Pub Date : 2010-06-08DOI: 10.1109/ISSCAA.2010.5633071
H. Nemati, M. Bahrami, B. Ebrahimi
Attitude control of a micro-satellite is analyzed with sliding control method. With this method, attitude dynamics of satellite is robust against uncertainties and unknown disturbances. Nonlinear and coupled model in this paper is utilized and to prevent chattering, saturation functions are invoked. The gravity gradient as a disturbance is applied. The sliding approach is applied to the SSETI/ESEO micro-satellite, initiated by the European Space Agency (ESA). The effectiveness of the controller is demonstrated through simulations.
{"title":"Sliding mode control of a microsatellite attitude","authors":"H. Nemati, M. Bahrami, B. Ebrahimi","doi":"10.1109/ISSCAA.2010.5633071","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633071","url":null,"abstract":"Attitude control of a micro-satellite is analyzed with sliding control method. With this method, attitude dynamics of satellite is robust against uncertainties and unknown disturbances. Nonlinear and coupled model in this paper is utilized and to prevent chattering, saturation functions are invoked. The gravity gradient as a disturbance is applied. The sliding approach is applied to the SSETI/ESEO micro-satellite, initiated by the European Space Agency (ESA). The effectiveness of the controller is demonstrated through simulations.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"49 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125436471","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 : 2010-06-08DOI: 10.1109/ISSCAA.2010.5633094
Erjian Shen, Zhang Tao, Liangwei Huang, Bin Liang, Jingyan Song
A new real-time simulation system is developed based on the Real Time Workshop (RTW) and real-time operation system VxWorks. The whole model of satellite is defined, which is proved by simulation in Simulink. This model is divided into two parts. One part is the attitude and orbit controller, i.e., attitude and orbit control system (AOCS), named AOCS model. The other is the external model of AOCS, named external model. The CAN bus interface blocks are designed for the two parts, respectively. The compiled codes of the two models are downloaded to two target computers with VxWorks for real-time simulation, which are connected by CAN bus. In addition, a method is proposed to verify the availability of the model in VxWorks, although not all blocks in Simulink can be implemented in VxWorks. This proposed method is compared by the simulation results of simulation in the Simulink and VxWorks. A simulation example is developed to test the availability and reliability of the system.
{"title":"A real-time simulation system for satellite based on RTW and VxWorks","authors":"Erjian Shen, Zhang Tao, Liangwei Huang, Bin Liang, Jingyan Song","doi":"10.1109/ISSCAA.2010.5633094","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633094","url":null,"abstract":"A new real-time simulation system is developed based on the Real Time Workshop (RTW) and real-time operation system VxWorks. The whole model of satellite is defined, which is proved by simulation in Simulink. This model is divided into two parts. One part is the attitude and orbit controller, i.e., attitude and orbit control system (AOCS), named AOCS model. The other is the external model of AOCS, named external model. The CAN bus interface blocks are designed for the two parts, respectively. The compiled codes of the two models are downloaded to two target computers with VxWorks for real-time simulation, which are connected by CAN bus. In addition, a method is proposed to verify the availability of the model in VxWorks, although not all blocks in Simulink can be implemented in VxWorks. This proposed method is compared by the simulation results of simulation in the Simulink and VxWorks. A simulation example is developed to test the availability and reliability of the system.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"74 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121014927","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 : 2010-06-08DOI: 10.1109/ISSCAA.2010.5632395
N. Zhao, D. Cao, Hongyang Gao
A 3-DOF dynamic model is used for a 2-D airfoil with a control surface. The cubic nonlinear structural stiffness is considered in this model, and the aerodynamic load in the supersonic airflow is obtained by 3rd order Piston Theory. Nonlinear flutter happens with a phenomenon of limit cycle oscillations (LCOs) when the flight speed reaches the critical speed. The LQR approach is employed to design a control law to increase the critical speed of aerodynamic flutter. And then a combined control law is proposed in order to reduce the amplitude of LCOs by adding the cubic nonlinear feedback control. The dynamic responses of controlled system are given and used to compare with those of the uncontrolled system. Results of simulation show that the active flutter suppression method proposed here is effective.
{"title":"Active flutter suppression for a 2-D supersonic airfoil with nonlinear stiffness","authors":"N. Zhao, D. Cao, Hongyang Gao","doi":"10.1109/ISSCAA.2010.5632395","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5632395","url":null,"abstract":"A 3-DOF dynamic model is used for a 2-D airfoil with a control surface. The cubic nonlinear structural stiffness is considered in this model, and the aerodynamic load in the supersonic airflow is obtained by 3rd order Piston Theory. Nonlinear flutter happens with a phenomenon of limit cycle oscillations (LCOs) when the flight speed reaches the critical speed. The LQR approach is employed to design a control law to increase the critical speed of aerodynamic flutter. And then a combined control law is proposed in order to reduce the amplitude of LCOs by adding the cubic nonlinear feedback control. The dynamic responses of controlled system are given and used to compare with those of the uncontrolled system. Results of simulation show that the active flutter suppression method proposed here is effective.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"32 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128112571","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 : 2010-06-08DOI: 10.1109/ISSCAA.2010.5633143
Yongxin Yin, Zhongming Ou, Wen Shi
In order to ensure the control precision of lateral thrust for interceptor missile, a new fire algorithm of pulse thrusters is presented. With a view to defect of lateral thrust from spinning interceptor missile, a method to search fire direction and fire quantity of pulse thrusters is presented. And improved genetic algorithm is given. In this improved genetic algorithm, the genetic operation is amended to overcome the local optimization in simple genetic algorithm. According to an improved genetic algorithm, the fire quantity of pulse thrusters is optimized, and the track error of fire command is compensated to ensure the control precision of lateral thrust. Simulation results show that this fire algorithm can implement efficiently control mission of lateral thrust for interceptor missile as well as preferable performance.
{"title":"Research on fire algorithm of pulse thrusters for interceptor missile","authors":"Yongxin Yin, Zhongming Ou, Wen Shi","doi":"10.1109/ISSCAA.2010.5633143","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633143","url":null,"abstract":"In order to ensure the control precision of lateral thrust for interceptor missile, a new fire algorithm of pulse thrusters is presented. With a view to defect of lateral thrust from spinning interceptor missile, a method to search fire direction and fire quantity of pulse thrusters is presented. And improved genetic algorithm is given. In this improved genetic algorithm, the genetic operation is amended to overcome the local optimization in simple genetic algorithm. According to an improved genetic algorithm, the fire quantity of pulse thrusters is optimized, and the track error of fire command is compensated to ensure the control precision of lateral thrust. Simulation results show that this fire algorithm can implement efficiently control mission of lateral thrust for interceptor missile as well as preferable performance.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"81 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126009979","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 : 2010-06-08DOI: 10.1109/ISSCAA.2010.5632537
Zhao Hui, Liu Xinglong, Yang Baoqing
The flyaround maneuvers have a broad application prospects in the future space activities. In this paper, a coplanar bi-elliptic flyaround maneuver by impulsive thrust control is discussed; the necessary conditions of the bi-elliptic flyaround formation are deduced based on the Hill's equation. Simulation results verify the superiority of the bi-elliptic flyaround maneuver compared with the natural flyaround maneuver.
{"title":"The research of bi-elliptic flyaround maneuver","authors":"Zhao Hui, Liu Xinglong, Yang Baoqing","doi":"10.1109/ISSCAA.2010.5632537","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5632537","url":null,"abstract":"The flyaround maneuvers have a broad application prospects in the future space activities. In this paper, a coplanar bi-elliptic flyaround maneuver by impulsive thrust control is discussed; the necessary conditions of the bi-elliptic flyaround formation are deduced based on the Hill's equation. Simulation results verify the superiority of the bi-elliptic flyaround maneuver compared with the natural flyaround maneuver.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"94 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126431283","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 : 2010-06-08DOI: 10.1109/ISSCAA.2010.5633262
Ma Ping, Chao Tao, Yang Ming
In order to get a deep insight into the multifield/multidisciplinary coupling mechanism of high speed flight vehicle, modeling and model solving methods for the multifield/multidisciplinary coupling problem of high speed flight vehicle is presented. Firstly the characteristics of the multifield/ multidisciplinary coupling are analyzed. Then the demands on the modeling and simulating for the problem are provided. Finally the main coupling relationships among aerodynamics, structure, heat transfer, and control field are analyzed, and the solving methods and process for the coupled models are presented.
{"title":"Research on modeling and model solving method for multifield/multidisciplinary coupling for flight vehicle","authors":"Ma Ping, Chao Tao, Yang Ming","doi":"10.1109/ISSCAA.2010.5633262","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633262","url":null,"abstract":"In order to get a deep insight into the multifield/multidisciplinary coupling mechanism of high speed flight vehicle, modeling and model solving methods for the multifield/multidisciplinary coupling problem of high speed flight vehicle is presented. Firstly the characteristics of the multifield/ multidisciplinary coupling are analyzed. Then the demands on the modeling and simulating for the problem are provided. Finally the main coupling relationships among aerodynamics, structure, heat transfer, and control field are analyzed, and the solving methods and process for the coupled models are presented.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"25 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125119993","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 : 2010-06-08DOI: 10.1109/ISSCAA.2010.5633031
Yongsheng Wang, Zhanxue Wang, Zeng-wen Liu, Huimin Ma
To investigate the installed performance of turbine based combined cycle engines, parallel configuration was selected as a turbo-ramjet engine. Work process and selection of transition Mach number of turbo-ramjet were described. Both installed losses and installed performance computational model were established. Accordingly, the installed performance characteristics of turbofan-ramjet were simulated by numerical methods on basis of this model. As the numerical simulation results, in transonic and low supersonic conditions, installation losses are larger than other conditions, and the installed thrust which is continuous during the process of mode transition is decreased along flight trajectory. The specific fuel consumption is increased in trend while the specific impulse which is decreased in trend along the flight trajectory. The simulation results show that the installed performance is acceptable and considerable. In conclusion, we state that the scheme design of parallel configuration of turbo-ramjet engine is reasonable and feasible.
{"title":"Numerical simulation of parallel turbo-ramjet combined cycle propulsion system installed performance","authors":"Yongsheng Wang, Zhanxue Wang, Zeng-wen Liu, Huimin Ma","doi":"10.1109/ISSCAA.2010.5633031","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5633031","url":null,"abstract":"To investigate the installed performance of turbine based combined cycle engines, parallel configuration was selected as a turbo-ramjet engine. Work process and selection of transition Mach number of turbo-ramjet were described. Both installed losses and installed performance computational model were established. Accordingly, the installed performance characteristics of turbofan-ramjet were simulated by numerical methods on basis of this model. As the numerical simulation results, in transonic and low supersonic conditions, installation losses are larger than other conditions, and the installed thrust which is continuous during the process of mode transition is decreased along flight trajectory. The specific fuel consumption is increased in trend while the specific impulse which is decreased in trend along the flight trajectory. The simulation results show that the installed performance is acceptable and considerable. In conclusion, we state that the scheme design of parallel configuration of turbo-ramjet engine is reasonable and feasible.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"6 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123696313","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 : 2010-06-08DOI: 10.1109/ISSCAA.2010.5632732
Ming Liu, Haijun Wang, Qingye Guo, Xiaoxiong Jiang
Inertial navigation system is an autonomous navigation system, but there exists error accumulation. The geomagnetic navigation has the features of long-term stability. In order to solve the problem that the inertial navigation system has accumulated errors, the geomagnetic information is introduced in this paper. Based on the actual situation, the geomagnetic aided inertial navigation system error model is established firstly. Because there is nonlinear problem in this system, the particle filter which is a new nonlinear filtering algorithm is applied to the geomagnetic aided inertial navigation system, and a simulation analysis is done. Simulation results show that, compared with the EKF algorithm, due to the particle filter algorithm has no linearization part, the navigation precision of particle filter based geomagnetic aided inertial navigation system can be enhanced.
{"title":"Research on particle filter based geomagnetic aided inertial navigation algorithm","authors":"Ming Liu, Haijun Wang, Qingye Guo, Xiaoxiong Jiang","doi":"10.1109/ISSCAA.2010.5632732","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5632732","url":null,"abstract":"Inertial navigation system is an autonomous navigation system, but there exists error accumulation. The geomagnetic navigation has the features of long-term stability. In order to solve the problem that the inertial navigation system has accumulated errors, the geomagnetic information is introduced in this paper. Based on the actual situation, the geomagnetic aided inertial navigation system error model is established firstly. Because there is nonlinear problem in this system, the particle filter which is a new nonlinear filtering algorithm is applied to the geomagnetic aided inertial navigation system, and a simulation analysis is done. Simulation results show that, compared with the EKF algorithm, due to the particle filter algorithm has no linearization part, the navigation precision of particle filter based geomagnetic aided inertial navigation system can be enhanced.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"9 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123736320","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 : 2010-06-08DOI: 10.1109/ISSCAA.2010.5632897
Meng Gao, K. He, Huaping Liu, F. Sun
In this paper, a new type of autonomous vehicle is developed. This vehicle consists of three sets of control systems to regulate the direction, brake and fuels. The sensing system is a combination of laser radar and camera. The localization system is constructed with GPS device and electronically compass. Currently, three tasks, including lane detection and following, object detection, and obstacle avoidance, has been implemented on this platform. We reported some experimental results.
{"title":"Design and development of autonomous driving vehicle","authors":"Meng Gao, K. He, Huaping Liu, F. Sun","doi":"10.1109/ISSCAA.2010.5632897","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5632897","url":null,"abstract":"In this paper, a new type of autonomous vehicle is developed. This vehicle consists of three sets of control systems to regulate the direction, brake and fuels. The sensing system is a combination of laser radar and camera. The localization system is constructed with GPS device and electronically compass. Currently, three tasks, including lane detection and following, object detection, and obstacle avoidance, has been implemented on this platform. We reported some experimental results.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"27 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121648109","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 : 2010-06-08DOI: 10.1109/ISSCAA.2010.5632871
Fang Liu, B. Fang, Wenhu Huang
As an effective means of separating the vibration transmitted from rocket to satellite, the Whole-Spacecraft Vibration Isolation (WSVI) has been widely studied and applied in the past 20 years. Based on a new Circular Payload Adapter Fitting (CPAF), this paper studied the vibration principles of the CPAF and established corresponding vibration isolation model. With the piezoelectric stack actuators, integrated passive and active vibration control was achieved based on passive vibration control. Model simulation results show that the CPAF has good vibration isolation performance, and could reduce the vibration transmitted from rocket to satellite in a wide frequency band.
{"title":"Vibration control of flexible satellites using a new isolator","authors":"Fang Liu, B. Fang, Wenhu Huang","doi":"10.1109/ISSCAA.2010.5632871","DOIUrl":"https://doi.org/10.1109/ISSCAA.2010.5632871","url":null,"abstract":"As an effective means of separating the vibration transmitted from rocket to satellite, the Whole-Spacecraft Vibration Isolation (WSVI) has been widely studied and applied in the past 20 years. Based on a new Circular Payload Adapter Fitting (CPAF), this paper studied the vibration principles of the CPAF and established corresponding vibration isolation model. With the piezoelectric stack actuators, integrated passive and active vibration control was achieved based on passive vibration control. Model simulation results show that the CPAF has good vibration isolation performance, and could reduce the vibration transmitted from rocket to satellite in a wide frequency band.","PeriodicalId":324652,"journal":{"name":"2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics","volume":"109 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124763745","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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