Pub Date : 2023-06-01DOI: 10.1051/jnwpu/20234130579
Dongxia Li, Siyu Song, Haitao Liu
An unmanned aerial vehicle's(UAV) trajectory optimization is an important way to improve the performance of its relay communication system. The trajectory optimization method for the UAV cascade relay broadcast communication system that uses the decoding and forwarding protocols is studied. Firstly, the expressions of the signal-to-noise ratio of the UAV and the user are given. Then, a joint trajectory optimization method and a distributed trajectory optimization method for cascaded UAVs based on the minimized maximum user interruption probability are proposed. The transmission performance of the system link that uses the two trajectory optimization methods is studied; the mathematical expressions of the relay communication system's traverse capacity and the outage probability of a single user are given. Finally, the influence of the relay communication system's characteristic parameters on the optimal trajectory of the cascade relay UAV and its performance are verified with computer simulations. The simulation results show that the performance of the two trajectory optimization methods is basically the same, thus verifying the effectiveness of the trajectory optimization criterion.
{"title":"A trajectory optimization method for UAV cascade relay broadcast communication system","authors":"Dongxia Li, Siyu Song, Haitao Liu","doi":"10.1051/jnwpu/20234130579","DOIUrl":"https://doi.org/10.1051/jnwpu/20234130579","url":null,"abstract":"An unmanned aerial vehicle's(UAV) trajectory optimization is an important way to improve the performance of its relay communication system. The trajectory optimization method for the UAV cascade relay broadcast communication system that uses the decoding and forwarding protocols is studied. Firstly, the expressions of the signal-to-noise ratio of the UAV and the user are given. Then, a joint trajectory optimization method and a distributed trajectory optimization method for cascaded UAVs based on the minimized maximum user interruption probability are proposed. The transmission performance of the system link that uses the two trajectory optimization methods is studied; the mathematical expressions of the relay communication system's traverse capacity and the outage probability of a single user are given. Finally, the influence of the relay communication system's characteristic parameters on the optimal trajectory of the cascade relay UAV and its performance are verified with computer simulations. The simulation results show that the performance of the two trajectory optimization methods is basically the same, thus verifying the effectiveness of the trajectory optimization criterion.","PeriodicalId":39691,"journal":{"name":"西北工业大学学报","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"45582194","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2023-06-01DOI: 10.1051/jnwpu/20234130529
S. Ishkov, G. A. Filippov, Xiao Zhou, Changqing Wang
To solve the time-free rendezvous problem of two spacecraft, the multi-criteria optimization of the relative motion trajectory of the linear motion model in an orbiting cylindrical reference frame is studied. The equations for describing the secular and periodic parameters of the relative motion are obtained. The structure of the nominal control program for the longitudinal motion control variant with finite transversal thrust is investigated in some detail, and its analytical solutions are obtained. An algorithm for solving the Pareto-optimal control program for arbitrary boundary conditions and thrust control acceleration values in the standard time including maneuver time and total time is developed. The algorithm uses the Pareto optimal method to achieve two kinds of multi-objective optimization (total time optimization and fuel optimization). The numerical calculation results on the geostationary planar orbit parameter correction variants are given.
{"title":"Pareto-optimal control of relative motion in the orbital maneuvering problem of spacecraft with finite thrust","authors":"S. Ishkov, G. A. Filippov, Xiao Zhou, Changqing Wang","doi":"10.1051/jnwpu/20234130529","DOIUrl":"https://doi.org/10.1051/jnwpu/20234130529","url":null,"abstract":"To solve the time-free rendezvous problem of two spacecraft, the multi-criteria optimization of the relative motion trajectory of the linear motion model in an orbiting cylindrical reference frame is studied. The equations for describing the secular and periodic parameters of the relative motion are obtained. The structure of the nominal control program for the longitudinal motion control variant with finite transversal thrust is investigated in some detail, and its analytical solutions are obtained. An algorithm for solving the Pareto-optimal control program for arbitrary boundary conditions and thrust control acceleration values in the standard time including maneuver time and total time is developed. The algorithm uses the Pareto optimal method to achieve two kinds of multi-objective optimization (total time optimization and fuel optimization). The numerical calculation results on the geostationary planar orbit parameter correction variants are given.","PeriodicalId":39691,"journal":{"name":"西北工业大学学报","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"45924258","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2023-06-01DOI: 10.1051/jnwpu/20234130568
Ting Qin, Tao He, Jindong Lyu, Junkun Yan, Tianqi Qin, Hongzhi Liu
Reasonable planning the trajectory of the airborne radar network can decrease its repeated surveillance region, and improve the search efficiency. To complete a wider range of reconnaissance searches within a certain time, a search task oriented path optimization method of airborne radar network is proposed. Firstly, the single-platform search range by combing the radar equation is characterized, and the multi-radar area coverage function based on the rasterization idea is calculated. A trajectory optimization model with the goal of maximizing the search coverage function is constructed, by combining with the motion constraints of each node and adopting an intelligent method. Simulation results show that the present method can obtain higher search coverage within specified time.
{"title":"Search task oriented path planning method of airborne radar network","authors":"Ting Qin, Tao He, Jindong Lyu, Junkun Yan, Tianqi Qin, Hongzhi Liu","doi":"10.1051/jnwpu/20234130568","DOIUrl":"https://doi.org/10.1051/jnwpu/20234130568","url":null,"abstract":"Reasonable planning the trajectory of the airborne radar network can decrease its repeated surveillance region, and improve the search efficiency. To complete a wider range of reconnaissance searches within a certain time, a search task oriented path optimization method of airborne radar network is proposed. Firstly, the single-platform search range by combing the radar equation is characterized, and the multi-radar area coverage function based on the rasterization idea is calculated. A trajectory optimization model with the goal of maximizing the search coverage function is constructed, by combining with the motion constraints of each node and adopting an intelligent method. Simulation results show that the present method can obtain higher search coverage within specified time.","PeriodicalId":39691,"journal":{"name":"西北工业大学学报","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"45908748","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Aerial safety separation is an important indicator to evaluate the flight performance of medium and low speed combination aircraft. In this paper, the concept of impact box and safe separation corridor will be introduced for the air separation problem of the composite aircraft, and a numerical method for quickly obtaining the safe separation area of the composite aircraft is proposed: the influence box-corridor method, and the suitable separation area generation of a composite aircraft will be studied by this method. The article introduces and simplifies the separation process of a certain type of combined aircraft. The concept of impact box and safe separation corridor and the logic and process of the impact box-corridor method are expounded. On this basis, the method is applied to determine the safe separation area of a single body of a composite aircraft through numerical simulation. Finally, the application of this method to the field of real-time separation of aircraft is extended.
{"title":"Research on the safe separation corridor of the combined aircraft and its generation method","authors":"Yihua Pan, Qingsong Zhang, Jincheng Zhang, Chengzhi Cai, Shan Jia","doi":"10.1051/jnwpu/20234130480","DOIUrl":"https://doi.org/10.1051/jnwpu/20234130480","url":null,"abstract":"Aerial safety separation is an important indicator to evaluate the flight performance of medium and low speed combination aircraft. In this paper, the concept of impact box and safe separation corridor will be introduced for the air separation problem of the composite aircraft, and a numerical method for quickly obtaining the safe separation area of the composite aircraft is proposed: the influence box-corridor method, and the suitable separation area generation of a composite aircraft will be studied by this method. The article introduces and simplifies the separation process of a certain type of combined aircraft. The concept of impact box and safe separation corridor and the logic and process of the impact box-corridor method are expounded. On this basis, the method is applied to determine the safe separation area of a single body of a composite aircraft through numerical simulation. Finally, the application of this method to the field of real-time separation of aircraft is extended.","PeriodicalId":39691,"journal":{"name":"西北工业大学学报","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"41614866","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2023-06-01DOI: 10.1051/jnwpu/20234130595
Pengcheng Gao, Qiaogao Huang, Dong Song, Guang-xu Pan, Yunlong Ma
To investigate the effect of group gliding formation on the hydrodynamic performance of manta rays, numerical simulations were used to investigate the drag, the lift and pressure distribution of multiple manta rays in tandem, triangular and diamond-shaped arrangements. The simulation results show that the leader manta ray at the head of the group always suffers the least drag, and in most cases, the companion manta ray at the tail of the group suffers the most drag. The pressure distribution in the flow field shows that the drag reduction effect mainly comes from the distribution of high pressure and low pressure zones among the individual rays in the cluster, the high pressure zone is beneficial to the manta rays at the front of the group, and under certain circumstances, the presence of low pressure zone generates forward suction to reduce the drag of the manta rays at the end of the group. It is found that when manta rays glide in "two in front and one at the back", four-body diamond, six-body tandem and six-body diamond arrangement, the average drag of the system can be reduced, which provides theoretical guidance for the formation of bionic vehicle groups.
{"title":"Hydrodynamic performance study of manta ray gliding in groups","authors":"Pengcheng Gao, Qiaogao Huang, Dong Song, Guang-xu Pan, Yunlong Ma","doi":"10.1051/jnwpu/20234130595","DOIUrl":"https://doi.org/10.1051/jnwpu/20234130595","url":null,"abstract":"To investigate the effect of group gliding formation on the hydrodynamic performance of manta rays, numerical simulations were used to investigate the drag, the lift and pressure distribution of multiple manta rays in tandem, triangular and diamond-shaped arrangements. The simulation results show that the leader manta ray at the head of the group always suffers the least drag, and in most cases, the companion manta ray at the tail of the group suffers the most drag. The pressure distribution in the flow field shows that the drag reduction effect mainly comes from the distribution of high pressure and low pressure zones among the individual rays in the cluster, the high pressure zone is beneficial to the manta rays at the front of the group, and under certain circumstances, the presence of low pressure zone generates forward suction to reduce the drag of the manta rays at the end of the group. It is found that when manta rays glide in \"two in front and one at the back\", four-body diamond, six-body tandem and six-body diamond arrangement, the average drag of the system can be reduced, which provides theoretical guidance for the formation of bionic vehicle groups.","PeriodicalId":39691,"journal":{"name":"西北工业大学学报","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"48119032","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2023-06-01DOI: 10.1051/jnwpu/20234130621
Xiaoyan Zhang, Jia'ao Cheng, Hongjun Xue
The tough noise environment in helicopter cockpit can passively influence pilots in mental and physical way, weaken their core competency, and as a result, maybe causing pilot error and even accidents. The current research can evaluate the physical characteristics of noise and its impact on emotion such as noise annoyance, but it ignores the impact of cockpit noise on human competence. Therefore, this paper establishes a noise evaluation and prediction model based on core competence with task performance, cognitive load and eye movement data. Experiment is designed and implemented in three noise levels and three task difficulties to verify the model. The results indicate that: 1) core competency and task accuracy decline in higher noise levels significantly. 2) the noise assessment method based on core competency can accurately predict the influence of noise on human performance. This novel method can quantitatively reflect the impact of noise changes on human performance in emergency condition. It can expand the connotation of noise evaluation, provide the evaluation and control of cockpit noise with theoretical explanations, and provide the optimization design of helicopter cockpit with practical data.
{"title":"A novel noise assessment method based on human core competency","authors":"Xiaoyan Zhang, Jia'ao Cheng, Hongjun Xue","doi":"10.1051/jnwpu/20234130621","DOIUrl":"https://doi.org/10.1051/jnwpu/20234130621","url":null,"abstract":"The tough noise environment in helicopter cockpit can passively influence pilots in mental and physical way, weaken their core competency, and as a result, maybe causing pilot error and even accidents. The current research can evaluate the physical characteristics of noise and its impact on emotion such as noise annoyance, but it ignores the impact of cockpit noise on human competence. Therefore, this paper establishes a noise evaluation and prediction model based on core competence with task performance, cognitive load and eye movement data. Experiment is designed and implemented in three noise levels and three task difficulties to verify the model. The results indicate that: 1) core competency and task accuracy decline in higher noise levels significantly. 2) the noise assessment method based on core competency can accurately predict the influence of noise on human performance. This novel method can quantitatively reflect the impact of noise changes on human performance in emergency condition. It can expand the connotation of noise evaluation, provide the evaluation and control of cockpit noise with theoretical explanations, and provide the optimization design of helicopter cockpit with practical data.","PeriodicalId":39691,"journal":{"name":"西北工业大学学报","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"47013651","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2023-06-01DOI: 10.1051/jnwpu/20234130601
Denghui Qin, Qiaogao Huang, Guang-xu Pan, Fuzheng Li, Peng Han
A pre-swirl pumpjet propeller(PJP) is widely used in the new generation of quiet submarines all over the world, although the experimental study of its hydrodynamic performances is still rare. This paper carries out experimental tests of the pre-swirl PJP with a 9-blade stator and a 7-blade rotor in a cavitation water tunnel. The thrust coefficient and torque coefficient of the pre-swirl PJP in open water are tested with a force measurement device, and the wake flow field of the pre-swirl PJP is tested with a laser particle velocimetry system. The experimental results show that the rotor thrust coefficient, stator-duct thrust coefficient and rotor torque coefficient of the pre-swirl PJP decrease with increasing the advance coefficient J, but the absolute value of the torque coefficient of the stator-duct thrust increases with increasing J. The open water efficiency of the pre-swirl PJP reaches the maximum when J=1.0, being 61.91%. The thrust of the pre-swirl PJP is mainly provided by the rotor. In addition, the wake flow field of the pre-swirl PJP is composed of jet acceleration zone, hub low-speed zone and mixed zone. The transient velocity and average velocity in the wake flow field under different working conditions are obtained.
{"title":"Experimental study of hydrodynamic performances of pre-swirl pumpjet propeller","authors":"Denghui Qin, Qiaogao Huang, Guang-xu Pan, Fuzheng Li, Peng Han","doi":"10.1051/jnwpu/20234130601","DOIUrl":"https://doi.org/10.1051/jnwpu/20234130601","url":null,"abstract":"A pre-swirl pumpjet propeller(PJP) is widely used in the new generation of quiet submarines all over the world, although the experimental study of its hydrodynamic performances is still rare. This paper carries out experimental tests of the pre-swirl PJP with a 9-blade stator and a 7-blade rotor in a cavitation water tunnel. The thrust coefficient and torque coefficient of the pre-swirl PJP in open water are tested with a force measurement device, and the wake flow field of the pre-swirl PJP is tested with a laser particle velocimetry system. The experimental results show that the rotor thrust coefficient, stator-duct thrust coefficient and rotor torque coefficient of the pre-swirl PJP decrease with increasing the advance coefficient J, but the absolute value of the torque coefficient of the stator-duct thrust increases with increasing J. The open water efficiency of the pre-swirl PJP reaches the maximum when J=1.0, being 61.91%. The thrust of the pre-swirl PJP is mainly provided by the rotor. In addition, the wake flow field of the pre-swirl PJP is composed of jet acceleration zone, hub low-speed zone and mixed zone. The transient velocity and average velocity in the wake flow field under different working conditions are obtained.","PeriodicalId":39691,"journal":{"name":"西北工业大学学报","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"45703603","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2023-06-01DOI: 10.1051/jnwpu/20234130490
Yu Wang, Xiaoping Zhu, Zhou Zhou
This paper studies the dynamic modeling method of fold-able multi-body aircraft based on the dynamics theory of multi-body system. Considering the multi-body aircraft as a complete multi-rigid body system, the dynamic model for the free unfolding process of the multi-body aircraft after horizontal launch is established. On the basis of the multi-body dynamics model, the coil spring moment model and the damping moment model for the flexible connection between the flight units are added. Taking a certain type of fold-able three-section wing aircraft as an example, the numerical simulation calculation is carried out. The influence of the flexible connection stiffness coefficient between the flight unit on the dynamic characteristics of the fold-able multi-body aircraft in the free deployment process and the relationship between the stiffness of the flexible connection and the maximum initial folding angle are studied. Finally, the stability envelope between the stiffness coefficient of the flexible connection and the maximum initial folding angle is determined.
{"title":"Dynamics modeling and flight characteristics of folded multi-body aircraft","authors":"Yu Wang, Xiaoping Zhu, Zhou Zhou","doi":"10.1051/jnwpu/20234130490","DOIUrl":"https://doi.org/10.1051/jnwpu/20234130490","url":null,"abstract":"This paper studies the dynamic modeling method of fold-able multi-body aircraft based on the dynamics theory of multi-body system. Considering the multi-body aircraft as a complete multi-rigid body system, the dynamic model for the free unfolding process of the multi-body aircraft after horizontal launch is established. On the basis of the multi-body dynamics model, the coil spring moment model and the damping moment model for the flexible connection between the flight units are added. Taking a certain type of fold-able three-section wing aircraft as an example, the numerical simulation calculation is carried out. The influence of the flexible connection stiffness coefficient between the flight unit on the dynamic characteristics of the fold-able multi-body aircraft in the free deployment process and the relationship between the stiffness of the flexible connection and the maximum initial folding angle are studied. Finally, the stability envelope between the stiffness coefficient of the flexible connection and the maximum initial folding angle is determined.","PeriodicalId":39691,"journal":{"name":"西北工业大学学报","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"48915506","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2023-06-01DOI: 10.1051/jnwpu/20234130557
Min Zhang, Junsheng Wu, Xining Cui, Jingchang Sun
Partition operating system conforming to ARINC653 is widely used in airborne to support application software integration. Under the two-level scheduling model for partition operating system, the demanding real-time requirements of airborne software are usually difficult to obtain effective deterministic guarantee, so it is very important to analyze the schedulability of the system. Judging whether the scheduling table can meet the real-time requirements of the process in the partition through the schedulability analysis algorithm is an effective means to ensure that all processes in the system complete the computing task within the specified time. Based on the method of operations research and the introduction of virtual process, a schedulability analysis algorithm for multi partition system is designed, and the numerical verification is carried out. The verification results show that the algorithm can accurately judge whether the scheduling table matches the process time attribute, give the qualitative analysis conclusion of whether the system can be scheduled, help the system integrator to verify the rationality of the scheduling table before the actual operation of the system, and reduce the risk of test and flight test.
{"title":"Research on schedulability analysis algorithm of airborne multi partition system","authors":"Min Zhang, Junsheng Wu, Xining Cui, Jingchang Sun","doi":"10.1051/jnwpu/20234130557","DOIUrl":"https://doi.org/10.1051/jnwpu/20234130557","url":null,"abstract":"Partition operating system conforming to ARINC653 is widely used in airborne to support application software integration. Under the two-level scheduling model for partition operating system, the demanding real-time requirements of airborne software are usually difficult to obtain effective deterministic guarantee, so it is very important to analyze the schedulability of the system. Judging whether the scheduling table can meet the real-time requirements of the process in the partition through the schedulability analysis algorithm is an effective means to ensure that all processes in the system complete the computing task within the specified time. Based on the method of operations research and the introduction of virtual process, a schedulability analysis algorithm for multi partition system is designed, and the numerical verification is carried out. The verification results show that the algorithm can accurately judge whether the scheduling table matches the process time attribute, give the qualitative analysis conclusion of whether the system can be scheduled, help the system integrator to verify the rationality of the scheduling table before the actual operation of the system, and reduce the risk of test and flight test.","PeriodicalId":39691,"journal":{"name":"西北工业大学学报","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"44781825","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2023-06-01DOI: 10.1051/jnwpu/20234130464
Yufan Zhang, Yuren Li, Rui Ma, Hongyu Zhang, Bo Liang
Fuel cell involves many disciplines such as electricity, mechanics, electrochemistry, and thermodynamics, and its performance degradation process is complex, involving multi-physics, multi-scale, multi-parts, and multi-factors. Thus, it is difficult for a single model to capture all kinds of characteristics of fuel cell simultaneously in degradation prediction. To ensure the prediction accuracy while better fitting the data linearly and nonlinearly, a prediction model of ARIMA combined with LSTM neural network is proposed in this study. The prediction results with residuals are used as features for LSTM prediction work after first predicting the voltage decay data by ARIMA and LSTM. Comparing the hybrid model with the single ARIMA model and the NAR model with support vector regression learning, it is found that the hybrid model performs better in terms of prediction accuracy and prediction performance.
{"title":"Degradation prediction method of PEMFC based on deep learning hybrid model integrating ARIMA and LSTM","authors":"Yufan Zhang, Yuren Li, Rui Ma, Hongyu Zhang, Bo Liang","doi":"10.1051/jnwpu/20234130464","DOIUrl":"https://doi.org/10.1051/jnwpu/20234130464","url":null,"abstract":"Fuel cell involves many disciplines such as electricity, mechanics, electrochemistry, and thermodynamics, and its performance degradation process is complex, involving multi-physics, multi-scale, multi-parts, and multi-factors. Thus, it is difficult for a single model to capture all kinds of characteristics of fuel cell simultaneously in degradation prediction. To ensure the prediction accuracy while better fitting the data linearly and nonlinearly, a prediction model of ARIMA combined with LSTM neural network is proposed in this study. The prediction results with residuals are used as features for LSTM prediction work after first predicting the voltage decay data by ARIMA and LSTM. Comparing the hybrid model with the single ARIMA model and the NAR model with support vector regression learning, it is found that the hybrid model performs better in terms of prediction accuracy and prediction performance.","PeriodicalId":39691,"journal":{"name":"西北工业大学学报","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"57899171","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
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