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Development and applications of airport avian radar: Review CHEN Weishi, HUANG Yifeng, CHEN Xiaolong, LU Xianfeng, ZHANG Jie ACTA AERONAUTICAET ASTRONAUTICA SINICA    2022, 43 (1): 24758-024758.   DOI: 10.7527/S1000-6893.2020.24758 Abstract （1784）   HTML （37）    PDF（pc） （36464KB）（483）       Knowledge map    Save Avian radar has become an important bird situation observation tool in airport bird strike avoidance. The origin of avian radar technology is first introduced, followed by analysis of the target characteristics of flying birds in terms of the target echo amplitude, flight speed, flight height, trajectory characteristics and micro-Doppler characteristics. Four typical airport avian radar systems, including Merlin radar, Accipiter radar, Robin radar and Aveillant radar, and the research status of the domestic avian radar technology are then introduced. Key radar technologies such as antenna, radar waveform, target detection and tracking, target recognition and classification are analyzed, and the performance of typical avian radar systems compared. In addition, the applications of avian radar are discussed with respect to the fusion of radar and photoelectric technologies, the linkage of bird detection and repellent, and the bird information analysis. Conclusions are finally drawn and prospects are made. Reference | Related Articles | Metrics

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Current status and prospect of overseas research on aeronautical fatigue SUN Xiasheng, SU Shaopu, SUN Hanbin, DONG Dengke ACTA AERONAUTICAET ASTRONAUTICA SINICA    2021, 42 (5): 524791-524791.   DOI: 10.7527/S1000-6893.2020.24791 Abstract （1330）   HTML （57）    PDF（pc） （17003KB）（1169）       Knowledge map    Save Fatigue is one of the key factors affecting the performance of aircraft in research or service. In this article, firstly, the aeronautical accidents caused by fatigue were quoted as clues to state the evolution of structural strength design concept and research situation at each specific period. Meanwhile, international aeronautical fatigue research and their significant development as well as the future developing directions in areas since 21 century has been reviewed and evaluated in the aspects of structural long-life design, fatigue analysis approaches and tools, full-scale structural fatigue testing technology, structural health monitoring and life extension of aging aircraft. Conclusively, considering the current problems and potential development directions, the challenges resisting the realization of high requirement on the long life, lightweight and high reliability of future aircraft design were pointed out on four topics:aeronautical fatigue on evaluation basic research, design and application research, testing evaluation and digital technology, which provides technical materials for the development of aeronautical fatigue. Reference | Related Articles | Metrics

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Technical development of variable camber wing: Review WANG Binwen, YANG Yu, QIAN Zhansen, WANG Zhigang, LYU Shuaishuai, SUN Xiasheng ACTA AERONAUTICAET ASTRONAUTICA SINICA    2022, 43 (1): 24943-024943.   DOI: 10.7527/S1000-6893.2020.24943 Abstract （1327）   HTML （80）    PDF（pc） （36682KB）（1131）       Knowledge map    Save The Variable Camber Wing(VCW) remains a research hot-spot as it aims to ensure that aircraft acquire optimal aerodynamic efficiency in various flight conditions. The benefits brought by VCWs are firstly presented, and the demands of VCWs from different types of aircraft are classified and thoroughly described. The developing process of VCWs in the past decades are then reviewed in terms of the leading edge and the trailing edge, respectively, and the current major obstacles in application are listed. Further research directions are finally suggested. Reference | Related Articles | Metrics

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Real-time dense small object detection algorithm for UAV based on improved YOLOv5 ACTA AERONAUTICAET ASTRONAUTICA SINICA    DOI: 10.7527/S1000-6893.2022.27106 Accepted: 09 May 2022

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Development of aircraft structural fatigue and structural integrity: Review CUI Degang, BAO Rui, ZHANG Rui, LIU Binchao, OUYANG Tian ACTA AERONAUTICAET ASTRONAUTICA SINICA    2021, 42 (5): 524394-524394.   DOI: 10.7527/S1000-6893.2020.24394 Abstract （1268）   HTML （31）    PDF（pc） （9154KB）（495）       Knowledge map    Save As the main factor affecting the safety of structures, the structural design and strength analysis of aircraft has developed from static strength design to safety-life design and damage-tolerance design, and further to the durability concept and aircraft structural integrity, during which the design and technique philosophies keep improving and undergo qualitative changes. However, the present understanding towards structural integrity in engineering practice is limited to the level of product development and testing, hindering its significance at a further level. This paper first introduces the development of aircraft structural design from static strength design to structural integrity design, the basic concept of aircraft structural integrity, and the main contents and key points of Aircraft Structural Integrity Program (ASIP). Moreover, the promotional transition from the traditional specification for analysis and testing within the design phase to the present one for process control and management within the whole product lifecycle is addressed by elucidating the "Five Tasks". Finally, two typical successful ASIP applications involving the design, verification and maintenance of aircraft structural integrity are presented as examples. Through the basic concepts and development of the main design philosophies, this paper shows the qualitative change of aircraft structural safety strategies from limited application within the design and development phase to thorough application for process control within the full lifecycle, and points out the trend that structural integrity philosophies are developing from experiment-based systematic approaches to digital ones. Reference | Related Articles | Metrics

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Binary convolutional neural network: Review DING Wenrui, LIU Chunlei, LI Yue, ZHANG Baochang ACTA AERONAUTICAET ASTRONAUTICA SINICA    2021, 42 (6): 24504-024504.   DOI: 10.7527/S1000-6893.2020.24504 Abstract （1204）   HTML （13）    PDF（pc） （6618KB）（255）       Knowledge map    Save In recent years, Binary Convolutional Neural Networks (BNNs) have attracted much attention owing to their low storage and high computational efficiency. However, the mismatch between forward and backward quantization results in a huge performance gap between the BNN and the full-precision convolutional neural network, affecting the deployment of the BNN on resource-constrained platforms. Researchers have proposed a series of algorithms and training methods to reduce the performance gap during the binarization process, thereby promoting the application of BNNs to embedded portable devices. This paper makes a comprehensive review of BNNs, mainly from the perspectives of improving network representative capabilities and fully exploring the network training potential. Specifically, improving network representative capabilities includes the design of the binary quantization method and structure design, while fully exploring the network training potential involves loss function design and the training strategy. Finally, we discuss the performance of BNNs in different tasks and hardware platforms, and summarize the challenges in future research. Reference | Related Articles | Metrics

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Parallel HVDC electric power system for more-electric-aircraft: State of the art and key technologies ZHANG Zhuoran, XU Yanwu, YU Li, LI Jincai, XIA Yiwen ACTA AERONAUTICAET ASTRONAUTICA SINICA    2021, 42 (6): 624069-624069.   DOI: 10.7527/S1000-6893.2020.24069 Abstract （1164）   HTML （25）    PDF（pc） （17725KB）（710）       Knowledge map    Save The integration of onboard secondary energy is gradually realized by the More Electric Aircraft (MEA), improving the efficiency, reliability, and safety of energy utilization. The High-Voltage DC (HVDC) power supply system with outstanding advantages such as lightweight, low loss, and high reliability can, in principle, realize easier parallel operation of the Electric Power System (EPS), enabling the expansion of the power supply capacity in a multi-engine/multi-generator layout, and hence uninterrupted power supply. In addition, both the electric power quality and reliability of the EPS are improved. The characteristics and advantages of the HVDC EPS are analyzed in this paper, followed by a summary of the research status and the key technical issues of the HVDC parallel EPS. A dual-channel HVDC parallel EPS based on novel doubly salient brushless DC generators is proposed and implemented to achieve current sharing control of the system, and the dynamic responses during sudden load changes, paralleling in, and splitting out are examined. The research has proved that the HVDC parallel EPS provides good steady-state accuracy and dynamic performance, exhibiting important value in the MEA or All Electric Aircraft (AEA) applications. The dynamic behaviors, the modeling method, and the protection logic of the HVDC parallel EPS still require further research. Reference | Related Articles | Metrics

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Comprehensive evaluation of ergonomics of civil aircraft cockpit display touch control system DONG Lei, XIANG Chenyang, ZHAO Changxiao, DANG Xiangjun, SHI Chunlei ACTA AERONAUTICAET ASTRONAUTICA SINICA    2021, 42 (6): 624053-624053.   DOI: 10.7527/S1000-6893.2020.24053 Abstract （1079）   HTML （9）    PDF（pc） （6240KB）（443）       Knowledge map    Save Touch control technology will be extensively applied in civil aircraft cockpits in the future; however, no ergonomic evaluation system and evaluation method for the display touch system of civil aircraft cockpits exist currently. Aiming at this problem, we first sort out the current standards and norms related to the touch control system of civil aircraft cockpit displays, and propose the man-machine ergonomic evaluation index system of civil aircraft cockpit display touch control systems in combination with the human factor investigation items in airworthiness regulations. Secondly, considering the fuzziness and grayness of the evaluation indexes, we improve the traditional fuzzy hierarchy comprehensive evaluation algorithm from two directions of data aggregation processing and index weight determination based on the gray correlation analysis. The expert reliability coefficient modified rank matrix is constructed to realize the quantitative description of expert cognitive characteristics, and the man-machine ergonomic comprehensive evaluation model of civil aircraft cockpit display touch control systems is established. Finally, combined with the ergonomic evaluation test cases of civil aircraft cockpit displays and touch systems under the project ACROSS, the influence of the configuration strategy of cockpit displays and touch systems on the ergonomic efficiency of the system is analyzed, and the applicability and rationality of the evaluation system and evaluation method are verified. Reference | Related Articles | Metrics

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Technical innovations of the Tianwen-1 Mission ZHANG Rongqiao, GENG Yan, SUN Zezhou, LI Dong, ZHONG Wenan, LI Haitao, CUI Xiaofeng, LIU Jianjun ACTA AERONAUTICAET ASTRONAUTICA SINICA    2022, 43 (3): 626689-626689.   DOI: 10.7527/S1000-6893.2021.26689 Abstract （1078）   HTML （76）    PDF（pc） （2192KB）（683）       Knowledge map    Save Tianwen-1 is the first mission in the world to achieve the three goals of Mars orbiting, landing and roving in one mission, and has made some key-technology breakthroughs. The mission objectives and flight progress are introduced, and eight kinds of innovation achievements and the main technical breakthroughs are comprehensively summarized in this paper. Specifically, the key technologies include the overall design of Mars orbiting, landing and roving objectives strongly coupled, multi-trajectory launch of Earth escape orbit, interplanetary flight and Mars capture, Mars enter, descent and landing, solutions adaptive to Martian harsh environment, 400-million-kilometer communication, advanced payloads of remote sensing and patrol detection, and Mars environmental modeling and ground validation. The complete success of the mission has made China become one of the advanced countries in the field of deep space exploration. Reference | Related Articles | Metrics

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An automatic parallel and implicit assembly method for overset grid GUO Yongheng, JIANG Xiong, XIAO Zhongyun, WANG Ziwei, LU Fengshun ACTA AERONAUTICAET ASTRONAUTICA SINICA    2021, 42 (6): 124369-124369.   DOI: 10.7527/S1000-6893.2020.24369 Abstract （1067）   HTML （2）    PDF（pc） （25273KB）（474）       Knowledge map    Save Overset grid assembly is one of the key technologies dealing with multi-body motion in the field of computational fluid dynamics. Existing implicit assembly methods usually have problems of complicated geometric analysis and low assembly efficiency caused by the search operation among all nodes. To address these issues, a highly automated overset grid implicit assembly method is proposed. First, based on fast algorithms such as the covariance analysis and box cutting, the calculation of wall distance is decoupled from the existence judgment of contribution units, realizing automatic identification of the dynamic overset relationship of grid groups. Secondly, combined with the set analysis, a parallel automatic digging algorithm is designed. Finally, a quick query method is used to establish the interpolation relationship between overset cells and denoting cells. In view of the implemented parallel overset grid implicit assembly library, a five-sphere component is used to verify the accuracy of the automatic digging scheme, and the accuracy of the interpolation relationship between the overset cells and denoting cells is also verified by the Wing-Pylon-Finned Store(WPFS) model. Reference | Related Articles | Metrics

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Development status, challenges and trends of strength technology for hypersonic vehicles SUN Cong ACTA AERONAUTICAET ASTRONAUTICA SINICA    2022, 43 (6): 527590-527590.   DOI: 10.7527/S1000-6893.2022.27590 Abstract （1030）   HTML （286）    PDF（pc） （26942KB）（897）       Knowledge map    Save As a type of hi-tech weapon, hypersonic vehicle plays an important strategic role in national security and benefits. It has now become a research hotspot in the field of aerospace, and the competition is becoming increasingly fierce all over the world. Advanced material and structure design is a basic key technology to support the development of hypersonic vehicle. The strength of materials and structures in extremely severe service environments is still a key issue restricting the development of this type of aircraft. This paper reviews the structure strength problems and evolution characteristics in the field of hypersonic vehicles in the past few decades. Combined with the current vehicle model development demand and technology development trend, this paper analyzes the current situation and shortcomings of structure strength technology in supporting the development of hypersonic vehicles and discusses the new requirements, new characteristics and new methods of strength problems in this field in the future. Finally, the future development direction in the field of hypersonic vehicle structure strength is proposed after summarization. Reference | Related Articles | Metrics

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Evaluation and optimization method for power systems of distributed electric propulsion aircraft LEI Tao, KONG Delin, WANG Runlong, LI Weilin, ZHANG Xiaobin ACTA AERONAUTICAET ASTRONAUTICA SINICA    2021, 42 (6): 624047-624047.   DOI: 10.7527/S1000-6893.2020.24047 Abstract （1013）   HTML （13）    PDF（pc） （18873KB）（432）       Knowledge map    Save Taking the electric propulsion aircraft power system as the research object, we conduct the following research. The power flow calculation method for the power system is used to analyze the distributed electric propulsion aircraft electrical system with the high-voltage DC power supply system; the energy flow relationship between the electrical system in the stable operating state and the open circuit fault state is simulated; the influence of the DC voltage level on the electrical system is analyzed. A complete distributed electric propulsion aircraft power system simulation model is built. The advantages and disadvantages of pure electric propulsion and turbo electric propulsion architectures in terms of three evaluation indicators (propulsion power, propulsion efficiency, and range) are comparatively analyzed. A parametric model of typical components of the power system is established and then optimized by the signomial geometric programming algorithm. The optimized trade-off relationship between the power system quality and fuel consumption rate with the traditional turbo propulsion and turbo-electric propulsion architectures is compared. The research results provide a valuable forward design method for the design of hybrid propulsion systems for electric propulsion aircraft. Reference | Related Articles | Metrics

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Damage mechanism and corrosion resistance of 38CrMoAl nitrided steel under impact load ZHANG Zhuzhu, CHEN Yueliang, YAO Niankui, BIAN Guixue, ZHANG Yong, ZHANG Yangguang ACTA AERONAUTICAET ASTRONAUTICA SINICA    2021, 42 (5): 524215-524215.   DOI: 10.7527/S1000-6893.2020.24215 Abstract （1010）   HTML （13）    PDF（pc） （10820KB）（280）       Knowledge map    Save To study the damage mechanism and corrosion resistance of 38CrMoAl steel materials under the combined effect of impact load and marine environment erosion, we subjected 38CrMoAl steel materials before and after nitriding to impact loading tests and corrosion performance tests. The studies found that the nitrided 38CrMoAl steel material has strong positive strain rate sensitivity at high strain rates. Under the impact load, cracks appeared on the nitriding layer on the surface of the test piece, accompanied by partial brittle peeling of the nitriding layer, with all crack lengths of 500-700 μm. The cracks only propagated in the nitriding layer without extending to the inside of the metal matrix. Electrochemical test results show that the nitriding treatment significantly improves the corrosion resistance of the material, with its self-corrosion potential shifting from -726.24 mV to -174.42 mV, compared with the non-nitrided specimen. However, due to the damage on the surface nitriding layer after the impact loading, part of the metal matrix is exposed, forming a potential difference with the undamaged surface, which in turn causes strong galvanic corrosion. The scanning Kelvin probe test showed that the anode-cathode potential difference and potential dispersion degree on the surface of nitriding parts are increased compared with the non-nitriding parts, and the nitriding parts are more prone to local corrosion. Impact loading changes the surface state of the nitrided layer, making the surface corrosion of the material more uneven. Finally, the salt spray test was carried out on the test piece, and the results were consistent with those of the electrochemical test. In the maintenance of the carrier-based aircraft, attention should be paid to the crack inspection of the nitrided layer of the impacted part, and corresponding anti-corrosion treatments should be done. Reference | Related Articles | Metrics

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Review of distributed hybrid electric propulsion aircraft technology ZHU Bingjie, YANG Xixiang, ZONG Jian'an, DENG Xiaolong ACTA AERONAUTICAET ASTRONAUTICA SINICA    2022, 43 (7): 25556-025556.   DOI: 10.7527/S1000-6893.2021.25556 Abstract （998）   HTML （22）    PDF（pc） （14513KB）（567）       Knowledge map    Save Distributed hybrid electric propulsion system has great potential and advantage in development of general electric aviation. By the optimization of secondary power system, hybrid electric technology can not only heighten the utilization efficiency of energy, but also satisfied the distributed arrangement of power system for higher propulsive efficiency. The paper firstly summarized the current major types of electric aircraft, reviewed the history background of distributed electric propulsion aircraft. Then, the research status of distributed hybrid electric propulsion aircraft technology is summarized, this part mainly discussed the distributed layout technology of propulsion system, type-selection design of hybrid electric propulsion system, modeling and energy management of hybrid electric propulsion system, and so on. The key technologies of distributed hybrid electric propulsion at home and abroad are discussed fully. Eventually, combined with the research of the team, the difficult point problems and solutions of distributed hybrid electric propulsion aircraft are discussed in detail, including dynamic management strategy of energy based on complex system optimization control, optimal energy distribution prediction model driven by historical big data, and principle prototype designing of distributed hybrid electric propulsion system. The main content of this paper clarify the design thoughts and analysis method for distributed hybrid electric propulsion system and energy arrangement, which can provide references for the research of electric propulsion aircraft technology. Reference | Related Articles | Metrics

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Uncalibrated visual servo of space robots performing on-orbit assembly alignment task JIA Qingxuan, DUAN Jiaqi, CHEN Gang ACTA AERONAUTICAET ASTRONAUTICA SINICA    2021, 42 (6): 424063-424063.   DOI: 10.7527/S1000-6893.2020.24063 Abstract （932）   HTML （9）    PDF（pc） （5436KB）（173）       Knowledge map    Save In the on-orbit assembly process of space robots, the relationship between their "hands" and "eyes" cannot be effectively calibrated, and the inertial parameters of the robot and the object being operated are variable, which may lead to assembly failure. To solve this problem, we design a depth estimator based on the traditional uncalibrated visual servo. It can estimate the depth value of the target feature online using the measurement data of the robot and the image motion. A sliding mode controller is designed in the space robot joint control ring to control the robot joint motion in real time, and the system error is corrected according to the feedback image information to complete alignment and tracking. Finally, the effectiveness of the method is verified by simulation. The uncalibrated visual servo alignment method proposed in this paper can free the space robot from the complicated calibration program, thereby overcoming the influence of uncertain inertial parameters on the assembly accuracy and improving the robustness of "hand-eye coordination" to ensure successful completion of on-orbit assembly tasks of the space robot in complex space environments. Reference | Related Articles | Metrics

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Kriging-assisted constrained differential evolution algorithm YE Nianhui, LONG Teng, WU Yufei, TANG Yifan, SHI Renhe ACTA AERONAUTICAET ASTRONAUTICA SINICA    2021, 42 (6): 324580-324580.   DOI: 10.7527/S1000-6893.2020.24580 Abstract （918）   HTML （9）    PDF（pc） （7522KB）（217）       Knowledge map    Save High-fidelity analysis models have been widely used in modern design, significantly increasing the computational budget of engineering design optimization. To reduce the computational cost, researchers have paid extensive attention to Surrogate Assisted Evolutionary Algorithms (SAEAs) recently. A Kriging-assisted Constrained Differential Evolution algorithm (KRG-CDE) is developed in this study to improve the efficiency of SAEAs in solving constrained optimization problems. Based on constraint improvement probability and optimality fitness, an improved feasibility rule is tailored to enhance the potential optimality and feasibility of the infill sample points. Moreover, the global exploration and local exploitation capacity of the KRG-CDE are balanced according to the population improvement. The proposed method is tested on several standard benchmark problems and compared with global and local surrogate-assisted differential evolution and (μ+λ)-constrained differential evolution to verify its optimization performance. The comparison results illustrate that the KRG-CDE outperforms the competitors in terms of efficiency, convergence, and robustness. Finally, the KRG-CDE is successfully applied to an all-electric propulsion satellite multidisciplinary design optimization problem, demonstrating the practicality and effectiveness of the proposed KRG-CDE in engineering practices. Reference | Related Articles | Metrics

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Research progress and prospect of fatigue and structural integrity for aeronautical industry in China WANG Binwen, CHEN Xianmin, SU Yunlai, SUN Hanbin, YANG Yu, FAN Junling ACTA AERONAUTICAET ASTRONAUTICA SINICA    2021, 42 (5): 524651-524651.   DOI: 10.7527/S1000-6893.2020.24651 Abstract （880）   HTML （51）    PDF（pc） （27012KB）（1055）       Knowledge map    Save In China, as the improvement of aeronautical industry, fatigue and structural integrity become one of the key problems that affect the life, safety and reliability of aircraft structures. After years of hard-working, aircraft design philosophy evolved gradually from static strength to safe-life, and now to fatigue and structural integrity as a guide. Aircraft structural integrity program has been implemented successfully into structural development for several new types. The service life, reliability and economy of the new generation aircraft structure have been improved significantly. However, with the improvement of aeronautical technology and the development requirements for new aircrafts, many new problems emerged in this area. From the perspective of aeronautical industry, this paper combs the progress and main achievements of aeronautical fatigue research in China, and focuses on the research status and engineering applications in the aspects of material/structure/process, analysis and evaluation method, fatigue test technology and service life management since 2000. Finally, some aeronautical fatigue research directions need to be focused on were proposed in order to provide reference for the further development of domestic aeronautical structures. Reference | Related Articles | Metrics

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Abnormal energy risk criteria of large civil airplanes in approach and landing LU Zhidong, ZHANG Shuguang, DAI Runzhi, HUANG Mingyuan ACTA AERONAUTICAET ASTRONAUTICA SINICA    2021, 42 (6): 624132-624132.   DOI: 10.7527/S1000-6893.2020.24132 Abstract （859）   HTML （8）    PDF（pc） （9769KB）（148）       Knowledge map    Save Statistics of large civil airplanes reveal that the accident rate is the highest in the approach and landing phases and that most of these accidents exhibit initial abnormal energy status which evolves into one of the end accident types such as loss of control, hard landing, tail strike, runway overrun, or go-around failure. This paper summarizes and focuses on the above five types of end accident types, establishing a generic flight simulation tool for large civil airplanes. Stochastic simulation and correlation analysis show the deviation tendency of energy state parameters leading to different types of approach and landing risks. Stochastic simulation results further provide safety boundaries determined by the key energy parameters to avoid the above five end accidents. Warning criteria of the abnormal energy status are then established, described by air-speed vs. glide angle envelops under possible wind conditions and go-around throttle settings, which are shown to be accurate and non-conservative for approach and landing risk warnings caused by abnormal energy. The proposed methods can be applied to on-board risk warning and the related flight control function design for approaching and landing safety of large civil airplanes. Reference | Related Articles | Metrics

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Effect of stress on precipitated phases in DD5 single crystal superalloy during stress rupture tests LV Peisen, GAO Qiang, LI Changjin, LIU Lirong, ZHANG Mingjun, PENG Zhijiang ACTA AERONAUTICAET ASTRONAUTICA SINICA    2021, 42 (6): 424073-424073.   DOI: 10.7527/S1000-6893.2020.24073 Abstract （857）   HTML （6）    PDF（pc） （8244KB）（208）       Knowledge map    Save The precipitation of second phase particles at different sites of the specimen in DD5 single crystal superalloy during stress rupture tests is investigated using a scanning electron microscope and a transmission electron microscope. Effect of stress on the precipitation of the second phases and the crystal structure of the two precipitated phases are analysed. The results show that at 1 038℃/172 MPa, with the increase of the local tensile stress, the number of precipitated phases in both the interdendritic region and the dendrite arm increases obviously, whereas at 871℃/552 MPa, only a small number of granular precipitates are precipitated in the interdendritic region, and the number of precipitates increases with the increase of the tensile stress. The TEM analysis shows that the phase precipitated in the dendrite arm is mainly μ phase with a rhombohedral structure and that precipitated in the interdendritic region is mainly M23C6 phase. Reference | Related Articles | Metrics

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Low cycle fatigue life prediction of FGH96 alloy based on modified SWT model XIAO Yang, QIN Haiqin, XU Kejun, JIA Mingming, ZHANG Zhuzhu ACTA AERONAUTICAET ASTRONAUTICA SINICA    2021, 42 (5): 524360-524360.   DOI: 10.7527/S1000-6893.2020.24360 Abstract （844）   HTML （11）    PDF（pc） （3778KB）（129）       Knowledge map    Save To solve the problems that Smith-Watson-Topper (SWT) model does not consider the sensitivity of material to the mean stress and ignores the effect of the mean stress on plastic deformation, we improved the computing method of the Walker exponent γ based on the yield strength and tensile strength, and modified the damage control parameter of the SWT model using the improved Walker exponent. Meanwhile, based on the Manson-Halford (M-H) model, the plastic deformation parameter of the SWT model was modified with the mean stress. Then an Low Cycle Fatigue (LCF) life prediction method for the FGH96 powder metallurgy superalloy was proposed based on the improved SWT model. The improved computing method of the Walker exponent was verified using the experimental calculation values of different materials, and the average relative error of calculation is 10.25%. The experimental data of the FGH96 alloy and other aero-engine materials show that the improved SWT model can provide better prediction than the M-H, SWT and Lv models, with nearly all the predicted results within ±2 times the scatter band. Reference | Related Articles | Metrics