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/icmeas54189.2021.00017
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}
With the improvement of the complexity of civil aircraft,Model Based Systems Engineering(MBSE) plays more important role in the aircraft design nowadays. In this paper, an architecture design method based on MBSE applied in aircraft cabin pressure control system is introduced. A top-down design process including functional physical architecture analysis is presented to ensure final solution can meet stakeholder needs. Functional architecture produced by functional analysis which transfers stakeholder needs and top-level requirements to design requirements has great effects on physical solution design. Physical architecture which is implementation of functional architecture provides enough detail to synthesize a physical architecture. This paper proposes a framework for efficient architecture based MBSE which can also provide common understanding of the scope and characterization of the system for engineers involved in system design. It shows that the proposed MBSE method significantly improves synthesis of design and integration, and ensure the requirements can be properly implemented
{"title":"Application Practice of Model-Based System Engineering Method in Civil Aircraft Cabin Pressure Control System Design","authors":"Tang Chao, He Yan, Zhang Kaili, litao litao, Jiafeng Li, Zhang Xinai","doi":"10.1109/icmeas54189.2021.00045","DOIUrl":"https://doi.org/10.1109/icmeas54189.2021.00045","url":null,"abstract":"With the improvement of the complexity of civil aircraft,Model Based Systems Engineering(MBSE) plays more important role in the aircraft design nowadays. In this paper, an architecture design method based on MBSE applied in aircraft cabin pressure control system is introduced. A top-down design process including functional physical architecture analysis is presented to ensure final solution can meet stakeholder needs. Functional architecture produced by functional analysis which transfers stakeholder needs and top-level requirements to design requirements has great effects on physical solution design. Physical architecture which is implementation of functional architecture provides enough detail to synthesize a physical architecture. This paper proposes a framework for efficient architecture based MBSE which can also provide common understanding of the scope and characterization of the system for engineers involved in system design. It shows that the proposed MBSE method significantly improves synthesis of design and integration, and ensure the requirements can be properly implemented","PeriodicalId":374943,"journal":{"name":"2021 7th International Conference on Mechanical Engineering and Automation Science (ICMEAS)","volume":"37 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":"117000765","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/ICMEAS54189.2021.00025
E. Marakhova, A.B. Shimanova, D. Uglanov, H. Adenane
In nowadays the best way to carry an operating body such hydrogen or nitrogen for example it’s to carry it in liquid state and low temperature which is cryogenic state. In this work it will be shown a computational studies of the recondensation process in a tank with a cryogenic filling, and also a promising technologies in the cryogenic filling tank that have been realized at the laboratory of Samara University. The computational studies carried out allow us to draw the following conclusion that during regasification of a cryoproduct in the cryogenic filling tank, recondensation of a part of the gasified product occurs due to the temperature difference between the wall of the thermos and the inner wall of the cryogenic filling tank. This process is observed at the beginning of regasification (in the first 3-5 minutes), and the intensity of this process is low and amounts to about 2-8%.
{"title":"Computational Studies of the Recondensation Process in a Tank with a Cryogenic Filling","authors":"E. Marakhova, A.B. Shimanova, D. Uglanov, H. Adenane","doi":"10.1109/ICMEAS54189.2021.00025","DOIUrl":"https://doi.org/10.1109/ICMEAS54189.2021.00025","url":null,"abstract":"In nowadays the best way to carry an operating body such hydrogen or nitrogen for example it’s to carry it in liquid state and low temperature which is cryogenic state. In this work it will be shown a computational studies of the recondensation process in a tank with a cryogenic filling, and also a promising technologies in the cryogenic filling tank that have been realized at the laboratory of Samara University. The computational studies carried out allow us to draw the following conclusion that during regasification of a cryoproduct in the cryogenic filling tank, recondensation of a part of the gasified product occurs due to the temperature difference between the wall of the thermos and the inner wall of the cryogenic filling tank. This process is observed at the beginning of regasification (in the first 3-5 minutes), and the intensity of this process is low and amounts to about 2-8%.","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":"122063290","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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