Pub Date : 2024-02-06DOI: 10.1177/09544100241232130
Chen Xu, Shaowen Chen, Yun Gong
The presence of bleed in an aero engine’s compressor can significantly impact its flow characteristics and contribute to rotating instability. This study focuses on the impact of a typical cavity bleed structure on the internal flow characteristics of a compressor, specifically its circumferential non-uniformity and aerodynamic stability. A numerical simulation involving multiple flow passages was conducted on the transonic high-pressure rotor of the E3 compressor, considering its typical bleed structure. The study delves deep into the non-uniform flow characteristics and the mechanisms behind their generation in the compressor flow field. Furthermore, the influence of bleed on the rotating instability of the compressor is explored by comparing changes in compressor instability and adiabatic efficiency under uniform and non-uniform flow field conditions. The findings indicate that the axial position of the cavity bleed structure plays a crucial role in influencing key parameters such as rotor stall margin, peak efficiency, and total pressure ratio under near-stall conditions. The circumferential non-uniformity, resulting from the presence of the cavity bleed, intensifies with higher bleed air flow rates. For the upstream bleed configuration applied to the rotor, with a total bleed rate of 5%, the maximum variation in absolute flow angle at the inlet of different rotor channels can reach up to 1°. Additionally, the maximum difference in inlet flow coefficient can reach 0.0392. These findings demonstrate that the non-uniformity caused by the typical bleed structure leads to a loss in stall margin for the rotor when compared to a uniform flow field scheme.
{"title":"Non-uniform flow characteristics and rotating instability of a transonic high-pressure compressor rotor with cavity bleed","authors":"Chen Xu, Shaowen Chen, Yun Gong","doi":"10.1177/09544100241232130","DOIUrl":"https://doi.org/10.1177/09544100241232130","url":null,"abstract":"The presence of bleed in an aero engine’s compressor can significantly impact its flow characteristics and contribute to rotating instability. This study focuses on the impact of a typical cavity bleed structure on the internal flow characteristics of a compressor, specifically its circumferential non-uniformity and aerodynamic stability. A numerical simulation involving multiple flow passages was conducted on the transonic high-pressure rotor of the E3 compressor, considering its typical bleed structure. The study delves deep into the non-uniform flow characteristics and the mechanisms behind their generation in the compressor flow field. Furthermore, the influence of bleed on the rotating instability of the compressor is explored by comparing changes in compressor instability and adiabatic efficiency under uniform and non-uniform flow field conditions. The findings indicate that the axial position of the cavity bleed structure plays a crucial role in influencing key parameters such as rotor stall margin, peak efficiency, and total pressure ratio under near-stall conditions. The circumferential non-uniformity, resulting from the presence of the cavity bleed, intensifies with higher bleed air flow rates. For the upstream bleed configuration applied to the rotor, with a total bleed rate of 5%, the maximum variation in absolute flow angle at the inlet of different rotor channels can reach up to 1°. Additionally, the maximum difference in inlet flow coefficient can reach 0.0392. These findings demonstrate that the non-uniformity caused by the typical bleed structure leads to a loss in stall margin for the rotor when compared to a uniform flow field scheme.","PeriodicalId":506990,"journal":{"name":"Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2024-02-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139861138","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 : 2024-02-06DOI: 10.1177/09544100231224071
Jianguo Guo, Yinghe Zhou, Min Zhou
This paper presents an integrated guidance and control design for the homing missiles with the radome error compensation to address the guidance problems caused by radome. Firstly, a mathematics model of the integrated guidance and control system with the compensation for the radome error is built by integrating the missile dynamics and the engagement kinematics between the missile and ground target on the longitudinal motion. Secondly, the model is transformed into a normal form by nonlinear coordinate transformation because the system is a time-varying system with mismatched uncertainties. Thirdly, an adaptive control law of the system is designed by adopting the sliding mode control theory, and the stability of the closed-loop system is also conducted. Finally, the simulation proves that the proposed integrated guidance and control scheme can effectively compensate for the radome error and ensure the hit-to-kill attack to the target.
{"title":"Adaptive control law based integrated guidance and control design for missile with the radome error compensation","authors":"Jianguo Guo, Yinghe Zhou, Min Zhou","doi":"10.1177/09544100231224071","DOIUrl":"https://doi.org/10.1177/09544100231224071","url":null,"abstract":"This paper presents an integrated guidance and control design for the homing missiles with the radome error compensation to address the guidance problems caused by radome. Firstly, a mathematics model of the integrated guidance and control system with the compensation for the radome error is built by integrating the missile dynamics and the engagement kinematics between the missile and ground target on the longitudinal motion. Secondly, the model is transformed into a normal form by nonlinear coordinate transformation because the system is a time-varying system with mismatched uncertainties. Thirdly, an adaptive control law of the system is designed by adopting the sliding mode control theory, and the stability of the closed-loop system is also conducted. Finally, the simulation proves that the proposed integrated guidance and control scheme can effectively compensate for the radome error and ensure the hit-to-kill attack to the target.","PeriodicalId":506990,"journal":{"name":"Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2024-02-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139861782","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 : 2024-02-06DOI: 10.1177/09544100241232126
Wenhao Ji, Wei-hua Sun, Hong‐lei Ma, Yu Zhang, Xin Wang
In the dynamic topology optimization design of pipeline system, parametric finite element modeling (PFEM) is needed to improve the model reconstruction efficiency. Taking a typical spatial single pipeline as the research object, this paper innovatively presents a PFEM method of pipeline system based on the newly constructed nonconforming solid (Solid-NC) element. The stiffness and mass matrices of the spatial 8-node Solid-NC element with second-order boundary accuracy are obtained by introducing the node-free displacement items and statics condensation method. The PFEM method of the pipeline body is proposed by selecting the straight-line segment lengths as the pipeline shape control parameters. The PFEM method of the pipeline is described in detail, including the node coordinate solutions of straight-line and curved arc segments based on the direction vector method and vector decomposition method, respectively, and the simulation of the clamp mechanical properties considering the actual pre-tightening state of the clamp. Furthermore, the modal analysis is carried out, the node stress response solution is solved based on the stress smoothing method, and the effectiveness of the PFEM method is verified through experiment. Finally, the mesh quality and model reconstruction efficiency of the PFEM method is analyzed, the results show that the developed PFEM method has higher mesh quality and fast model reconstruction speed, and the model reconstruction time is shortened by 544.5 times at most compared with ANSYS software.
{"title":"A general parametric finite element modeling and stress response analysis methods for pipeline system using the nonconforming solid element","authors":"Wenhao Ji, Wei-hua Sun, Hong‐lei Ma, Yu Zhang, Xin Wang","doi":"10.1177/09544100241232126","DOIUrl":"https://doi.org/10.1177/09544100241232126","url":null,"abstract":"In the dynamic topology optimization design of pipeline system, parametric finite element modeling (PFEM) is needed to improve the model reconstruction efficiency. Taking a typical spatial single pipeline as the research object, this paper innovatively presents a PFEM method of pipeline system based on the newly constructed nonconforming solid (Solid-NC) element. The stiffness and mass matrices of the spatial 8-node Solid-NC element with second-order boundary accuracy are obtained by introducing the node-free displacement items and statics condensation method. The PFEM method of the pipeline body is proposed by selecting the straight-line segment lengths as the pipeline shape control parameters. The PFEM method of the pipeline is described in detail, including the node coordinate solutions of straight-line and curved arc segments based on the direction vector method and vector decomposition method, respectively, and the simulation of the clamp mechanical properties considering the actual pre-tightening state of the clamp. Furthermore, the modal analysis is carried out, the node stress response solution is solved based on the stress smoothing method, and the effectiveness of the PFEM method is verified through experiment. Finally, the mesh quality and model reconstruction efficiency of the PFEM method is analyzed, the results show that the developed PFEM method has higher mesh quality and fast model reconstruction speed, and the model reconstruction time is shortened by 544.5 times at most compared with ANSYS software.","PeriodicalId":506990,"journal":{"name":"Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2024-02-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139858550","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 : 2024-01-16DOI: 10.1177/09544100241226991
Eiman B Saheby, Xing Shen, Saeed Jowkar
In this study, a new ridge surface is proposed and its impact on the aerodynamic efficiency of a generic top-mounted submerged inlet is investigated at Mach 0.3 to 0.5. The concept is developed to investigate the possibility of vortex breakdown manipulation by the ridge surface to control the chaotic flow pattern after the breakdown, measuring the overall drag increment and total pressure recovery due to the ridge integration. For this purpose, a conceptual submerged inlet is designed with a semi-elliptic entrance for integration with a generic fuselage and ridge surfaces; then different study cases are modeled based on this configuration for numerical simulations by Ansys Fluent. Key factors such as the quality of the captured streamtube, vortex patterns on the fuselage, induced lift, and vortex breakdown patterns are investigated and compared by second order accuracy. Results indicate that the modified ridge surface improves the overall efficiency of the fuselage-inlet configuration both in the terms of lift over drag and pressure recovery.
{"title":"Aerodynamic efficiency analysis of the ridge integrated submerged inlet","authors":"Eiman B Saheby, Xing Shen, Saeed Jowkar","doi":"10.1177/09544100241226991","DOIUrl":"https://doi.org/10.1177/09544100241226991","url":null,"abstract":"In this study, a new ridge surface is proposed and its impact on the aerodynamic efficiency of a generic top-mounted submerged inlet is investigated at Mach 0.3 to 0.5. The concept is developed to investigate the possibility of vortex breakdown manipulation by the ridge surface to control the chaotic flow pattern after the breakdown, measuring the overall drag increment and total pressure recovery due to the ridge integration. For this purpose, a conceptual submerged inlet is designed with a semi-elliptic entrance for integration with a generic fuselage and ridge surfaces; then different study cases are modeled based on this configuration for numerical simulations by Ansys Fluent. Key factors such as the quality of the captured streamtube, vortex patterns on the fuselage, induced lift, and vortex breakdown patterns are investigated and compared by second order accuracy. Results indicate that the modified ridge surface improves the overall efficiency of the fuselage-inlet configuration both in the terms of lift over drag and pressure recovery.","PeriodicalId":506990,"journal":{"name":"Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2024-01-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139528679","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 : 2024-01-13DOI: 10.1177/09544100231219736
Andrews Darfour Kwakye, I. Jennions, Cordelia Mattuvarkuzhali Ezhilarasu
Aircraft health management has been researched at both component and system levels. In instances of certain aircraft faults, like the Boeing 777 fuel icing problem, there is evidence suggesting that a platform approach using an Integrated Vehicle Health Management (IVHM) system could have helped detect faults and their interaction effects earlier, before they became catastrophic. This paper reviews aircraft health management from the aircraft maintenance point of view. It emphasizes the potential of a platform solution to diagnose faults, and their interaction effects, at an early stage. The paper conducts a thorough analysis of existing literature concerning maintenance and its evolution, delves into the application of Artificial Intelligence (AI) techniques in maintenance, explains the rationale behind their employment, and illustrates how AI implementation can enhance fault detection using platform sensor data. Further, it discusses how computational severity and criticality indexes (health indexes) can potentially be complementary to the use of AI for the provision of maintenance information on aircraft components, for assisting operational decisions.
{"title":"Platform health management for aircraft maintenance – a review","authors":"Andrews Darfour Kwakye, I. Jennions, Cordelia Mattuvarkuzhali Ezhilarasu","doi":"10.1177/09544100231219736","DOIUrl":"https://doi.org/10.1177/09544100231219736","url":null,"abstract":"Aircraft health management has been researched at both component and system levels. In instances of certain aircraft faults, like the Boeing 777 fuel icing problem, there is evidence suggesting that a platform approach using an Integrated Vehicle Health Management (IVHM) system could have helped detect faults and their interaction effects earlier, before they became catastrophic. This paper reviews aircraft health management from the aircraft maintenance point of view. It emphasizes the potential of a platform solution to diagnose faults, and their interaction effects, at an early stage. The paper conducts a thorough analysis of existing literature concerning maintenance and its evolution, delves into the application of Artificial Intelligence (AI) techniques in maintenance, explains the rationale behind their employment, and illustrates how AI implementation can enhance fault detection using platform sensor data. Further, it discusses how computational severity and criticality indexes (health indexes) can potentially be complementary to the use of AI for the provision of maintenance information on aircraft components, for assisting operational decisions.","PeriodicalId":506990,"journal":{"name":"Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2024-01-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139531328","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 : 2024-01-02DOI: 10.1177/09544100231225021
Zhiguo Wang, Pei Wang, Jun Liu, Qian Du, Pengfei Wang, Qingzong Xu, Xin Shen, Haohan Wang
Due to the large bending of turbine blades, there is strong three-dimensional flow in cascade channel, the three-dimensional flow at the endwall of blades generates extremely complex heat transfer characteristics. The design concept of high heat load turbine blades, particularly comprehensive optimization of flow and heat transfer at the endwall, has gained increasing attention. In this paper, we have developed a three-dimensional endwall parameterized modeling platform based on Body-Fitting Coordinates and introduced a novel approach for streamwise direction and normal direction concerning endwall profile construction. The endwall modeling was optimized using Genetic Algorithm to obtain a modified one with low heat transfer level on the premise that the aerodynamic loss is not increased. The analysis indicates that the reduction of aerodynamic loss with the modified endwall is relatively marginal, whereas the heat transfer intensity on the endwall surface experiences a significant decrease. Additionally, employing an endwall model can effectively mitigate the lateral pressure gradient in the cascade channel, which exerts a pronounced influence on suppressing secondary vortex development in the cascade.
{"title":"Research on modeling method of non-axisymmetric endwall based on body-fitted coordinates","authors":"Zhiguo Wang, Pei Wang, Jun Liu, Qian Du, Pengfei Wang, Qingzong Xu, Xin Shen, Haohan Wang","doi":"10.1177/09544100231225021","DOIUrl":"https://doi.org/10.1177/09544100231225021","url":null,"abstract":"Due to the large bending of turbine blades, there is strong three-dimensional flow in cascade channel, the three-dimensional flow at the endwall of blades generates extremely complex heat transfer characteristics. The design concept of high heat load turbine blades, particularly comprehensive optimization of flow and heat transfer at the endwall, has gained increasing attention. In this paper, we have developed a three-dimensional endwall parameterized modeling platform based on Body-Fitting Coordinates and introduced a novel approach for streamwise direction and normal direction concerning endwall profile construction. The endwall modeling was optimized using Genetic Algorithm to obtain a modified one with low heat transfer level on the premise that the aerodynamic loss is not increased. The analysis indicates that the reduction of aerodynamic loss with the modified endwall is relatively marginal, whereas the heat transfer intensity on the endwall surface experiences a significant decrease. Additionally, employing an endwall model can effectively mitigate the lateral pressure gradient in the cascade channel, which exerts a pronounced influence on suppressing secondary vortex development in the cascade.","PeriodicalId":506990,"journal":{"name":"Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2024-01-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139452681","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 : 2023-12-26DOI: 10.1177/09544100231223532
Shengwen Xiang, Pei Wang, Ye Yang, Kai Da, Hongqi Fan
Obtaining the probability density distribution of target motion mode is the basis for model set design in multi-model tracking methods. During reentry, the target is expected to perform a violent spiral maneuver due to aerodynamic resonance between roll and pitch modes, the motion of target is highly nonlinear and the spiral frequency is a prior unknown random variable. This paper evaluates the probability distribution of spiral frequency of reentry target under three different types of maneuvering control inputs, which can provide guidelines for the design of model sets. This work is based on the dynamic model of reentry spiral motion presented in this paper, whose effectiveness has been verified by using a large number of Monte Carlo simulations.
{"title":"Motion mode distribution of spiral maneuvering target during reentry phase","authors":"Shengwen Xiang, Pei Wang, Ye Yang, Kai Da, Hongqi Fan","doi":"10.1177/09544100231223532","DOIUrl":"https://doi.org/10.1177/09544100231223532","url":null,"abstract":"Obtaining the probability density distribution of target motion mode is the basis for model set design in multi-model tracking methods. During reentry, the target is expected to perform a violent spiral maneuver due to aerodynamic resonance between roll and pitch modes, the motion of target is highly nonlinear and the spiral frequency is a prior unknown random variable. This paper evaluates the probability distribution of spiral frequency of reentry target under three different types of maneuvering control inputs, which can provide guidelines for the design of model sets. This work is based on the dynamic model of reentry spiral motion presented in this paper, whose effectiveness has been verified by using a large number of Monte Carlo simulations.","PeriodicalId":506990,"journal":{"name":"Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-12-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139156199","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 : 2023-12-26DOI: 10.1177/09544100231220471
Youngshin Kang, Am Cho, Seongwook Choi, Yushin Kim, Jongmin Bae, Junho Cho, Donghyeon Ko, Haneul Yun
The direction of propeller rotation in a distributed electric-powered vertical take-off and landing (eVTOL) aircraft significantly influences control forces and induced drag during both helicopter and fixed-wing modes. This study proposes a strategy to determine the most effective rotational direction for each propeller. This approach effectively mitigates one-engine-inoperative (OEI) conditions during helicopter mode for a subscale eVTOL referred to as the optionally piloted personal air vehicle (OPPAV). Moreover, the study developed an optimal control law using the linear programming method, which minimizes the maximum power required for individual motors under OEI conditions. The lowest maximum power was achieved under OEI conditions when both the front and rear propellers in each pod rotated in the same direction. Furthermore, to validate this proposed control law, a tethered hover test was performed using the subscale OPPAV under OEI conditions. Our findings demonstrate that determining the rotational direction of propellers using the newly proposed reconfiguration control method significantly enhances the safety of eVTOL aircraft operating under OEI conditions.
{"title":"Evaluating one engine inoperative conditions in subscale electric vertical take-off and landing aircraft: An in-depth tethered hover test analysis","authors":"Youngshin Kang, Am Cho, Seongwook Choi, Yushin Kim, Jongmin Bae, Junho Cho, Donghyeon Ko, Haneul Yun","doi":"10.1177/09544100231220471","DOIUrl":"https://doi.org/10.1177/09544100231220471","url":null,"abstract":"The direction of propeller rotation in a distributed electric-powered vertical take-off and landing (eVTOL) aircraft significantly influences control forces and induced drag during both helicopter and fixed-wing modes. This study proposes a strategy to determine the most effective rotational direction for each propeller. This approach effectively mitigates one-engine-inoperative (OEI) conditions during helicopter mode for a subscale eVTOL referred to as the optionally piloted personal air vehicle (OPPAV). Moreover, the study developed an optimal control law using the linear programming method, which minimizes the maximum power required for individual motors under OEI conditions. The lowest maximum power was achieved under OEI conditions when both the front and rear propellers in each pod rotated in the same direction. Furthermore, to validate this proposed control law, a tethered hover test was performed using the subscale OPPAV under OEI conditions. Our findings demonstrate that determining the rotational direction of propellers using the newly proposed reconfiguration control method significantly enhances the safety of eVTOL aircraft operating under OEI conditions.","PeriodicalId":506990,"journal":{"name":"Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-12-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139156313","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 : 2023-12-19DOI: 10.1177/09544100231222035
Hyeong-Geun Kim, Jongho Shin
In this study, we present an optimal guidance structure that achieves impact angle and time constraints for the salvo attack of multiple missiles. As the first step in deriving a guidance law, we define a desired profile of the look angle that satisfies the impact angle and time constraints using a polynomial function of the relative range. The guidance command is configured based on the optimality formulation that achieves the desired profile of the look angle while minimizing the usage of the normal acceleration. The resulting trajectory under the proposed law is expressed as a polynomial form whose exponents can be selected to satisfy the desired constraints with the impact courses of various curvatures. In addition, the proposed law can achieve a wide range of terminal constraints since the time-to-go, which is difficult to estimate for a trajectory with a small radius of curvature, is not required for implementation. The numerical simulation results show that the proposed law achieves precise interception under various terminal conditions, validating the proposed law.
{"title":"Trajectory-shaping guidance based on optimality formulation for cooperative attack of multiple interceptors","authors":"Hyeong-Geun Kim, Jongho Shin","doi":"10.1177/09544100231222035","DOIUrl":"https://doi.org/10.1177/09544100231222035","url":null,"abstract":"In this study, we present an optimal guidance structure that achieves impact angle and time constraints for the salvo attack of multiple missiles. As the first step in deriving a guidance law, we define a desired profile of the look angle that satisfies the impact angle and time constraints using a polynomial function of the relative range. The guidance command is configured based on the optimality formulation that achieves the desired profile of the look angle while minimizing the usage of the normal acceleration. The resulting trajectory under the proposed law is expressed as a polynomial form whose exponents can be selected to satisfy the desired constraints with the impact courses of various curvatures. In addition, the proposed law can achieve a wide range of terminal constraints since the time-to-go, which is difficult to estimate for a trajectory with a small radius of curvature, is not required for implementation. The numerical simulation results show that the proposed law achieves precise interception under various terminal conditions, validating the proposed law.","PeriodicalId":506990,"journal":{"name":"Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-12-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139171651","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 : 2023-12-15DOI: 10.1177/09544100231219922
Jiang Shao, Qingrui Zhou, Yan Xiao, Franco Bernelli-Zazzera, Zhaowei Sun
This work proposes a saturation control scheme for underactuated spacecraft formation reconfiguration in elliptic orbits without radial or along-track thrust. Firstly, the rank criterion method is applied to analyze the controllability and feasibility of formation reconfiguration by linearizing the linear time-varying dynamics to linear time-invariant ones. Based on the inherent coupling of the linear time-varying system, the underactuated error dynamics are presented for either underactuated case. Subsequently, the developed underactuated saturation controller can ensure that the time-varying system trajectory asymptotically converges to the specified configuration. The Lyapunov-based analysis presents the constraint conditions of controller parameters and the stable reconfiguration accuracy of the system states. Finally, numerical simulations for both underactuated scenarios are performed in the environment with J2 perturbation to verify the validity of the proposed underactuated control scheme.
{"title":"Feasibility analysis and saturation control for underactuated spacecraft formation reconfiguration in elliptic orbits","authors":"Jiang Shao, Qingrui Zhou, Yan Xiao, Franco Bernelli-Zazzera, Zhaowei Sun","doi":"10.1177/09544100231219922","DOIUrl":"https://doi.org/10.1177/09544100231219922","url":null,"abstract":"This work proposes a saturation control scheme for underactuated spacecraft formation reconfiguration in elliptic orbits without radial or along-track thrust. Firstly, the rank criterion method is applied to analyze the controllability and feasibility of formation reconfiguration by linearizing the linear time-varying dynamics to linear time-invariant ones. Based on the inherent coupling of the linear time-varying system, the underactuated error dynamics are presented for either underactuated case. Subsequently, the developed underactuated saturation controller can ensure that the time-varying system trajectory asymptotically converges to the specified configuration. The Lyapunov-based analysis presents the constraint conditions of controller parameters and the stable reconfiguration accuracy of the system states. Finally, numerical simulations for both underactuated scenarios are performed in the environment with J2 perturbation to verify the validity of the proposed underactuated control scheme.","PeriodicalId":506990,"journal":{"name":"Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-12-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139178125","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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