To reduce the secondary flow loss of the high-pressure turbine caused by the tip leakage flow, the design of the composite honeycomb tip has been experimentally and numerically examined in this study. The arrangement angle of the composite honeycomb is defined and optimized using the radial basis function and genetic algorithm. The tip flow field of the high-pressure turbine blade with a 2.128 mm clearance is simulated by CFX 18.0, and the arrangement angle of the composite honeycomb is optimized to obtain a lower loss. Moreover, the flat tip, basic honeycomb tip, and optimized honeycomb tip are tested in a low-speed cascade test facility. The results show that the vortices and radial velocity induced by the honeycomb structure cavity increase the kinetic energy loss of the leakage flow and reduce the leakage flow rate. Compared with the basic honeycomb, the optimized honeycomb has a supplemental blocking effect on the tip leakage flow by reducing the crosswise pressure gradient in the blade tip. The optimized honeycomb also changes the outlet angle of the leakage flow in the tip clearance, reduces the leakage vortex, and the total pressure loss is further reduced by 2.5%.
{"title":"A study of angle parametric optimization of the composite honeycomb on turbine blade tip","authors":"Qingguo Kong, Jiaxin Ning, Xiaopeng Sun, Xiande Pan, Shuang Sun, Lehan Lu, Haixu Si","doi":"10.1177/09544100241248721","DOIUrl":"https://doi.org/10.1177/09544100241248721","url":null,"abstract":"To reduce the secondary flow loss of the high-pressure turbine caused by the tip leakage flow, the design of the composite honeycomb tip has been experimentally and numerically examined in this study. The arrangement angle of the composite honeycomb is defined and optimized using the radial basis function and genetic algorithm. The tip flow field of the high-pressure turbine blade with a 2.128 mm clearance is simulated by CFX 18.0, and the arrangement angle of the composite honeycomb is optimized to obtain a lower loss. Moreover, the flat tip, basic honeycomb tip, and optimized honeycomb tip are tested in a low-speed cascade test facility. The results show that the vortices and radial velocity induced by the honeycomb structure cavity increase the kinetic energy loss of the leakage flow and reduce the leakage flow rate. Compared with the basic honeycomb, the optimized honeycomb has a supplemental blocking effect on the tip leakage flow by reducing the crosswise pressure gradient in the blade tip. The optimized honeycomb also changes the outlet angle of the leakage flow in the tip clearance, reduces the leakage vortex, and the total pressure loss is further reduced by 2.5%.","PeriodicalId":506990,"journal":{"name":"Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering","volume":"4 2","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-04-22","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140674158","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 : 2024-02-13DOI: 10.1177/09544100241232133
Hyun-gi Kim, Sungchan Kim
Electrically powered airplanes can cope with global warming by reducing the use of fossil fuels and reduce airplane costs in the long run through the efficient use of energy. For this reason, advanced aviation countries such as the United States and several countries in the European Union are leading the development of innovative technologies to realize a fully electric airplane in the future. Currently, research and development efforts are underway domestically to convert existing two-seater airplanes into electric-powered airplanes. In this study, the KLA-100X, which was developed by converting the existing two-seat lightweight sport airplane KLA-100 into an electric propulsion airplane, was introduced. In this text, the main specifications, design characteristics, and performance of KLA-100X are examined. In addition, the performance of the major components of the propulsion system, in this case the propulsion motor, inverter, and battery developed for application to KLA-100X are assessed, and the control system, additionally altered according to electric propulsion modification, is explained. Finally, the applicability of the developed major components to an electric propulsion airplane is confirmed by conducting ground and flight tests on the KLA-100X and presenting the results. In the future, the expansion of research aimed at improving the performance of current electric propulsion airplanes can be reviewed through the development of a dedicated platform for an electric propulsion airplane.
{"title":"Development and flight test of a manned electric propulsion lightweight airplane","authors":"Hyun-gi Kim, Sungchan Kim","doi":"10.1177/09544100241232133","DOIUrl":"https://doi.org/10.1177/09544100241232133","url":null,"abstract":"Electrically powered airplanes can cope with global warming by reducing the use of fossil fuels and reduce airplane costs in the long run through the efficient use of energy. For this reason, advanced aviation countries such as the United States and several countries in the European Union are leading the development of innovative technologies to realize a fully electric airplane in the future. Currently, research and development efforts are underway domestically to convert existing two-seater airplanes into electric-powered airplanes. In this study, the KLA-100X, which was developed by converting the existing two-seat lightweight sport airplane KLA-100 into an electric propulsion airplane, was introduced. In this text, the main specifications, design characteristics, and performance of KLA-100X are examined. In addition, the performance of the major components of the propulsion system, in this case the propulsion motor, inverter, and battery developed for application to KLA-100X are assessed, and the control system, additionally altered according to electric propulsion modification, is explained. Finally, the applicability of the developed major components to an electric propulsion airplane is confirmed by conducting ground and flight tests on the KLA-100X and presenting the results. In the future, the expansion of research aimed at improving the performance of current electric propulsion airplanes can be reviewed through the development of a dedicated platform for an electric propulsion airplane.","PeriodicalId":506990,"journal":{"name":"Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering","volume":"190 ","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-02-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139841895","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 : 2024-02-13DOI: 10.1177/09544100241232133
Hyun-gi Kim, Sungchan Kim
Electrically powered airplanes can cope with global warming by reducing the use of fossil fuels and reduce airplane costs in the long run through the efficient use of energy. For this reason, advanced aviation countries such as the United States and several countries in the European Union are leading the development of innovative technologies to realize a fully electric airplane in the future. Currently, research and development efforts are underway domestically to convert existing two-seater airplanes into electric-powered airplanes. In this study, the KLA-100X, which was developed by converting the existing two-seat lightweight sport airplane KLA-100 into an electric propulsion airplane, was introduced. In this text, the main specifications, design characteristics, and performance of KLA-100X are examined. In addition, the performance of the major components of the propulsion system, in this case the propulsion motor, inverter, and battery developed for application to KLA-100X are assessed, and the control system, additionally altered according to electric propulsion modification, is explained. Finally, the applicability of the developed major components to an electric propulsion airplane is confirmed by conducting ground and flight tests on the KLA-100X and presenting the results. In the future, the expansion of research aimed at improving the performance of current electric propulsion airplanes can be reviewed through the development of a dedicated platform for an electric propulsion airplane.
{"title":"Development and flight test of a manned electric propulsion lightweight airplane","authors":"Hyun-gi Kim, Sungchan Kim","doi":"10.1177/09544100241232133","DOIUrl":"https://doi.org/10.1177/09544100241232133","url":null,"abstract":"Electrically powered airplanes can cope with global warming by reducing the use of fossil fuels and reduce airplane costs in the long run through the efficient use of energy. For this reason, advanced aviation countries such as the United States and several countries in the European Union are leading the development of innovative technologies to realize a fully electric airplane in the future. Currently, research and development efforts are underway domestically to convert existing two-seater airplanes into electric-powered airplanes. In this study, the KLA-100X, which was developed by converting the existing two-seat lightweight sport airplane KLA-100 into an electric propulsion airplane, was introduced. In this text, the main specifications, design characteristics, and performance of KLA-100X are examined. In addition, the performance of the major components of the propulsion system, in this case the propulsion motor, inverter, and battery developed for application to KLA-100X are assessed, and the control system, additionally altered according to electric propulsion modification, is explained. Finally, the applicability of the developed major components to an electric propulsion airplane is confirmed by conducting ground and flight tests on the KLA-100X and presenting the results. In the future, the expansion of research aimed at improving the performance of current electric propulsion airplanes can be reviewed through the development of a dedicated platform for an electric propulsion airplane.","PeriodicalId":506990,"journal":{"name":"Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering","volume":"32 28","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-02-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139782122","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 : 2024-02-12DOI: 10.1177/09544100241233327
Mian Gong, Siteng Zhou, Di Zhou
In this paper, an optimal sliding mode guidance law with impact angle constraint is proposed against maneuvering targets. Firstly, the impact angle frame for a static target is extended to a maneuvering target. Then, in this impact angle frame, the optimal reaching law of sliding mode is proposed to design an optimal sliding mode guidance law which is robust to target maneuvers and satisfies an impact angle constraint. The optimal sliding mode guidance law with impact angle constraint is also extended to the three-dimensional case. Numerical simulations in different scenarios with a realistic missile model show that the guidance law can intercept a maneuvering target with a desired impact angle, and the control effort is close to the optimal value, which verifies that the proposed optimal sliding mode guidance law has both robustness and optimality.
{"title":"Optimal sliding mode guidance law against maneuvering target with impact angle constraint","authors":"Mian Gong, Siteng Zhou, Di Zhou","doi":"10.1177/09544100241233327","DOIUrl":"https://doi.org/10.1177/09544100241233327","url":null,"abstract":"In this paper, an optimal sliding mode guidance law with impact angle constraint is proposed against maneuvering targets. Firstly, the impact angle frame for a static target is extended to a maneuvering target. Then, in this impact angle frame, the optimal reaching law of sliding mode is proposed to design an optimal sliding mode guidance law which is robust to target maneuvers and satisfies an impact angle constraint. The optimal sliding mode guidance law with impact angle constraint is also extended to the three-dimensional case. Numerical simulations in different scenarios with a realistic missile model show that the guidance law can intercept a maneuvering target with a desired impact angle, and the control effort is close to the optimal value, which verifies that the proposed optimal sliding mode guidance law has both robustness and optimality.","PeriodicalId":506990,"journal":{"name":"Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering","volume":"126 5","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-02-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139842875","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 : 2024-02-12DOI: 10.1177/09544100241233323
Shikai Shao, Yi Guo, Yuanjie Zhao
Planning a safe and dynamic flyable trajectory for unmanned aerial vehicle (UAV) is the precondition for autonomous flight. Considering environmental complexity and flight safety under limited motor speed, we proposed a new time-segmented trajectory planning method, which can ensure motor speed within the allowable range and achieve safe flight. Firstly, the candidate trajectory for quadrotor UAV is expressed by high-order polynomials. Herein, polynomial is used as the expression of trajectory, and nonlinear programming (NLP) is used to calculate polynomial coefficient. Then, two strategies and an initial value calculation method are proposed to improve the efficiency of NLP. Furthermore, aiming at the problem that the initial trajectory of UAV motor cannot meet the current speed limit constraint after the motor speed drops, an adjustment strategy based on feasible trajectory is designed. The method presented in this paper not only enhances flexibility of the flight process, improves solving efficiency of the algorithm but also enables UAV to continue flying when the motor speed is limited. Finally, simulation analysis and comparison illustrate the effectiveness and superiority of the proposed method.
{"title":"Rapid trajectory generation for quadrotor with limited motor speed","authors":"Shikai Shao, Yi Guo, Yuanjie Zhao","doi":"10.1177/09544100241233323","DOIUrl":"https://doi.org/10.1177/09544100241233323","url":null,"abstract":"Planning a safe and dynamic flyable trajectory for unmanned aerial vehicle (UAV) is the precondition for autonomous flight. Considering environmental complexity and flight safety under limited motor speed, we proposed a new time-segmented trajectory planning method, which can ensure motor speed within the allowable range and achieve safe flight. Firstly, the candidate trajectory for quadrotor UAV is expressed by high-order polynomials. Herein, polynomial is used as the expression of trajectory, and nonlinear programming (NLP) is used to calculate polynomial coefficient. Then, two strategies and an initial value calculation method are proposed to improve the efficiency of NLP. Furthermore, aiming at the problem that the initial trajectory of UAV motor cannot meet the current speed limit constraint after the motor speed drops, an adjustment strategy based on feasible trajectory is designed. The method presented in this paper not only enhances flexibility of the flight process, improves solving efficiency of the algorithm but also enables UAV to continue flying when the motor speed is limited. Finally, simulation analysis and comparison illustrate the effectiveness and superiority of the proposed method.","PeriodicalId":506990,"journal":{"name":"Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering","volume":"152 3","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-02-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139842721","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 : 2024-02-12DOI: 10.1177/09544100241233327
Mian Gong, Siteng Zhou, Di Zhou
In this paper, an optimal sliding mode guidance law with impact angle constraint is proposed against maneuvering targets. Firstly, the impact angle frame for a static target is extended to a maneuvering target. Then, in this impact angle frame, the optimal reaching law of sliding mode is proposed to design an optimal sliding mode guidance law which is robust to target maneuvers and satisfies an impact angle constraint. The optimal sliding mode guidance law with impact angle constraint is also extended to the three-dimensional case. Numerical simulations in different scenarios with a realistic missile model show that the guidance law can intercept a maneuvering target with a desired impact angle, and the control effort is close to the optimal value, which verifies that the proposed optimal sliding mode guidance law has both robustness and optimality.
{"title":"Optimal sliding mode guidance law against maneuvering target with impact angle constraint","authors":"Mian Gong, Siteng Zhou, Di Zhou","doi":"10.1177/09544100241233327","DOIUrl":"https://doi.org/10.1177/09544100241233327","url":null,"abstract":"In this paper, an optimal sliding mode guidance law with impact angle constraint is proposed against maneuvering targets. Firstly, the impact angle frame for a static target is extended to a maneuvering target. Then, in this impact angle frame, the optimal reaching law of sliding mode is proposed to design an optimal sliding mode guidance law which is robust to target maneuvers and satisfies an impact angle constraint. The optimal sliding mode guidance law with impact angle constraint is also extended to the three-dimensional case. Numerical simulations in different scenarios with a realistic missile model show that the guidance law can intercept a maneuvering target with a desired impact angle, and the control effort is close to the optimal value, which verifies that the proposed optimal sliding mode guidance law has both robustness and optimality.","PeriodicalId":506990,"journal":{"name":"Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering","volume":"11 15","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-02-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139783208","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 : 2024-02-12DOI: 10.1177/09544100241233323
Shikai Shao, Yi Guo, Yuanjie Zhao
Planning a safe and dynamic flyable trajectory for unmanned aerial vehicle (UAV) is the precondition for autonomous flight. Considering environmental complexity and flight safety under limited motor speed, we proposed a new time-segmented trajectory planning method, which can ensure motor speed within the allowable range and achieve safe flight. Firstly, the candidate trajectory for quadrotor UAV is expressed by high-order polynomials. Herein, polynomial is used as the expression of trajectory, and nonlinear programming (NLP) is used to calculate polynomial coefficient. Then, two strategies and an initial value calculation method are proposed to improve the efficiency of NLP. Furthermore, aiming at the problem that the initial trajectory of UAV motor cannot meet the current speed limit constraint after the motor speed drops, an adjustment strategy based on feasible trajectory is designed. The method presented in this paper not only enhances flexibility of the flight process, improves solving efficiency of the algorithm but also enables UAV to continue flying when the motor speed is limited. Finally, simulation analysis and comparison illustrate the effectiveness and superiority of the proposed method.
{"title":"Rapid trajectory generation for quadrotor with limited motor speed","authors":"Shikai Shao, Yi Guo, Yuanjie Zhao","doi":"10.1177/09544100241233323","DOIUrl":"https://doi.org/10.1177/09544100241233323","url":null,"abstract":"Planning a safe and dynamic flyable trajectory for unmanned aerial vehicle (UAV) is the precondition for autonomous flight. Considering environmental complexity and flight safety under limited motor speed, we proposed a new time-segmented trajectory planning method, which can ensure motor speed within the allowable range and achieve safe flight. Firstly, the candidate trajectory for quadrotor UAV is expressed by high-order polynomials. Herein, polynomial is used as the expression of trajectory, and nonlinear programming (NLP) is used to calculate polynomial coefficient. Then, two strategies and an initial value calculation method are proposed to improve the efficiency of NLP. Furthermore, aiming at the problem that the initial trajectory of UAV motor cannot meet the current speed limit constraint after the motor speed drops, an adjustment strategy based on feasible trajectory is designed. The method presented in this paper not only enhances flexibility of the flight process, improves solving efficiency of the algorithm but also enables UAV to continue flying when the motor speed is limited. Finally, simulation analysis and comparison illustrate the effectiveness and superiority of the proposed method.","PeriodicalId":506990,"journal":{"name":"Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering","volume":"13 7","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-02-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139782863","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 : 2024-02-12DOI: 10.1177/09544100241232140
Guanghui Cheng, W. Jing, C. Gao
For the vertical landing phase of the reusable rocket, in order to improve the landing accuracy with consideration of multiple uncertainties, a novel strategy to calculate the ignition height online is proposed based on polynomial guidance law (PGL), particle swarm optimization (PSO), and deep reinforcement learning (DRL). Firstly, a deep neural network (DNN) is designed to describe the relationship between the state of the reusable rocket and the ignition height. To accomplish the guidance task of the vertical landing phase, PGL is modified by introducing the estimated aerodynamic acceleration. Through simulation, the output range of the DNN is estimated by the modified PSO. Then, the reward function is shaped and the parameters of the DNN are trained on a training set of simulation scenarios by the DRL algorithm. Finally, to demonstrate the effectiveness of the proposed strategy, the trained DNN is used to calculate the ignition height of 1500 unlearned simulation scenarios online. The numerical simulation results show that the proposed strategy has higher landing accuracy and lower fuel consumption than the offline strategy of fixed ignition height based on the modified PSO.
{"title":"Calculate the ignition height of the vertical landing phase online for the reusable rocket","authors":"Guanghui Cheng, W. Jing, C. Gao","doi":"10.1177/09544100241232140","DOIUrl":"https://doi.org/10.1177/09544100241232140","url":null,"abstract":"For the vertical landing phase of the reusable rocket, in order to improve the landing accuracy with consideration of multiple uncertainties, a novel strategy to calculate the ignition height online is proposed based on polynomial guidance law (PGL), particle swarm optimization (PSO), and deep reinforcement learning (DRL). Firstly, a deep neural network (DNN) is designed to describe the relationship between the state of the reusable rocket and the ignition height. To accomplish the guidance task of the vertical landing phase, PGL is modified by introducing the estimated aerodynamic acceleration. Through simulation, the output range of the DNN is estimated by the modified PSO. Then, the reward function is shaped and the parameters of the DNN are trained on a training set of simulation scenarios by the DRL algorithm. Finally, to demonstrate the effectiveness of the proposed strategy, the trained DNN is used to calculate the ignition height of 1500 unlearned simulation scenarios online. The numerical simulation results show that the proposed strategy has higher landing accuracy and lower fuel consumption than the offline strategy of fixed ignition height based on the modified PSO.","PeriodicalId":506990,"journal":{"name":"Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering","volume":"81 3","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-02-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139784516","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 : 2024-02-12DOI: 10.1177/09544100241232140
Guanghui Cheng, W. Jing, C. Gao
For the vertical landing phase of the reusable rocket, in order to improve the landing accuracy with consideration of multiple uncertainties, a novel strategy to calculate the ignition height online is proposed based on polynomial guidance law (PGL), particle swarm optimization (PSO), and deep reinforcement learning (DRL). Firstly, a deep neural network (DNN) is designed to describe the relationship between the state of the reusable rocket and the ignition height. To accomplish the guidance task of the vertical landing phase, PGL is modified by introducing the estimated aerodynamic acceleration. Through simulation, the output range of the DNN is estimated by the modified PSO. Then, the reward function is shaped and the parameters of the DNN are trained on a training set of simulation scenarios by the DRL algorithm. Finally, to demonstrate the effectiveness of the proposed strategy, the trained DNN is used to calculate the ignition height of 1500 unlearned simulation scenarios online. The numerical simulation results show that the proposed strategy has higher landing accuracy and lower fuel consumption than the offline strategy of fixed ignition height based on the modified PSO.
{"title":"Calculate the ignition height of the vertical landing phase online for the reusable rocket","authors":"Guanghui Cheng, W. Jing, C. Gao","doi":"10.1177/09544100241232140","DOIUrl":"https://doi.org/10.1177/09544100241232140","url":null,"abstract":"For the vertical landing phase of the reusable rocket, in order to improve the landing accuracy with consideration of multiple uncertainties, a novel strategy to calculate the ignition height online is proposed based on polynomial guidance law (PGL), particle swarm optimization (PSO), and deep reinforcement learning (DRL). Firstly, a deep neural network (DNN) is designed to describe the relationship between the state of the reusable rocket and the ignition height. To accomplish the guidance task of the vertical landing phase, PGL is modified by introducing the estimated aerodynamic acceleration. Through simulation, the output range of the DNN is estimated by the modified PSO. Then, the reward function is shaped and the parameters of the DNN are trained on a training set of simulation scenarios by the DRL algorithm. Finally, to demonstrate the effectiveness of the proposed strategy, the trained DNN is used to calculate the ignition height of 1500 unlearned simulation scenarios online. The numerical simulation results show that the proposed strategy has higher landing accuracy and lower fuel consumption than the offline strategy of fixed ignition height based on the modified PSO.","PeriodicalId":506990,"journal":{"name":"Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering","volume":"59 52","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-02-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139844630","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 : 2024-02-09DOI: 10.1177/09544100241232136
Ridvan Oruc, T. Baklacioglu, Ozlem Sahin
Wake vortex (WV) produced by a large aircraft has the potential to cause serious damage to smaller aircraft following it. In this context, characterization of WV circulation decay under the reasonable worst case (RWC) conditions allows the separation minima to be found safely. In this study, modeling of dimensionless decay curves, which were developed using three experimental LIDAR (Light Detection and Ranging) datasets in the RECAT-EU project and is a useful tool to characterize the wake vortex circulation decay under RWC conditions, was carried out using cuckoo search algorithm (CSA). The decay curves used in the modeling are the median (P50), 10th (P10), and 90th (P90) percentile decay curves of the RWC tracks, which constitute the top 2% longest lasting wakes. The fact that the correlation coefficient (R) values are very close to 1 for all datasets as a result of the error analysis shows that the prediction success of the CSA model is quite high.
{"title":"Characterization modeling of wake vortex circulation decay under reasonable worst case conditions with cuckoo search algorithm","authors":"Ridvan Oruc, T. Baklacioglu, Ozlem Sahin","doi":"10.1177/09544100241232136","DOIUrl":"https://doi.org/10.1177/09544100241232136","url":null,"abstract":"Wake vortex (WV) produced by a large aircraft has the potential to cause serious damage to smaller aircraft following it. In this context, characterization of WV circulation decay under the reasonable worst case (RWC) conditions allows the separation minima to be found safely. In this study, modeling of dimensionless decay curves, which were developed using three experimental LIDAR (Light Detection and Ranging) datasets in the RECAT-EU project and is a useful tool to characterize the wake vortex circulation decay under RWC conditions, was carried out using cuckoo search algorithm (CSA). The decay curves used in the modeling are the median (P50), 10th (P10), and 90th (P90) percentile decay curves of the RWC tracks, which constitute the top 2% longest lasting wakes. The fact that the correlation coefficient (R) values are very close to 1 for all datasets as a result of the error analysis shows that the prediction success of the CSA model is quite high.","PeriodicalId":506990,"journal":{"name":"Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering","volume":"408 21","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-02-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139847874","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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