This paper is dedicated to modeling of fuel sloshing dynamics and its effect on the stability and control of the space vehicle. Sloshing due to the liquid movement in the fuel tank of a space vehicle's propulsion system can be effective on the vehicle’s control and stability. Force and moment interaction between fuel sloshing and space vehicle’s control system will be appeared as a feedback in the control system. With respect to simplicity of analyzing of a rigid body's equations of motion in comparison with a fluid dynamics equations and as a result reducing computational efforts, it is possible to apply a mechanical model instead. So in this paper fuel sloshing is modelled as a linear mechanical system to investigate its effect on the stability and control of the vehicle. For this purpose, two mechanical models, mass-spring and pendulum systems, are applied to model dynamics of a space vehicle with fuel sloshing and each system’s parameters are evaluated for simulat.
{"title":"Vibration control design of fuel sloshing in a spacecraft using virtual actuator","authors":"A. Khoshnood, A. Aminzadeh, P. Nikpey","doi":"10.30699/jsst.2021.1326","DOIUrl":"https://doi.org/10.30699/jsst.2021.1326","url":null,"abstract":"This paper is dedicated to modeling of fuel sloshing dynamics and its effect on the stability and control of the space vehicle. Sloshing due to the liquid movement in the fuel tank of a space vehicle's propulsion system can be effective on the vehicle’s control and stability. Force and moment interaction between fuel sloshing and space vehicle’s control system will be appeared as a feedback in the control system. With respect to simplicity of analyzing of a rigid body's equations of motion in comparison with a fluid dynamics equations and as a result reducing computational efforts, it is possible to apply a mechanical model instead. So in this paper fuel sloshing is modelled as a linear mechanical system to investigate its effect on the stability and control of the vehicle. For this purpose, two mechanical models, mass-spring and pendulum systems, are applied to model dynamics of a space vehicle with fuel sloshing and each system’s parameters are evaluated for simulat.","PeriodicalId":272394,"journal":{"name":"Journal of Space Science and Technology","volume":"87 4 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-03-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121930461","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}
In this article, a universal algorithm and engineering software is presented for the conceptual design of cryogenic rocket propulsion system. The algorithm consisting five engine working cycles: pressure fed, gas generator, staged combustion, closed and opened expansion cycles. For validation, the Vulcain and HM7B engines were redesigned, the obtained results certifies that the main design parameters have less than 5% errors and the other less than 20%. One of the advantages of this software is the presence of abut 150 parameters in the output and 14 diagrams related to the flow behavior in the thrust chamber and cooling vest, which allows the parametric study of the effect of input changes on the outputs. The modeling of mathematical functions and the combustion has been done, by using the MATLAB and CEA software. Finally, by merging in Visual studio programming environment and with the help of C# programming language, a software with GUI is presented.
{"title":"Developing a universal Software for the Conceptual Design of Cryogenic Rocket Propulsion System","authors":"Nourbakhsh Fouladi, Neda sadat Seddighi renani","doi":"10.30699/jsst.2022.1313","DOIUrl":"https://doi.org/10.30699/jsst.2022.1313","url":null,"abstract":"In this article, a universal algorithm and engineering software is presented for the conceptual design of cryogenic rocket propulsion system. The algorithm consisting five engine working cycles: pressure fed, gas generator, staged combustion, closed and opened expansion cycles. For validation, the Vulcain and HM7B engines were redesigned, the obtained results certifies that the main design parameters have less than 5% errors and the other less than 20%. One of the advantages of this software is the presence of abut 150 parameters in the output and 14 diagrams related to the flow behavior in the thrust chamber and cooling vest, which allows the parametric study of the effect of input changes on the outputs. The modeling of mathematical functions and the combustion has been done, by using the MATLAB and CEA software. Finally, by merging in Visual studio programming environment and with the help of C# programming language, a software with GUI is presented.","PeriodicalId":272394,"journal":{"name":"Journal of Space Science and Technology","volume":"55 49","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-03-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131471399","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}
How to Cite: A. R. Kosari, A. Ahmadi, A. Sharifi, and M. Khoshsima, "Rapid Performance Sizing of Reaction Wheels in a Very High Resolution Remote Sensing Satellite Using Matching Diagram Technique," Journal of Space Science and Technology, vol. 15, pp. 23-42, 2022 (in Persian). Rapid Performance Sizing of Reaction Wheels in a Very High Resolution Remote Sensing Satellite Using Matching Diagram Technique
引用方式:a . R. Kosari, a . Ahmadi, a . Sharifi和M. Khoshsima，“使用匹配图技术的超高分辨率遥感卫星反作用轮的快速性能尺寸”，《空间科学与技术杂志》，第15卷，第23-42页，2022年(波斯语)。基于匹配图技术的超高分辨率遥感卫星反作用轮快速性能评定
{"title":"Rapid Performance Sizing of Reaction Wheels in a Very High Resolution Remote Sensing Satellite Using Matching Diagram Technique","authors":"A. Kosari, A. Ahmadi, A. Sharifi, M. Khoshsima","doi":"10.30699/jsst.2022.1249","DOIUrl":"https://doi.org/10.30699/jsst.2022.1249","url":null,"abstract":"How to Cite: A. R. Kosari, A. Ahmadi, A. Sharifi, and M. Khoshsima, \"Rapid Performance Sizing of Reaction Wheels in a Very High Resolution Remote Sensing Satellite Using Matching Diagram Technique,\" Journal of Space Science and Technology, vol. 15, pp. 23-42, 2022 (in Persian). Rapid Performance Sizing of Reaction Wheels in a Very High Resolution Remote Sensing Satellite Using Matching Diagram Technique","PeriodicalId":272394,"journal":{"name":"Journal of Space Science and Technology","volume":"24 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-03-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130597734","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}
From the past, space activities which has been extremely important for governments as the main and traditional players in the space industry, are now attractive to non-governmental and private individuals, who are the new actors in the space industry. Undoubtedly, in this field, technology is a prerequisite for the implementation and development of space activities. Developing and less developed governments are trying to pave the way for these activities by passing national space legislations, but it should be noted that there are still many obstacles in this way. One of these obstacles is the existence of restrictive acts and regulations of developed countries on transfer of technology in the space industry. Identifying the dimensions of these barriers and limitations and evaluating them from the standpoint of intellectual property rights is the subject of this article. The conflict between the tendency towards commercialization of space activities and tight control over technology transfer in the space industry is one of the results that this article has achieved.
{"title":"The Intellectual Property Rights and Transfer of Technology in Space Industry","authors":"Saied Habiba, Hamid Kazemi, Milad Sadeghi","doi":"10.30699/jsst.2022.1331","DOIUrl":"https://doi.org/10.30699/jsst.2022.1331","url":null,"abstract":"From the past, space activities which has been extremely important for governments as the main and traditional players in the space industry, are now attractive to non-governmental and private individuals, who are the new actors in the space industry. Undoubtedly, in this field, technology is a prerequisite for the implementation and development of space activities. Developing and less developed governments are trying to pave the way for these activities by passing national space legislations, but it should be noted that there are still many obstacles in this way. One of these obstacles is the existence of restrictive acts and regulations of developed countries on transfer of technology in the space industry. Identifying the dimensions of these barriers and limitations and evaluating them from the standpoint of intellectual property rights is the subject of this article. The conflict between the tendency towards commercialization of space activities and tight control over technology transfer in the space industry is one of the results that this article has achieved.","PeriodicalId":272394,"journal":{"name":"Journal of Space Science and Technology","volume":"31 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-03-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"117349555","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}
{"title":"Modelling Diversity in Redundant Systems: Case Study of Satellite Systems","authors":"G. Kahe, Mehdi Alemi Rostami","doi":"10.30699/jsst.2021.1283","DOIUrl":"https://doi.org/10.30699/jsst.2021.1283","url":null,"abstract":"","PeriodicalId":272394,"journal":{"name":"Journal of Space Science and Technology","volume":"40 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-03-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131250468","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}
Muscle atrophy is one of the problems that astronauts face after returning to earth. Myostatin is a known negative regulator of muscle growth. This study aimed to investigate the effects of simulated microgravity condition on mouse myotube cells (C2C12) growth and the myostatin gene expression. The morphological studies and MTT cytotoxicity assay showed no significant alternation in cells after 48h simulation microgravity, however, after 72h ~40% of cell death accrued ( p <0.05). The AO/PI staining and DNA fragmentation analysis confirmed this observation too. Analysis of the gene expression revealed that simulated microgravity reduced myostatin gene expression significantly after 48h ( p <0.0001), however, after 72h, increased significantly ( P <0.001). So, inhibition of myostatin expression in differentiated myocyte cells of astronauts could be an effective procedure to reduce skeletal muscle atrophy under microgravity condition
{"title":"Effect of Simulated microgravity condition on cells proliferation and myostatin gene expression in differentiated skeletal muscle cells (C2C12)","authors":"Narjes Rhmanian, A. Hekmat, Z. Hajebrahimi","doi":"10.30699/jsst.2021.1346","DOIUrl":"https://doi.org/10.30699/jsst.2021.1346","url":null,"abstract":"Muscle atrophy is one of the problems that astronauts face after returning to earth. Myostatin is a known negative regulator of muscle growth. This study aimed to investigate the effects of simulated microgravity condition on mouse myotube cells (C2C12) growth and the myostatin gene expression. The morphological studies and MTT cytotoxicity assay showed no significant alternation in cells after 48h simulation microgravity, however, after 72h ~40% of cell death accrued ( p <0.05). The AO/PI staining and DNA fragmentation analysis confirmed this observation too. Analysis of the gene expression revealed that simulated microgravity reduced myostatin gene expression significantly after 48h ( p <0.0001), however, after 72h, increased significantly ( P <0.001). So, inhibition of myostatin expression in differentiated myocyte cells of astronauts could be an effective procedure to reduce skeletal muscle atrophy under microgravity condition","PeriodicalId":272394,"journal":{"name":"Journal of Space Science and Technology","volume":"147 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-03-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116617633","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}
In this numerical study, the effect of the magnetic field on the convective heat transfer of a magnetic fluid in an enclosure is investigated in the microgravity condition. Two cases of a single magnetic field source under the enclosure and two sources on the top and below the enclosure are considered. The simulations are carried out for different magnetic field intensities and magnetic source distances from the enclosure. Results indicate that the heat transfer in the microgravity is much lower than that of natural conditions due to the lack of the flow vortex. Applying the magnetic field and the induced vortex due to the magnetic body force cause a significant improvement in the heat transfer. Results show that the heat transfer rate in the microgravity condition can be increased up to 6.5 times. Moreover, placing two magnetic field sources improves the main vortex and leads to a 19.7 times enhancement of the heat transfer rate compared to the case of a single source.
{"title":"Magnetic field effects on heat transfer enhancement in an enclosure in microgravity conditions","authors":"Mohammad ghoharkhah, B. Alizadeh","doi":"10.30699/jsst.2021.1235","DOIUrl":"https://doi.org/10.30699/jsst.2021.1235","url":null,"abstract":"In this numerical study, the effect of the magnetic field on the convective heat transfer of a magnetic fluid in an enclosure is investigated in the microgravity condition. Two cases of a single magnetic field source under the enclosure and two sources on the top and below the enclosure are considered. The simulations are carried out for different magnetic field intensities and magnetic source distances from the enclosure. Results indicate that the heat transfer in the microgravity is much lower than that of natural conditions due to the lack of the flow vortex. Applying the magnetic field and the induced vortex due to the magnetic body force cause a significant improvement in the heat transfer. Results show that the heat transfer rate in the microgravity condition can be increased up to 6.5 times. Moreover, placing two magnetic field sources improves the main vortex and leads to a 19.7 times enhancement of the heat transfer rate compared to the case of a single source.","PeriodicalId":272394,"journal":{"name":"Journal of Space Science and Technology","volume":"43 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-12-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130261033","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}
This paper presents the design, analysis and performance verification test of student microsatellite Attitude Determination and Control Subsystem (ADCS). ADCS design and implementation procedure contain several various steps. There are four main test levels during simulation called “Model-in-the-Loop”, “Software-in-the-Loop”, “Processor-in-the-Loop” and “Hardware-in-the-Loop”. This paper results from scientific and practical research during two years on the student microsatellite, an eight-nation collaboration project among Asia-Pacific universities. In what follows, “Model-in-the-Loop” and “Processor-in-the-Loop” test and simulation will be discussed. This paper aims to illustrate the result of these two tests and validate the ADCS design. In the end, it is demonstrated that designed control algorithms are precise enough to meet the student microsatellite ADCS requirements, and they can be used in the next level of microsatellite development.
{"title":"Development of MIL and PIL testbed for Student Microsatellite Attitude Control Subsystem","authors":"Niki Sajjad, M. Mirshams, Shahrokh Jaliian","doi":"10.30699/jsst.2021.1205","DOIUrl":"https://doi.org/10.30699/jsst.2021.1205","url":null,"abstract":"This paper presents the design, analysis and performance verification test of student microsatellite Attitude Determination and Control Subsystem (ADCS). ADCS design and implementation procedure contain several various steps. There are four main test levels during simulation called “Model-in-the-Loop”, “Software-in-the-Loop”, “Processor-in-the-Loop” and “Hardware-in-the-Loop”. This paper results from scientific and practical research during two years on the student microsatellite, an eight-nation collaboration project among Asia-Pacific universities. In what follows, “Model-in-the-Loop” and “Processor-in-the-Loop” test and simulation will be discussed. This paper aims to illustrate the result of these two tests and validate the ADCS design. In the end, it is demonstrated that designed control algorithms are precise enough to meet the student microsatellite ADCS requirements, and they can be used in the next level of microsatellite development.","PeriodicalId":272394,"journal":{"name":"Journal of Space Science and Technology","volume":"190 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-09-22","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116516935","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}
Amirhossain Adami, M. Nosratollahi, Hanieh Eshagh nia, Sajjad Kheirkhah, S. Emami, Ali Saadat dar, N. Afsari, Khashayar Mashhadi, Mansour Hozuri
{"title":"The presentation of the ARTA CanSat design and construction process at the CANSAT International Competition in Iran","authors":"Amirhossain Adami, M. Nosratollahi, Hanieh Eshagh nia, Sajjad Kheirkhah, S. Emami, Ali Saadat dar, N. Afsari, Khashayar Mashhadi, Mansour Hozuri","doi":"10.30699/jsst.2020.1216","DOIUrl":"https://doi.org/10.30699/jsst.2020.1216","url":null,"abstract":"","PeriodicalId":272394,"journal":{"name":"Journal of Space Science and Technology","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-06-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115681376","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}
{"title":"Applying multi-objective optimization approaches to design an optimal controller for orbital docking by consideration of actuators dynamics and comparing results","authors":"H. Taei, Pourya Shokrolahi","doi":"10.30699/jsst.2020.1186","DOIUrl":"https://doi.org/10.30699/jsst.2020.1186","url":null,"abstract":"","PeriodicalId":272394,"journal":{"name":"Journal of Space Science and Technology","volume":"37 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-06-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114814172","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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