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2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics最新文献

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Sliding mode control of a microsatellite attitude 微卫星姿态的滑模控制
2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics Pub Date : 2010-06-08 DOI: 10.1109/ISSCAA.2010.5633071
H. Nemati, M. Bahrami, B. Ebrahimi
{"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}
引用次数: 2
A real-time simulation system for satellite based on RTW and VxWorks 基于RTW和VxWorks的卫星实时仿真系统
2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics Pub Date : 2010-06-08 DOI: 10.1109/ISSCAA.2010.5633094
Erjian Shen, Zhang Tao, Liangwei Huang, Bin Liang, Jingyan Song
{"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}
引用次数: 1
Active flutter suppression for a 2-D supersonic airfoil with nonlinear stiffness 具有非线性刚度的二维超音速翼型颤振主动抑制
2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics Pub Date : 2010-06-08 DOI: 10.1109/ISSCAA.2010.5632395
N. Zhao, D. Cao, Hongyang Gao
{"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}
引用次数: 10
Research on fire algorithm of pulse thrusters for interceptor missile 拦截导弹脉冲推力器点火算法研究
2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics Pub Date : 2010-06-08 DOI: 10.1109/ISSCAA.2010.5633143
Yongxin Yin, Zhongming Ou, Wen Shi
{"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}
引用次数: 0
The research of bi-elliptic flyaround maneuver 双椭圆绕飞机动的研究
2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics Pub Date : 2010-06-08 DOI: 10.1109/ISSCAA.2010.5632537
Zhao Hui, Liu Xinglong, Yang Baoqing
{"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}
引用次数: 0
Research on modeling and model solving method for multifield/multidisciplinary coupling for flight vehicle 飞行器多领域/多学科耦合建模及模型求解方法研究
2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics Pub Date : 2010-06-08 DOI: 10.1109/ISSCAA.2010.5633262
Ma Ping, Chao Tao, Yang Ming
{"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}
引用次数: 0
Numerical simulation of parallel turbo-ramjet combined cycle propulsion system installed performance 并联涡轮-冲压发动机联合循环推进系统安装性能的数值模拟
2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics Pub Date : 2010-06-08 DOI: 10.1109/ISSCAA.2010.5633031
Yongsheng Wang, Zhanxue Wang, Zeng-wen Liu, Huimin Ma
{"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}
引用次数: 0
Research on particle filter based geomagnetic aided inertial navigation algorithm 基于粒子滤波的地磁辅助惯性导航算法研究
2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics Pub Date : 2010-06-08 DOI: 10.1109/ISSCAA.2010.5632732
Ming Liu, Haijun Wang, Qingye Guo, Xiaoxiong Jiang
{"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}
引用次数: 2
Design and development of autonomous driving vehicle 自动驾驶汽车的设计与开发
2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics Pub Date : 2010-06-08 DOI: 10.1109/ISSCAA.2010.5632897
Meng Gao, K. He, Huaping Liu, F. Sun
{"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}
引用次数: 1
Vibration control of flexible satellites using a new isolator 基于新型隔振器的柔性卫星振动控制
2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics Pub Date : 2010-06-08 DOI: 10.1109/ISSCAA.2010.5632871
Fang Liu, B. Fang, Wenhu Huang
{"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}
引用次数: 5
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