, ultra-high temperature structure and thermal protection, ground test and numerical simulation, and expounds the understanding and suggestions on the development direction of key technologies such as wide speed range, repeatability, and higher Mach number of scramjet.

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    Disruptive technologies in aviation: Preliminary study
    Huitao FAN, Pengfei DUAN, Cheng YUAN
    Acta Aeronautica et Astronautica Sinica    2024, 45 (5): 529893-529893.   DOI: 10.7527/S1000-6893.2023.29893
    Abstract525)   HTML14)    PDF(pc) (5463KB)(785)       Save

    Disruptive technologies, with their innovative and destructive characteristics, have been leading the transformation of human mode of life and combat operations, and also playing an important role in the rise and fall of major powers and civilization evolution. In the history of aviation, numerous disruptive technologies have emerged to replace the previous technologies, profoundly influencing the process of aviation and shaping the basic pattern of today's air combat and civil aviation transportation. The world is currently at the crossroads of a new round of industrial and military revolution, and whether it is possible to identify, research, and industrialize various disruptive technologies including those in the aviation field is crucial for reshaping the future social form and military landscape. This article briefly illustrates the understanding of disruptive technologies from the aspects of concept, three significant characteristics, and identification and acquisition. The important influence of disruptive technologies on the previous three industrial revolutions is discussed, the significant changes brought by five typical aviation disruptive technologies in history presented, the important trend of the high-energy and intelligent compound development of aviation science and technology in the future analyzed, nine possible disruptive technologies and potential impacts in the four fields of material manufacturing, energy power, information electronics and cross-integration predicted, and suggestions for the development of disruptive technologies in aviation proposed. We expect that more future disruptive technologies in aviation will be initiated and developed by Chinese people.

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    Acta Aeronautica et Astronautica Sinica    2024, 45 (4): 0-.  
    Abstract84)      PDF(pc) (20823KB)(217)       Save
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    Key technologies in collaborative airframe⁃engine design for high performance fighters
    Haifeng WANG
    Acta Aeronautica et Astronautica Sinica    2024, 45 (5): 529978-529978.   DOI: 10.7527/S1000-6893.2024.29978
    Abstract229)   HTML12)    PDF(pc) (8792KB)(301)       Save

    The future operational environment imposes higher and more comprehensive requirements for the performance of fighters, calling for deeper integration between fighter airframe and engine and closer collaborative design during fighter research and development. Building on theories and practices for optimum airframe-engine integration in fighter design in the past decades, this paper proposes a collaborative airframe-engine design concept. Through an analysis of the combat requirements of Penetrating Counter Air (PCA) and other operational concepts, this paper then presents the essential capabilities of high performance fighters and looks into the requirements of future-oriented collaborative airframe-engine design. The key technologies concerning flight performance, stealth characteristics, flight control and aircraft energy are discussed, and the possible implementation approaches and suggestions for design and research are also provided.

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    Research progress on vibration monitoring and fault diagnosis for aero-engine
    Minghui HU, Jinji GAO, Zhinong JIANG, Weimin WANG, Limin ZOU, Tao ZHOU, Yunfeng FAN, Yue WANG, Jiaxin FENG, Chenyang LI
    Acta Aeronautica et Astronautica Sinica    2024, 45 (4): 630194-630194.   DOI: 10.7527/S1000-6893.2024.30194
    Abstract382)   HTML31)    PDF(pc) (3663KB)(235)       Save

    Aeroengine amalgamates state-of-the-art technologies across diverse domains, serving as a comprehensive manifestation of a nation’s prowess in science and industry. Frequent malfunctions occur due to its complicated structure and harsh service environment. Therefore, it is essential to employ prognostic and health management technology to provide crucial support for aviation safety and reliable operations. As vibration faults constitute a primary failure mode in aeroengine, this paper, grounded in this premise, systematically reviews and analyzes existing vibration monitoring and fault diagnosis for aviation engines both domestically and internationally. The analysis is categorized into three dimensions, covering the application of overall vibration monitoring and diagnostic systems, typical fault characteristics and diagnostic methods, and the overall vibration fault diagnostic technology, including dynamic analysis, signal processing techniques, and relevant technologies such as deep learning. Then, the problems and challenges faced by the existing vibration fault diagnosis of aeroengine are identified. Furthermore, future development goals are provided.

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    Acta Aeronautica et Astronautica Sinica    2024, 45 (5): 0-.  
    Abstract64)      PDF(pc) (48208KB)(175)       Save
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    Refined track initiation algorithm for partly resolvable group targets based on phase correlation
    WANG Cong, WANG Haipeng, XIONG Wei, HE You
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2017, 38 (4): 320299-320299.   DOI: 10.7527/S1000-6893.2016.0163
    Abstract1243)      PDF(pc) (1623KB)(811)       Save

    To deal with the problem of refined initiation in partly resolvable condition, a refined track initiation algorithm based on phase correlation is proposed in this paper. The radar measurements are preprocessed by using fast group segmentation based on coordinate mapping distance difference and pre-association based on group center point. To solve the problem of group topology alignment in low target detection probability condition, the phase correlation characteristics in image matching are then used in compensation and alignment of topological structure between adjacent times. Combined with the nearest neighbor method, a method by using virtual measurement and posterior decision is proposed to associate the group track refinedly, which can fill the missing tracks, add more correct ones, and at the same time suppress the false ones. The simulation results show that compared with the modified logic method and refined gray track initiation algorithm, the algorithm proposed has better performance in correct track initiation rate and suppression of false track, being robust to environment clutter and radar accuracy and more adaptable to target discovery probability.

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    Low altitude UAV traffic management:An introductory overview and proposal
    QUAN Quan, LI Gang, BAI Yiqin, FU Rao, LI Mengxin, KE Chenxu, CAI Kaiyuan
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2020, 41 (1): 23238-023238.   DOI: 10.7527/S1000-6893.2019.23238
    Abstract3610)      PDF(pc) (7884KB)(2295)       Save
    A large number of disorderly low-altitude UAVs may bring harm to ground facilities, public safety, piloted aerial vehicles/manned aerial vehicles, and so on. However, current air traffic management for civil aviation is not suitable for millions of UAVs in the future. In response to the challenge, new frameworks for low-altitude UAV air traffic management have been developed by many countries, which is a new thing in recent years. This paper focuses on the traffic management of low-altitude UAVs and overviews the related four aspects:the basic concept and current status quo of air traffic related to low-altitude UAV, the introduction to low-altitude UAV traffic management, the key technology of low-altitude UAV traffic management and the corresponding scientific issues of low-altitude UAV traffic management, hoping to contribute the healthy development of UAV industry.
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    Deformation modes and key technologies of aerodynamic layout design for morphing aircraft: Review
    Shusheng CHEN, Muliang JIA, Yanxu LIU, Zhenghong GAO, Xinghao XIANG
    Acta Aeronautica et Astronautica Sinica    2024, 45 (6): 629595-629595.   DOI: 10.7527/S1000-6893.2023.29595
    Abstract505)   HTML1)    PDF(pc) (19367KB)(341)       Save

    Morphing aircraft, capable of real-time shape deformation according to task requirements and flight conditions to achieve optimal flight performance, has emerged as a significant direction for the future development of aircraft. This paper reviews the research status of deformation modes and key technologies of aerodynamic layout design for morphing aircraft. Firstly, the development of morphing aircraft can be divided into two stages by the progression of time: the mechanical deformation stage and the flexible and muti-dimensional deformation stage. Then, this article summarizes morphing solutions for different parts of the aircraft, namely, the head deformation, wing deformation, power plant deformation, and combined deformation. It particularly explores the developmental history of various wing morphing schemes, discusses their applications in different aerodynamic configurations including variable sweep wing, variable forward sweep wing, folding wing, telescopic wing, oblique wing, continuous variable curvature wing, and analyzes their aerodynamic and stability characteristics, respectively. Next, the implementation objectives of morphing aircraft are summarized and divided into three types: single domain optimal variable configuration, multi-domain fusion variable configuration, and one vessel multi-energy variable configuration. Subsequently, compared with fixed shape aircraft, the key technical challenges in aerodynamic layout and overall coordination design, time-varying aerodynamic effect evaluation, aerodynamic layout scheme optimization, and multidisciplinary coupling design derived from the implementation of morphing aircraft are analyzed, with particular focus on the research progress and current status of dynamic aerodynamic calculation methods and aerodynamic optimization design technologies for morphing aircraft. Finally, the future research direction and development prospects of morphing technologies are envisioned. Targeting at the needs of wide velocity domain and large airspace flight, exploring new conceptual deformation methods that can improve the performance of multiple flight missions and establishing intelligent morphing design model and multidisciplinary strong coupling integrated design system will become important development trends.

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    Connotation and key research areas of new application code “Aerospace Mechanics” of the National Natural Science Foundation of China
    Meng CHEN, Rumeng LIU, Lifeng WANG, Yazhong LUO, Tao SUO, Chong PAN, Panfeng ZHANG, Guoxuan DONG, Haiyan HU
    Acta Aeronautica et Astronautica Sinica    2024, 45 (2): 129947-129947.   DOI: 10.7527/S1000-6893.2023.29947
    Abstract404)   HTML25)    PDF(pc) (3690KB)(461)       Save

    The development of aerospace, including the integration of space and universe, hypersonic flight, etc., has presented mechanics with new challenges and fundamental scientific problems. To enhance object-oriented fundamental research in mechanics to meet major national requirements, National Natural Science Foundation of China (NSFC) has introduced a new primary application code of “Aerospace Mechanics” within the mechanics discipline of the Department of Mathematical and Physical Sciences, based on recommendations from the 14th Five Year Plan Development Strategy Research Committee of the Mechanics Discipline. This article provides an overview of the background and process of introducing the application code “Aerospace Mechanics”. It also explains the connotation and funding scope, as well as key research areas. The goal is to assist researchers in understanding the establishment of aerospace mechanics code, as well as the research areas and directions they should focus on. It is expected to guide researchers to update their personal research fields and submit proposals in the natural science foundation information system, based on the sub-codes and research directions in aerospace mechanics.

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    Networking and control mechanism for low-altitude intelligent networks
    Qihui WU, Chao DONG, Ziye JIA, Can CUI, Simeng FENG, Fuhui ZHOU, Hua XIE
    Acta Aeronautica et Astronautica Sinica    2024, 45 (3): 28809-028809.   DOI: 10.7527/S1000-6893.2023.28809
    Abstract582)   HTML19)    PDF(pc) (6175KB)(333)       Save

    Low-Altitude Intelligent Network (LAIN), as a new type of intelligent network, relies on space-air-ground-sea facilities to constitute a digital intelligent network system. It is a key component of the space-air-ground integrated network, and can support the seamless and ubiquitous connections of the sixth generation communication technology and promote the development of intelligent network service from ground to low-altitude space. However, LAIN is still in the developing stage and faces the following key challenges: intractability of aerial control, severe spectrum interference, and multi-dimensional resource limitation. This article focuses on the issues of LAIN architecture and safety control, including the current development status of low-altitude network and its significance for industrial technology transformation. Then, from the perspective of spectrum resources, network resources, and airspace resource management, the recent related works are analyzed. Furthermore, we analyze the key technologies such as low-altitude aircraft air-ground spectrum sharing, sensing, transmission, computing networking coverage, low-altitude airspace intelligent supervision, and point out future development directions. Finally, an application demonstration of LAIN is proposed, aiming to satisfy the significant requirements for efficient operation and safety in low-altitude airspace, and providing the theoretical basis as well as technology for the further development of the next generation space-air-ground integrated network.

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    Research methods for whole aeroengine vibration and their engineering application
    Xiangdong GE, Fayong WU, Yongquan LIU, Zhongyan AN, Baodong QIAO, Qiang GAO, Tianlong QIN, Xiaoyang ZHOU
    Acta Aeronautica et Astronautica Sinica    2024, 45 (4): 628353-628353.   DOI: 10.7527/S1000-6893.2023.28353
    Abstract421)   HTML12)    PDF(pc) (13899KB)(301)       Save

    To address the difficulty in feature traceability of whole aeroengine vibration, this paper proposes a research method for vibration feature traceability based on dynamic experiments of whole aeroengines and parts, with the study of typical vibration mutation feature traceability of an aeroengine as an example. This method firstly reveals the dynamic properties of the engine and deep features of typical phenomena by dynamic experiments of the whole aeroengine and parts, and then traces to the dynamic and structural causes of vibration features through comprehensive analysis. Properties of supporting dynamic stiffness of the stator and modal characteristics of the whole aeroengine are obtained by experimental study on supporting dynamic stiffness of the whole stator casing and modal characteristics of the whole aeroengine. The experimental study on the dynamic properties and modality of full speed rotors reveals the imbalance excitation and elastic line changing rule of rotors with centrifugal load, and the modal properties of the rotor joint interface with different mechanical parameters. Holographic vibration measurement of the rotor bearing block under working conditions of the whole aeroengine and that of the rotor based on the blade tip interval of the engine show the changing rule of the transient characteristics of the classical vibration feature, support point vibration modal, vortex motion of the rotor and primary phase spots. As found from comprehensive study and judgment, the vibration mutation characteristic of the aeroengine results from the rotor imbalance excitation status mutation caused by the change in the joint interface of the rotor. The study on the rotor balance technique based on this mechanism is conducted and the result shows that the vibration mutation properties of multiple aeroengines are effectively suppressed, further proving the correctness of this tracing method.

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    Technical status and development of electric vertical take⁃off and landing aircraft
    Jinghui DENG
    Acta Aeronautica et Astronautica Sinica    2024, 45 (5): 529937-529937.   DOI: 10.7527/S1000-6893.2023.29937
    Abstract133)   HTML10)    PDF(pc) (7735KB)(115)       Save

    The development of electric Vertical Take-off and Landing (eVTOL) aircraft is greatly promoted for the advances in battery and motor technologies and the application of distributed electric propulsion system. In this paper, the advantages and disadvantages of different eVTOL configurations and their application scenarios are summarized, and a comprehensive comparison between eVTOL and conventional fuel aircraft is made in terms of performance, noise and cost. The interaction noise by rotors and rotor-wing is more prominent for eVTOL, but the electric propulsion rotor system with low tip speed and large rotor solidity greatly reduces its noise level (about a reduction of 15 dB). Lithium-ion batteries are the main energy source for current and future eVTOL. The advanced battery material system, integrated design of battery-structure and excellent battery management system are effective ways to improve the energy density and energy security of the whole aircraft in the future. The redundant manipulation of eVTOL increases the difficulty of flight control system design, but improves the safety of the whole aircraft at the same time. Fault reconstruction and collaborative control are new challenges faced by eVTOL. A wide variety of configurations and novel design features such as high voltage power, electric propulsion, flight-by-wire flight system and electric actuation are proposed for eVTOLs. In the absence of flight test data, the system-based method is the main method for safety design of eVTOL.

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    Kriging surrogate model and its application to design optimization: A review of recent progress
    HAN Zhonghua
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2016, 37 (11): 3197-3225.   DOI: 10.7527/S1000-6893.2016.0083
    Abstract11429)      PDF(pc) (9181KB)(6714)       Save

    Over the past two decades, surrogate modeling has received much attention from the researchers in the area of aerospace science and engineering due to its capability of greatly improving the efficiency of design optimization when high-fidelity numerical analysis is employed. Design optimization via surrogate models is intensively researched and eventually leads to a new type of optimization algorithm which is called surrogate-based optimization (SBO). Among the available surrogate models, such as polynomial response surface model, radial-basis functions, artificial neutral network, support-vector regression, multivariate interpolation or regression, and polynomial chaos expansion, Kriging model is the most representative surrogate model which has great potential in engineering design and optimization. In the context of aircraft design, this paper reviews the theory, algorithm and recent progress for researches on the Kriging surrogate model. First, the fundamental theory and algorithm of Kriging model are briefly reviewed and the experience about how to improve the robustness and efficiency is presented. Second, three major breakthroughs of Kriging model in recent years are reviewed, including gradient-enhanced Kriging, CoKriging and hierarchical Kriging. Third, the optimization mechanism and framework of surrogate-based optimization using Kriging model are discussed. In the meanwhile, the concept of infill-sampling criterion and sub optimization is presented. Five infill-sampling criteria as well as the dedicated constraint handling methods are described. Furthermore, the newly developed local EI (expected improvement) method and termination criteria for SBO are introduced. Fourth, a number of test cases including benchmark optimization problems as well as aerodynamic and multidisciplinary design optimization problems are given to demonstrate the excellent performance and great potential of the surrogate-based optimization using Kriging model. At last, the key challenges as well as future directions about the theory, algorithm and applications are discussed.

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    ESTIMATION OF THE MAXIMUM INSTANTANEOUS DISTORTION WITH CORRELATED FLUCTUATION PRESSURES
    Liang De-wang;Zhang Shi-ying
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    1992, 13 (7): 427-430.  
    Abstract1321)      PDF(pc) (225KB)(504)       Save
    The predicting formula of maximum instantaneous distortion are given in this paper. The comparison between estimated values and experimental results shows that the accuracy of estimation of the maximum value can be improved by considering the correlations between fluctuating pressures. The average relative error of the estimation for parameter (Kmax-Kss) can be reduced from 19.96% to 11.84%, and that for(K-Kss)and δK are respectively reduced from 28.16% to 12.33%, and from 11.37% to 5.43%, with consideration of the correlation between fluctuating pressures. The effects of the correlation coefficient between fluctuating pressures on the estimation of the maximum values are discussed in this paper. When the mean correlation coefficient, defined in this paper, is less than 0.1, at different condition the relative error of estimated values are less than 3%, the maximum value of instantaneous distortion can be estimated by an assumption of uncorrelated fluctuation pressures.
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    Development trend of navigation guidance and control technology for new generation aircraft
    Weiping YANG
    Acta Aeronautica et Astronautica Sinica    2024, 45 (5): 529720-529720.   DOI: 10.7527/S1000-6893.2024.29720
    Abstract104)   HTML2)    PDF(pc) (5554KB)(108)       Save

    This paper systematically sorts out the development status of aviation navigation guidance and control technology at home and abroad, and analyzes the existing gaps and reasons through comparisons in terms of demand traction, principal mechanism, product realization and application services. Under the background of systematic coordinated operation supported by aviation aircraft, the requirements for networking, systematization and intelligence are taken as the technical development goals, and the future development priorities and program routes of navigation guidance and control technology are proposed in five aspects: supporting new quality combat concepts, high-precision autonomous navigation, multibody cooperative aircraft control, research and development of new generation core devices, and unified architecture of next generation aircraft control management. Action suggestions are finally put forward at the two levels of technology and management to guide the effective combination of China’s advantageous innovation resources. Facing the needs of future equipment development, this study can provide an important reference for promoting national defense science and technology towards high-quality development.

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    Energy-optimal in orbit mission planning for agile remote sensing satellites
    ZHAO Lin, WANG Shuo, HAO Yong, LIU Yuan
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2017, 38 (6): 320654-320654.   DOI: 10.7527/S1000-6893.2016.0298
    Abstract1227)      PDF(pc) (6326KB)(1345)       Save

    A new hybrid algorithm combining pseudospectral method and genetic algorithm is presented in this work to solve the in orbit autonomous mission planning problem for the agile remote sensing satellite at multiple discrete observation points. The problem is broken into space resource scheduling problem and continuous optimal control problem based on the coupling of attitude motion equations. This algorithm, according to the space resource scheduling model built based on the travelling salesman problem (TSP) model, encodes the observation sequence and the relative observation time by a two-dimensional real coding structure, and calculates the observation sequence and the observation time by the genetic algorithm. The time optimal control problem in judging the observation time feasibility and the minimal energy consumption in attitude maneuvering are considered as the continuous optimal control problem, which is then solved by Gauss pseudospectral method based on Gauss pseudospectral costate mapping theorem. A comparative simulation test is carried out for the simple genetic algorithm and the proposed algorithm. The simulation results show that the energy consumption obtained by the proposed algorithm is reduced by 60% compared with that obtained by the simple genetic algorithm under typical simulation conditions.

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    Air combat intelligent decision-making method based on self-play and deep reinforcement learning
    Shengzhe SHAN, Weiwei ZHANG
    Acta Aeronautica et Astronautica Sinica    2024, 45 (4): 328723-328723.   DOI: 10.7527/S1000-6893.2023.28723
    Abstract342)   HTML8)    PDF(pc) (3500KB)(259)       Save

    Air combat is an important element in the three-dimensional nature of war, and intelligent air combat has become a hotspot and focus of research in the military field both domestically and internationally. Deep reinforcement learning is an important technological approach to achieving air combat intelligence. To address the challenge of constructing high-level opponents in single agent training method, a self-play based air combat agent training method is proposed, and a visualization research platform is built to develop a decision-making agent for close-range air combat. The field knowledge of pilots is embedded in the design process of the agent’s observation, action, and reward, training the agent to convergence. Simulation experiments show that the air combat tactics of agent gradually improves by self-play training, achieving a win rate of over 70% against the decision making by single agent training and the emerging of the strategies similar to human “single/double loop” tactics.

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    3D printed continuous fiber-reinforced composites: State of the art and perspectives
    CHEN Xiangming, YAO Liaojun, GUO Licheng, SUN Yi
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2021, 42 (10): 524787-524787.   DOI: 10.7527/S1000-6893.2020.24787
    Abstract3278)   HTML194)    PDF(pc) (15830KB)(2025)       Save
    Three-Dimensional(3D) printing, also termed as Additive Manufacturing (AM), has experienced significant development in the last several years. This advanced technology has the potential to promote new revolution in high-end equipment manufacturing, and has been widely used in aerospace, marine, electronic and biomedical engineering. Fiber reinforced composites can offer significant advantages over metals, for their excellent mechanical properties, weight saving potential, good resistance to corrosion and fatigue, design tailorability, etc. AM of fiber-reinforced composites can promote AM into a robust manufacturing paradigm and make great possibility for customization, automatic fabrication and flexibility in designing high performance components with complicated geometries at relatively low cost and time. 3D printed continuous fiber-reinforced composites therefore have got great attention in the last several years. This paper provides a critical review on the mechanical properties and performance of 3D printed continuous fiber-reinforced composites. Specifically, a thorough discussion on the effects of printing process parameters on the performance of 3D printed composites has been carefully provided in the first part of this paper. The mechanical properties and damage mechanisms of 3D printed composites under various loading conditions are subsequently discussed and summarized. The corresponding models and methods for stiffness and strength prediction of 3D printed composites are introduced in the third part. Future research directions and desirable objectives are also discussed.
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