Pub Date : 2019-01-01DOI: 10.26732/2618-7957-2019-3-171-183
A. I. Gornostaev
In the development of a unified multi-channel interface temperature control module for measuring instruments, built on a main-modular principle on the basis of the central instrument module and used on spacecraft for various purposes, the primary task is to determine its structure, which allows to provide temperature control on the elements of the spacecraft design in different measurement ranges and with different requirements for accuracy and stability of measurement. The article is devoted to the analysis of general requirements to the structure of the multi-channel interface temperature control module, in which the measuring channels can have different technical characteristics and the choice of variants for measuring the resistance of thermal converters to ensure the elimination of the systematic component of the measurement error. It is shown that in the structure of a unified multichannel interface temperature control module there should be a multichannel measurement scheme forming several measurement channels with different technical characteristics operating on a common channel of analog-to-digital conversion. To match the measuring channels with different input resistances and operating in different measurement ranges with the common channel of the analog-to-digital converter, it is necessary to use a controlled normalizing amplifier. To eliminate the systematic component of the measurement error, it is necessary to use three- or four-wire variants of the measurement schemes of thermal resistance converters, which allow the automatic compensation of the measurement error introduced by the resistances of the wires of the communication lines of the measuring cables, and the automatic calibration of the measurement error introduced by the measuring channels. To compensate for the nonlinear component of the measurement error introduced by thermal resistance converters, it is necessary on the basis of piecewise linear approximation of their nominal static characteristics to divide the operating ranges of measurement into subranges and to carry out automatic calibration measurement errors in each subrange separately.
{"title":"Optimization of the structure of the unified multichannel interface temperature control module for measuring instruments of spacecraft","authors":"A. I. Gornostaev","doi":"10.26732/2618-7957-2019-3-171-183","DOIUrl":"https://doi.org/10.26732/2618-7957-2019-3-171-183","url":null,"abstract":"In the development of a unified multi-channel interface temperature control module for measuring instruments, built on a main-modular principle on the basis of the central instrument module and used on spacecraft for various purposes, the primary task is to determine its structure, which allows to provide temperature control on the elements of the spacecraft design in different measurement ranges and with different requirements for accuracy and stability of measurement. The article is devoted to the analysis of general requirements to the structure of the multi-channel interface temperature control module, in which the measuring channels can have different technical characteristics and the choice of variants for measuring the resistance of thermal converters to ensure the elimination of the systematic component of the measurement error. It is shown that in the structure of a unified multichannel interface temperature control module there should be a multichannel measurement scheme forming several measurement channels with different technical characteristics operating on a common channel of analog-to-digital conversion. To match the measuring channels with different input resistances and operating in different measurement ranges with the common channel of the analog-to-digital converter, it is necessary to use a controlled normalizing amplifier. To eliminate the systematic component of the measurement error, it is necessary to use three- or four-wire variants of the measurement schemes of thermal resistance converters, which allow the automatic compensation of the measurement error introduced by the resistances of the wires of the communication lines of the measuring cables, and the automatic calibration of the measurement error introduced by the measuring channels. To compensate for the nonlinear component of the measurement error introduced by thermal resistance converters, it is necessary on the basis of piecewise linear approximation of their nominal static characteristics to divide the operating ranges of measurement into subranges and to carry out automatic calibration measurement errors in each subrange separately.","PeriodicalId":33896,"journal":{"name":"Kosmicheskie apparaty i tekhnologii","volume":"1 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2019-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"69097123","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 : 2019-01-01DOI: 10.26732/2618-7957-2019-1-5-12
I. I. Shilko, J. A. M. R. I. S. Systems”, Y. Voloshko, O. V. Ruzhilova, O. A. Anisimova
{"title":"ANALYSIS OF UPGRADE OPTIONS FOR THE STRUCTURE OF ORBITAL GROUPING OF THE GLONASS SYSTEM TO ENSURE ITS COMPETITIVENESS","authors":"I. I. Shilko, J. A. M. R. I. S. Systems”, Y. Voloshko, O. V. Ruzhilova, O. A. Anisimova","doi":"10.26732/2618-7957-2019-1-5-12","DOIUrl":"https://doi.org/10.26732/2618-7957-2019-1-5-12","url":null,"abstract":"","PeriodicalId":33896,"journal":{"name":"Kosmicheskie apparaty i tekhnologii","volume":"1 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2019-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"69097375","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 : 2019-01-01DOI: 10.26732/2618-7957-2019-3-140-148
V. Moskvichev, A. Lepikhin, A. Burov, S. Doronin, E. Moskvichev
Modern polymer composite materials with high specific characteristics of strength and stiffness allow creating strong, durable and geometrically stable space structures. To expand the scope of application of composite materials and increase the competitiveness of space structures, it is necessary to further improve design methods with the widespread use of multiscale computational modeling of deformation and fracture processes. The paper presents the results of analysis on the strength and dimensional stability of structures made of polymer composites. A metal-composite high-pressure tank for electric propulsion systems and the design of precision reflectors for space- and ground-based antennas are considered. The methods and results of experimental and computational studies on the stress-strain and ultimate states of structures are described. The methods and means of non-destructive testing, the results of the analysis on the stress-strain state and full-scale tests of the tank structure are described. Generalized estimates of the load-carrying capacity of reflector structures under given operating conditions are given.
{"title":"Calculation and experimental assessment of the strength and limit states of composite structures for spacecraft","authors":"V. Moskvichev, A. Lepikhin, A. Burov, S. Doronin, E. Moskvichev","doi":"10.26732/2618-7957-2019-3-140-148","DOIUrl":"https://doi.org/10.26732/2618-7957-2019-3-140-148","url":null,"abstract":"Modern polymer composite materials with high specific characteristics of strength and stiffness allow creating strong, durable and geometrically stable space structures. To expand the scope of application of composite materials and increase the competitiveness of space structures, it is necessary to further improve design methods with the widespread use of multiscale computational modeling of deformation and fracture processes. The paper presents the results of analysis on the strength and dimensional stability of structures made of polymer composites. A metal-composite high-pressure tank for electric propulsion systems and the design of precision reflectors for space- and ground-based antennas are considered. The methods and results of experimental and computational studies on the stress-strain and ultimate states of structures are described. The methods and means of non-destructive testing, the results of the analysis on the stress-strain state and full-scale tests of the tank structure are described. Generalized estimates of the load-carrying capacity of reflector structures under given operating conditions are given.","PeriodicalId":33896,"journal":{"name":"Kosmicheskie apparaty i tekhnologii","volume":"1 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2019-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"69097026","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 : 2019-01-01DOI: 10.26732/2618-7957-2019-1-22-27
V. Myznikova, V. Ustimenko, A. Chubar
{"title":"FUZZY CONTROLLERS CONSTRUCTION IN THE SimInTech ENVIRONMENT","authors":"V. Myznikova, V. Ustimenko, A. Chubar","doi":"10.26732/2618-7957-2019-1-22-27","DOIUrl":"https://doi.org/10.26732/2618-7957-2019-1-22-27","url":null,"abstract":"","PeriodicalId":33896,"journal":{"name":"Kosmicheskie apparaty i tekhnologii","volume":"1 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2019-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"69097165","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 : 2019-01-01DOI: 10.26732/2618-7957-2019-3-149-154
A. Chubar, I. Pozharkova, V. Ustimenko
Paper is divote to results of the development of the thermal vacuum tests computer model of allowing to investigate impact of external factors on the devices which are in conditions of own external atmosphere of the spacecraft in the SimInTech environment of the technical systems dynamic modeling. For a solution an objective models of a control object of the thermal vacuum TVAC-1400 camera are created, and the regulators executed on the basis of the programmable industrial controller Siemens S7-300 setup of key parameters is made, control algorithms are implemented by the modes of tests. The developed model allows to exercise control of test programs of the different equipment, prevention of failures at an error of the operator or interruptions in engineering networks, to reveal the most adverse situations which can arise process of functioning of the thermal vacuum camera. Besides, the presented model can be used for a research of behavior of controlled parameters of thermal vacuum tests and working off of control algorithms. In article development process and settings of model of thermal vacuum tests, its submodels and a control bar, implementation of the main algorithms are step by step described. Also results of adequacy check to the developed model are presented.
{"title":"Creation of control algorithms thermal vacuum tests in the SimInTech environment","authors":"A. Chubar, I. Pozharkova, V. Ustimenko","doi":"10.26732/2618-7957-2019-3-149-154","DOIUrl":"https://doi.org/10.26732/2618-7957-2019-3-149-154","url":null,"abstract":"Paper is divote to results of the development of the thermal vacuum tests computer model of allowing to investigate impact of external factors on the devices which are in conditions of own external atmosphere of the spacecraft in the SimInTech environment of the technical systems dynamic modeling. For a solution an objective models of a control object of the thermal vacuum TVAC-1400 camera are created, and the regulators executed on the basis of the programmable industrial controller Siemens S7-300 setup of key parameters is made, control algorithms are implemented by the modes of tests. The developed model allows to exercise control of test programs of the different equipment, prevention of failures at an error of the operator or interruptions in engineering networks, to reveal the most adverse situations which can arise process of functioning of the thermal vacuum camera. Besides, the presented model can be used for a research of behavior of controlled parameters of thermal vacuum tests and working off of control algorithms. In article development process and settings of model of thermal vacuum tests, its submodels and a control bar, implementation of the main algorithms are step by step described. Also results of adequacy check to the developed model are presented.","PeriodicalId":33896,"journal":{"name":"Kosmicheskie apparaty i tekhnologii","volume":"1 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2019-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"69097061","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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