Pub Date : 2021-10-01DOI: 10.1109/ICMEAS54189.2021.00027
Wenqiang Yin, Yalong Wang
Based on its advantages of wide application fields, low manufacturing cost and long working hours, the mission demand of large civilian UAVs in the market is expanding, and their usage patterns and safety features have become the future development direction, which has put forward higher requirements on the autonomous capability of UAVs. Carrying out the autonomous capability assessment of large civil UAVs is of great significance to their market positioning and application scenarios. In this paper, an autonomous capability assessment method is proposed for large civil UAVs. The method classifies the autonomous capability level of large civil UAVs, then sorts out the autonomous capability evaluation elements, and finally determines the autonomous capability flight test verification content and formulates corresponding assessment guidelines, which can provide guidance for the autonomous capability assessment of large civil UAVs and that can also provide guidance for other types of UAVs.
{"title":"Research on autonomous capability assessment technology for large civilian UAVs","authors":"Wenqiang Yin, Yalong Wang","doi":"10.1109/ICMEAS54189.2021.00027","DOIUrl":"https://doi.org/10.1109/ICMEAS54189.2021.00027","url":null,"abstract":"Based on its advantages of wide application fields, low manufacturing cost and long working hours, the mission demand of large civilian UAVs in the market is expanding, and their usage patterns and safety features have become the future development direction, which has put forward higher requirements on the autonomous capability of UAVs. Carrying out the autonomous capability assessment of large civil UAVs is of great significance to their market positioning and application scenarios. In this paper, an autonomous capability assessment method is proposed for large civil UAVs. The method classifies the autonomous capability level of large civil UAVs, then sorts out the autonomous capability evaluation elements, and finally determines the autonomous capability flight test verification content and formulates corresponding assessment guidelines, which can provide guidance for the autonomous capability assessment of large civil UAVs and that can also provide guidance for other types of UAVs.","PeriodicalId":374943,"journal":{"name":"2021 7th International Conference on Mechanical Engineering and Automation Science (ICMEAS)","volume":"22 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134158945","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 : 2021-10-01DOI: 10.1109/icmeas54189.2021.00036
Zhihong Yan, X. Sui
In order to explore the correlation between the characteristic peaks of infrared absorption spectrum and the maximum elongation of HTPB propellant, the tensile test and Fourier infrared spectrum test of HTPB propellant after accelerated aging at 50 centigrade,60 centigrade and 70 centigrade were carried out. S-G smoothing filtering method and derivative spectrum method were used to process the infrared spectrum data, and the correlation between the infrared spectrum data and the maximum elongation was analyzed. The results show that the characteristic peak wave number of infrared absorption spectrum is highly related to the maximum elongation, and the fitting formula between the characteristic peak of infrared absorption spectrum and the maximum elongation is established at the wave number 1785cm-l; It was found that the maximum elongation of HTPB propellant decreases first in the aging process, then after a plateau period or rising period, and finally maintains a downward trend.
{"title":"Study on the correlation between characteristic peaks of infrared absorption spectra and maximum elongation of HTPB propellant","authors":"Zhihong Yan, X. Sui","doi":"10.1109/icmeas54189.2021.00036","DOIUrl":"https://doi.org/10.1109/icmeas54189.2021.00036","url":null,"abstract":"In order to explore the correlation between the characteristic peaks of infrared absorption spectrum and the maximum elongation of HTPB propellant, the tensile test and Fourier infrared spectrum test of HTPB propellant after accelerated aging at 50 centigrade,60 centigrade and 70 centigrade were carried out. S-G smoothing filtering method and derivative spectrum method were used to process the infrared spectrum data, and the correlation between the infrared spectrum data and the maximum elongation was analyzed. The results show that the characteristic peak wave number of infrared absorption spectrum is highly related to the maximum elongation, and the fitting formula between the characteristic peak of infrared absorption spectrum and the maximum elongation is established at the wave number 1785cm-l; It was found that the maximum elongation of HTPB propellant decreases first in the aging process, then after a plateau period or rising period, and finally maintains a downward trend.","PeriodicalId":374943,"journal":{"name":"2021 7th International Conference on Mechanical Engineering and Automation Science (ICMEAS)","volume":"104 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133151225","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 : 2021-10-01DOI: 10.1109/icmeas54189.2021.00050
Zhanbin Fan, Jiang Luo, Yuan Zhang, Q. Bian, Z. Liang, Wubo Huang, Bingtian Jie
At present, the fire extinguisher used in manned spacecraft has some problems that are difficult to solve. For example, the use of carbon dioxide in a narrow and closed environment has a great impact on the air quality of small space, and the medium after combustion in microgravity environment is scattered everywhere. The above problems can be solved by a kind of suction technology for negative pressure. In this paper, a vacuum lire suction experimental device is designed to meet the requirements of spacecraft lire suppression. The typical fire suppression process of spacecraft by vacuum lire suction technology is studied, which provides data support for the practical application of vacuum fire suction technology in manned spacecraft.
{"title":"Research on Vacuum Fire Absorption Technology for Manned Spacecraft","authors":"Zhanbin Fan, Jiang Luo, Yuan Zhang, Q. Bian, Z. Liang, Wubo Huang, Bingtian Jie","doi":"10.1109/icmeas54189.2021.00050","DOIUrl":"https://doi.org/10.1109/icmeas54189.2021.00050","url":null,"abstract":"At present, the fire extinguisher used in manned spacecraft has some problems that are difficult to solve. For example, the use of carbon dioxide in a narrow and closed environment has a great impact on the air quality of small space, and the medium after combustion in microgravity environment is scattered everywhere. The above problems can be solved by a kind of suction technology for negative pressure. In this paper, a vacuum lire suction experimental device is designed to meet the requirements of spacecraft lire suppression. The typical fire suppression process of spacecraft by vacuum lire suction technology is studied, which provides data support for the practical application of vacuum fire suction technology in manned spacecraft.","PeriodicalId":374943,"journal":{"name":"2021 7th International Conference on Mechanical Engineering and Automation Science (ICMEAS)","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133277009","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 : 2021-10-01DOI: 10.1109/icmeas54189.2021.00040
D. Tiniakov, L. Makarova, O. Dveirin
For the transport category aircraft variants creation there are some ways. They are: keeping constant area and other geometric parameters of a wing and solve this task by the serious modification of a powerplant; modifying area and geometric parameters of a wing for an existing powerplant. Both of these ways have their own advantages, but in time for their realization there are some problems: excessive growth of new variant airplanes’ takeoff weight; possible derating of the takeoff and landing performance for a new airplane’s variant; derating of the fuel efficiency and other integral airplane’s performances that are reasons for the decreasing of the new variant’s competitive. The best performance of the new variant airplane can be obtained only at one condition: these changes are created synchronously and consistently. In the article the way of such changes coordination for increasing cargo capacity, flight range and fuel efficiency of new aircraft variant was created. The main specific of the proposed way is modification changes of a wing geometric parameters are providing of the decreasing its inductive drag for given lift. The model of design changes influence of wing geometric parameters such as taper ratio and local chords twist angle that are depending on elliptical factor of taper wing, to wings polar graph and its lift-to-drag ratio are proposed. Step-by-step evaluation for aerodynamic quality dependence on required values of lift coefficient CL and specific lift coefficient $overline{C}_{L}$ are given. CL and $overline{C}_{L}$ depend on coordination of modification changes for a wing and powerplant performance. The scope of lift-to-drag ratio $K(C_{L})$ for possible applying of required cargo capacity increasing was determined. Obtained results that relate to simulation of geometric wing changes are inherent part of the deep modification changes coordination for a wing and powerplant, which are needed for new aircraft variant creation with higher productivity.
{"title":"Analysis Of The Wings And Powerplant Changes At The Time Of Civil Aircraft Variant Development","authors":"D. Tiniakov, L. Makarova, O. Dveirin","doi":"10.1109/icmeas54189.2021.00040","DOIUrl":"https://doi.org/10.1109/icmeas54189.2021.00040","url":null,"abstract":"For the transport category aircraft variants creation there are some ways. They are: keeping constant area and other geometric parameters of a wing and solve this task by the serious modification of a powerplant; modifying area and geometric parameters of a wing for an existing powerplant. Both of these ways have their own advantages, but in time for their realization there are some problems: excessive growth of new variant airplanes’ takeoff weight; possible derating of the takeoff and landing performance for a new airplane’s variant; derating of the fuel efficiency and other integral airplane’s performances that are reasons for the decreasing of the new variant’s competitive. The best performance of the new variant airplane can be obtained only at one condition: these changes are created synchronously and consistently. In the article the way of such changes coordination for increasing cargo capacity, flight range and fuel efficiency of new aircraft variant was created. The main specific of the proposed way is modification changes of a wing geometric parameters are providing of the decreasing its inductive drag for given lift. The model of design changes influence of wing geometric parameters such as taper ratio and local chords twist angle that are depending on elliptical factor of taper wing, to wings polar graph and its lift-to-drag ratio are proposed. Step-by-step evaluation for aerodynamic quality dependence on required values of lift coefficient CL and specific lift coefficient $overline{C}_{L}$ are given. CL and $overline{C}_{L}$ depend on coordination of modification changes for a wing and powerplant performance. The scope of lift-to-drag ratio $K(C_{L})$ for possible applying of required cargo capacity increasing was determined. Obtained results that relate to simulation of geometric wing changes are inherent part of the deep modification changes coordination for a wing and powerplant, which are needed for new aircraft variant creation with higher productivity.","PeriodicalId":374943,"journal":{"name":"2021 7th International Conference on Mechanical Engineering and Automation Science (ICMEAS)","volume":"7 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122401733","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 : 2021-10-01DOI: 10.1109/icmeas54189.2021.00052
Zeng Wei-yi, Zhao Zhong-liang, Yang Hai-yong, Wang Xiao-bin
With the development of modern air combat and the intensification of military confrontation, modern battlefields have put forward higher demands for the lift and drag characteristics and stealth characteristics of fighters. Because the configuration of flying wing with low aspect ratio removes the tail wing and adopts the wing body fusion design, its lift and drag characteristics and stealth are significantly better than the traditional configuration of wing body separation body. The configuration of flying wing with low aspect ratio has been widely concerned by aviation scientists from various countries and has been determined as the development direction of the future fighter configuration. Aircraft often fly at different speeds on the battlefield. Therefore, it is important to investigate the influence of different incoming flow speeds on the aerodynamic force of flying wing with low aspect ratio and to conduct mechanism analysis. In order to explore the influence of different incoming velocity on the aerodynamic coefficients of the configuration of flying wing with low aspect ratio and the underlying mechanism, the FL-24 wind tunnel of the China Aerodynamics Research and Development Center High Speed Institute conducted a test of the standard model of the flying wing with low aspect ratio. The test with flow Mach number of 0.4, 0.6, 0.8 obtained the normal force coefficient curve and found that the normal force coefficient decreases with the increase of Mach number at high angles of attack. The IDDES turbulence model is used to numerically calculate the standard mode, and the specific flow field details are obtained to explain the flow mechanism behind the phenomenon.
{"title":"The Impact and Mechanism Analysis of Effect of Incoming Flow Velocity on Aerodynamic of Flying Wing Model with Low Aspect Ratio","authors":"Zeng Wei-yi, Zhao Zhong-liang, Yang Hai-yong, Wang Xiao-bin","doi":"10.1109/icmeas54189.2021.00052","DOIUrl":"https://doi.org/10.1109/icmeas54189.2021.00052","url":null,"abstract":"With the development of modern air combat and the intensification of military confrontation, modern battlefields have put forward higher demands for the lift and drag characteristics and stealth characteristics of fighters. Because the configuration of flying wing with low aspect ratio removes the tail wing and adopts the wing body fusion design, its lift and drag characteristics and stealth are significantly better than the traditional configuration of wing body separation body. The configuration of flying wing with low aspect ratio has been widely concerned by aviation scientists from various countries and has been determined as the development direction of the future fighter configuration. Aircraft often fly at different speeds on the battlefield. Therefore, it is important to investigate the influence of different incoming flow speeds on the aerodynamic force of flying wing with low aspect ratio and to conduct mechanism analysis. In order to explore the influence of different incoming velocity on the aerodynamic coefficients of the configuration of flying wing with low aspect ratio and the underlying mechanism, the FL-24 wind tunnel of the China Aerodynamics Research and Development Center High Speed Institute conducted a test of the standard model of the flying wing with low aspect ratio. The test with flow Mach number of 0.4, 0.6, 0.8 obtained the normal force coefficient curve and found that the normal force coefficient decreases with the increase of Mach number at high angles of attack. The IDDES turbulence model is used to numerically calculate the standard mode, and the specific flow field details are obtained to explain the flow mechanism behind the phenomenon.","PeriodicalId":374943,"journal":{"name":"2021 7th International Conference on Mechanical Engineering and Automation Science (ICMEAS)","volume":"26 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114627638","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 : 2021-10-01DOI: 10.1109/ICMEAS54189.2021.00041
Bahador Beigomi, Dan Zhang
In this paper, a strategy to accomplish small stone carving operations using a four-degree-of-freedom (DOF) robotic arm is presented. This research work tries to design a novel robotic arm that is small enough that can be mounted on the table and create artwork by carving and shaping stones. In the past two decades, there were many different designs for the robotic arm from simple 3DoF serial manipulator to advanced hybrid one, but the main thing in those designs was that they have been designed in order to use on an industrial scale. In this design what we have considered as a priority is to create a manipulator that can be mounted on a small table and also could be used by nonprofessionals. The designed robot, CarveARM, has a unique End Effector (EE) which is rotating around itself so fast to carve a stone precisely. At first, by gathering the link transformation matrices between each joint and also using the Denavit-Hartenberg (DH) notations the CarveARM manipulator coordinate transformation is completely described. We have also used some robotics methods to achieve some particular tasks such as solving the forward kinematics description, inverse kinematics problem, workspace evaluation, and dexterity analysis. Besides the position control of EE, we also control the final angle of EE to handle the stone carving procedure more accurately.
{"title":"Mechanical Design of a Novel 4DOF Serial Manipulator","authors":"Bahador Beigomi, Dan Zhang","doi":"10.1109/ICMEAS54189.2021.00041","DOIUrl":"https://doi.org/10.1109/ICMEAS54189.2021.00041","url":null,"abstract":"In this paper, a strategy to accomplish small stone carving operations using a four-degree-of-freedom (DOF) robotic arm is presented. This research work tries to design a novel robotic arm that is small enough that can be mounted on the table and create artwork by carving and shaping stones. In the past two decades, there were many different designs for the robotic arm from simple 3DoF serial manipulator to advanced hybrid one, but the main thing in those designs was that they have been designed in order to use on an industrial scale. In this design what we have considered as a priority is to create a manipulator that can be mounted on a small table and also could be used by nonprofessionals. The designed robot, CarveARM, has a unique End Effector (EE) which is rotating around itself so fast to carve a stone precisely. At first, by gathering the link transformation matrices between each joint and also using the Denavit-Hartenberg (DH) notations the CarveARM manipulator coordinate transformation is completely described. We have also used some robotics methods to achieve some particular tasks such as solving the forward kinematics description, inverse kinematics problem, workspace evaluation, and dexterity analysis. Besides the position control of EE, we also control the final angle of EE to handle the stone carving procedure more accurately.","PeriodicalId":374943,"journal":{"name":"2021 7th International Conference on Mechanical Engineering and Automation Science (ICMEAS)","volume":"33 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125637900","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 : 2021-10-01DOI: 10.1109/icmeas54189.2021.00015
Weiqi Xie, Long Cheng, Yan Li, Jingwei Jingwei-An
Based on the feasibility of the pre-launch attitude composite control method based on grid rudder+RCS (Reaction Control System), the anti-interference ability of the single channel and three channel pre-launch attitude composite control methods is analyse by adding interference torque. The results show that the pre-launch attitude composite control method has strong anti-interference ability and can complete the attitude control task of the launch vehicle. The robustness of the composite control method is analysed by introducing the environmental error and aerodynamic coefficient error to simulate the atmospheric environment change of the rocket in the real environment. The results show that the composite control method has good robustness to the atmospheric density change and aerodynamic coefficient error within the control capability range, which further verifies the feasibility and effectiveness of the method. At the same time, the pre-launch attitude composite control method based on grid rudder+RCS is compared with the more mature stable parachute control method and “stable parachute+control platform” control method. The results show that the designed composite scheme has obvious advantages in control accuracy and control speed, and not only realizes three channel closed-loop active control; It can also reduce the height and speed loss of the arrow body, and clarify the advantages of the composite control method.
{"title":"Performance Analysis of Pre-launch Attitude Compound Control Method Based on Grid Rudder and RCS","authors":"Weiqi Xie, Long Cheng, Yan Li, Jingwei Jingwei-An","doi":"10.1109/icmeas54189.2021.00015","DOIUrl":"https://doi.org/10.1109/icmeas54189.2021.00015","url":null,"abstract":"Based on the feasibility of the pre-launch attitude composite control method based on grid rudder+RCS (Reaction Control System), the anti-interference ability of the single channel and three channel pre-launch attitude composite control methods is analyse by adding interference torque. The results show that the pre-launch attitude composite control method has strong anti-interference ability and can complete the attitude control task of the launch vehicle. The robustness of the composite control method is analysed by introducing the environmental error and aerodynamic coefficient error to simulate the atmospheric environment change of the rocket in the real environment. The results show that the composite control method has good robustness to the atmospheric density change and aerodynamic coefficient error within the control capability range, which further verifies the feasibility and effectiveness of the method. At the same time, the pre-launch attitude composite control method based on grid rudder+RCS is compared with the more mature stable parachute control method and “stable parachute+control platform” control method. The results show that the designed composite scheme has obvious advantages in control accuracy and control speed, and not only realizes three channel closed-loop active control; It can also reduce the height and speed loss of the arrow body, and clarify the advantages of the composite control method.","PeriodicalId":374943,"journal":{"name":"2021 7th International Conference on Mechanical Engineering and Automation Science (ICMEAS)","volume":"3 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129995087","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 : 2021-10-01DOI: 10.1109/icmeas54189.2021.00023
Yun Luan, Junhang Luo, Beibei Wu, F. He, Jian-hua Wang
For a simple water cooling system, which consists of a U-shaped round pipe and a reservoir, how to discharge the vapor generated in the heated pipe during the cooling process is an interesting topic, especially when pumps or other driving units are hard to install and maintain in the device. In this paper, a thermal-driving method is proposed. By adding different heat fluxes on different parts of the U-shaped pipe, the fluid density difference between those parts can drive a natural circulation of fluid in the loop, and then the vapor bubbles can be discharged with the flow. Numerical simulations are carried out to study the transient performances of the thermal-driving water pipe cooling system under different heat flux distributions. The aim is to obtain the mechanism and evolution law of fluid movement, phase change and heat dissipation. The numerical results indicate that, when the heat flux is uniformly added on the whole pipe, slugs appear in the vertical pipe and where local heat transfer deterioration occurs. When the heat fluxes are different on the left and right vertical parts of the pipe, an overall circulating flow generates. In this process, small vapor bubbles can be discharged, which avoids the formation of the vapor slugs, and the system works stably at boiling point thereby. In addition, with an increase in the heat flux difference between the two vertical parts of the pipe, the initial time of the overall circulating flow shortens.
{"title":"Transient numerical investigation of a thermal-driving water pipe cooling system","authors":"Yun Luan, Junhang Luo, Beibei Wu, F. He, Jian-hua Wang","doi":"10.1109/icmeas54189.2021.00023","DOIUrl":"https://doi.org/10.1109/icmeas54189.2021.00023","url":null,"abstract":"For a simple water cooling system, which consists of a U-shaped round pipe and a reservoir, how to discharge the vapor generated in the heated pipe during the cooling process is an interesting topic, especially when pumps or other driving units are hard to install and maintain in the device. In this paper, a thermal-driving method is proposed. By adding different heat fluxes on different parts of the U-shaped pipe, the fluid density difference between those parts can drive a natural circulation of fluid in the loop, and then the vapor bubbles can be discharged with the flow. Numerical simulations are carried out to study the transient performances of the thermal-driving water pipe cooling system under different heat flux distributions. The aim is to obtain the mechanism and evolution law of fluid movement, phase change and heat dissipation. The numerical results indicate that, when the heat flux is uniformly added on the whole pipe, slugs appear in the vertical pipe and where local heat transfer deterioration occurs. When the heat fluxes are different on the left and right vertical parts of the pipe, an overall circulating flow generates. In this process, small vapor bubbles can be discharged, which avoids the formation of the vapor slugs, and the system works stably at boiling point thereby. In addition, with an increase in the heat flux difference between the two vertical parts of the pipe, the initial time of the overall circulating flow shortens.","PeriodicalId":374943,"journal":{"name":"2021 7th International Conference on Mechanical Engineering and Automation Science (ICMEAS)","volume":"31 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114903760","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 : 2021-10-01DOI: 10.1109/icmeas54189.2021.00017
Yuandong Hu, Zhen Lu, W. Liao, X. Zhang
This study investigates an attitude control scheme for the satellite with moving masses and reaction wheels to solve the problem of the strong aerodynamic disturbance in low Earth orbit. The moving mass actuator is introduced to minimize the influence of the aerodynamic torque, so as to avoid the frequent saturation of the reaction wheel speed. The rotational dynamic equations of the attitude and the translational dynamic equations of the masses are derived by Newtonian mechanics. The dynamic effects of the mass movement are analyzed. A nonlinear observer is used for the precise estimation of the system disturbance to minimize the effects of the disturbance on attitude control through feedforward compensation. An incremental discrete PID control algorithm is used to slow down the mass movement and reduce the dynamic effects. The aerodynamic torque can be used to actively compensate the system disturbance in y and z axes of the body system without knowing structural parameters of the satellite. The numerical simulation indicates that the satellite is capable of maintaining the attitude convergence accuracy within ±0.1° all the time despite strong and uncertain aerodynamic torque. The results verify the feasibility and effectiveness of the proposed control scheme for the satellite with moving masses and reaction wheels.
{"title":"Attitude Control of the Low Earth Orbit Satellite with Moving Masses under Strong Aerodynamic Disturbance","authors":"Yuandong Hu, Zhen Lu, W. Liao, X. Zhang","doi":"10.1109/icmeas54189.2021.00017","DOIUrl":"https://doi.org/10.1109/icmeas54189.2021.00017","url":null,"abstract":"This study investigates an attitude control scheme for the satellite with moving masses and reaction wheels to solve the problem of the strong aerodynamic disturbance in low Earth orbit. The moving mass actuator is introduced to minimize the influence of the aerodynamic torque, so as to avoid the frequent saturation of the reaction wheel speed. The rotational dynamic equations of the attitude and the translational dynamic equations of the masses are derived by Newtonian mechanics. The dynamic effects of the mass movement are analyzed. A nonlinear observer is used for the precise estimation of the system disturbance to minimize the effects of the disturbance on attitude control through feedforward compensation. An incremental discrete PID control algorithm is used to slow down the mass movement and reduce the dynamic effects. The aerodynamic torque can be used to actively compensate the system disturbance in y and z axes of the body system without knowing structural parameters of the satellite. The numerical simulation indicates that the satellite is capable of maintaining the attitude convergence accuracy within ±0.1° all the time despite strong and uncertain aerodynamic torque. The results verify the feasibility and effectiveness of the proposed control scheme for the satellite with moving masses and reaction wheels.","PeriodicalId":374943,"journal":{"name":"2021 7th International Conference on Mechanical Engineering and Automation Science (ICMEAS)","volume":"60 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128444754","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 : 2021-10-01DOI: 10.1109/icmeas54189.2021.00024
W. Yang, S. Gu, Ji-peng Zhao, T. Ma, Bin Yu, Yu Jiang
In order to investigate the deformation characteristics of titanium diaphragm for a spacecraft propellant tank during its reversal process, Based on FE software MSC. Marc, a FE model of the reversal process of the titanium diaphragm is established. In this model, the nonlinear thickness distributions of the diaphragm are coupled by a MSC. Marc subprogram. With the aid of the model, the paper analyses the characteristics of different field variables during the whole reversal process, such as pressure drop, equivalent von mises stress, equivalent plastic strain and apex displacement. The results show that the deformation of the diaphragm is relatively stable during the reversal process. Simulated values of pressure differential show good agreement with measured ones.
{"title":"Modelling the Deformation Characteristics of Titanium Diaphragm for a Spacecraft Propellant Tank","authors":"W. Yang, S. Gu, Ji-peng Zhao, T. Ma, Bin Yu, Yu Jiang","doi":"10.1109/icmeas54189.2021.00024","DOIUrl":"https://doi.org/10.1109/icmeas54189.2021.00024","url":null,"abstract":"In order to investigate the deformation characteristics of titanium diaphragm for a spacecraft propellant tank during its reversal process, Based on FE software MSC. Marc, a FE model of the reversal process of the titanium diaphragm is established. In this model, the nonlinear thickness distributions of the diaphragm are coupled by a MSC. Marc subprogram. With the aid of the model, the paper analyses the characteristics of different field variables during the whole reversal process, such as pressure drop, equivalent von mises stress, equivalent plastic strain and apex displacement. The results show that the deformation of the diaphragm is relatively stable during the reversal process. Simulated values of pressure differential show good agreement with measured ones.","PeriodicalId":374943,"journal":{"name":"2021 7th International Conference on Mechanical Engineering and Automation Science (ICMEAS)","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131096803","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}
京公网安备 11010802042870号
京ICP备2023020795号-1
扫码关注我们
求助内容：
应助结果提醒方式：