Pub Date : 2019-06-21DOI: 10.26732/2618-7957-2019-2-59-72
N. A. Berdnikova, O. Belov, А. V. Lopatin
The article presents a finite element model of CFRP (carbon fiber reinforcement material) reflector polymerization in autoclave for prediction of its shape after removing from the tool. The simulation was performed in the FEM software environment. The technique has developed in this work provides an opportunity to predict a shape and values of the production deformation of the reflector prior to its manufacture, and, if necessary, to introduce design and technological modifications. Successful verification of the finite-element modeling results of the reflector polymerization was performed using a full-scale experiment. Tool from CFRP has been created to forming the composite antenna reflector. This tool is cheaper than the Invar tool currently used. Also, the CFRP tool requires less time to manufacture. Recommendations for improving the technological process of composite contour antenna reflectors production manufactured on CFRP-tool are developed in the paper. The optimum curing mode of the composite reflector is determined. The research results were used in the performance of experimental design work and in the manufacture of reflectors for the spacecraft.
{"title":"Research and optimization of production cycle of high-precision composite spacecraft antenna reflector","authors":"N. A. Berdnikova, O. Belov, А. V. Lopatin","doi":"10.26732/2618-7957-2019-2-59-72","DOIUrl":"https://doi.org/10.26732/2618-7957-2019-2-59-72","url":null,"abstract":"The article presents a finite element model of CFRP (carbon fiber reinforcement material) reflector polymerization in autoclave for prediction of its shape after removing from the tool. The simulation was performed in the FEM software environment. The technique has developed in this work provides an opportunity to predict a shape and values of the production deformation of the reflector prior to its manufacture, and, if necessary, to introduce design and technological modifications. Successful verification of the finite-element modeling results of the reflector polymerization was performed using a full-scale experiment. Tool from CFRP has been created to forming the composite antenna reflector. This tool is cheaper than the Invar tool currently used. Also, the CFRP tool requires less time to manufacture. Recommendations for improving the technological process of composite contour antenna reflectors production manufactured on CFRP-tool are developed in the paper. The optimum curing mode of the composite reflector is determined. The research results were used in the performance of experimental design work and in the manufacture of reflectors for the spacecraft.","PeriodicalId":33896,"journal":{"name":"Kosmicheskie apparaty i tekhnologii","volume":" ","pages":""},"PeriodicalIF":0.0,"publicationDate":"2019-06-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"45528665","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 : 2019-06-21DOI: 10.26732/2618-7957-2019-2-87-93
A. A. Kovel
The ground-experimental testing of the elements of space technology is a crucial stage in the creation of space products, in fact, this is the ground «flight» of the devices being created. And how well the operating conditions will be reproduced at this stage and the successful functioning of the devices under the expected conditions is ensured, its successful operation in real flight during the service life depends. Electronic equipment (apparatus) of the spacecraft is one of the essential elements that ensure the fulfillment of target tasks, which should confirm their readiness for the forthcoming work at the stage of ground-based experimental testing. The technology of experimental development at a time when the scientific and production association of applied mechanics (now the JSC Academician M. F. Reshetnev Information Satellite Systems) was part of the circle of enterprises that created space technology. And at the same time, the peak of research and implementation in the engineering practice of mathematical experiment planning turned out to be very timely. There was a backlog of applied work in various branches of science and technology and a minimum of work on radio-electronic topics, since the element base of the latter did not allow managing the internal parameters of electronic components, i. e., to reveal the influence of internal factors. This became an obstacle to the implementation of the capabilities of the method in research and improvement of electronic equipment. The article shows how the developers of the enterprise equipment overcame the existing limitations and successfully applied mathematical planning of the experiment for the first time in Russian space technology. Using the capabilities of the methodology, the tasks of optimization of circuit design and design implementation of devices, the choice of the element base for space equipment, the establishment of tolerances and the formation of test modes, etc. were solved.
{"title":"Prognostic potential of mathematical experiment planning","authors":"A. A. Kovel","doi":"10.26732/2618-7957-2019-2-87-93","DOIUrl":"https://doi.org/10.26732/2618-7957-2019-2-87-93","url":null,"abstract":"The ground-experimental testing of the elements of space technology is a crucial stage in the creation of space products, in fact, this is the ground «flight» of the devices being created. And how well the operating conditions will be reproduced at this stage and the successful functioning of the devices under the expected conditions is ensured, its successful operation in real flight during the service life depends. Electronic equipment (apparatus) of the spacecraft is one of the essential elements that ensure the fulfillment of target tasks, which should confirm their readiness for the forthcoming work at the stage of ground-based experimental testing.\u0000The technology of experimental development at a time when the scientific and production association of applied mechanics (now the JSC Academician M. F. Reshetnev Information Satellite Systems) was part of the circle of enterprises that created space technology. And at the same time, the peak of research and implementation in the engineering practice of mathematical experiment planning turned out to be very timely.\u0000There was a backlog of applied work in various branches of science and technology and a minimum of work on radio-electronic topics, since the element base of the latter did not allow managing the internal parameters of electronic components, i. e., to reveal the influence of internal factors. This became an obstacle to the implementation of the capabilities of the method in research and improvement of electronic equipment.\u0000The article shows how the developers of the enterprise equipment overcame the existing limitations and successfully applied mathematical planning of the experiment for the first time in Russian space technology.\u0000Using the capabilities of the methodology, the tasks of optimization of circuit design and design implementation of devices, the choice of the element base for space equipment, the establishment of tolerances and the formation of test modes, etc. were solved.","PeriodicalId":33896,"journal":{"name":"Kosmicheskie apparaty i tekhnologii","volume":" ","pages":""},"PeriodicalIF":0.0,"publicationDate":"2019-06-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"45718686","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 : 2019-06-21DOI: 10.26732/2618-7957-2019-2-73-86
M. Ovchinnikov, D. Roldugin
The paper covers main recent results in the active magnetic attitude control of satellites. Three main implementation situations are outlined. Angular velocity damping opens the problem as the auxiliary control task. Next, implementation with other actuators and passive stabilization concepts is considered. Magnetic attitude control is restricted in the direction: control torque cannot be applied along the magnetic induction vector. Other actuators or environmental properties may enhance the control, providing control authority along the restricted axis. This comes at the cost of restricted attitude motion. Passive gravitational stabilization, spin stabilization and dual spin satellites present main cases. The satellite may acquire the local vertical and one axis inertial attitude that represent important cases. The most challenging and practically promising situation is the fully magnetic three axis attitude control. This reduces the hardware requirements for the attitude control system to the minimum. However, this also comes at the cost of a restriction on the control torque vector and low attitude accuracy and time-response. Feedback law with proper control gains tuning, sliding control and optimization techniques are considered for this problem.
{"title":"Recent advances in the active magnetic control of satellites","authors":"M. Ovchinnikov, D. Roldugin","doi":"10.26732/2618-7957-2019-2-73-86","DOIUrl":"https://doi.org/10.26732/2618-7957-2019-2-73-86","url":null,"abstract":"The paper covers main recent results in the active magnetic attitude control of satellites. Three main implementation situations are outlined. Angular velocity damping opens the problem as the auxiliary control task. Next, implementation with other actuators and passive stabilization concepts is considered. Magnetic attitude control is restricted in the direction: control torque cannot be applied along the magnetic induction vector. Other actuators or environmental properties may enhance the control, providing control authority along the restricted axis. This comes at the cost of restricted attitude motion. Passive gravitational stabilization, spin stabilization and dual spin satellites present main cases. The satellite may acquire the local vertical and one axis inertial attitude that represent important cases. The most challenging and practically promising situation is the fully magnetic three axis attitude control. This reduces the hardware requirements for the attitude control system to the minimum. However, this also comes at the cost of a restriction on the control torque vector and low attitude accuracy and time-response. Feedback law with proper control gains tuning, sliding control and optimization techniques are considered for this problem.","PeriodicalId":33896,"journal":{"name":"Kosmicheskie apparaty i tekhnologii","volume":" ","pages":""},"PeriodicalIF":0.0,"publicationDate":"2019-06-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"46137686","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: 10.26732/2618-7957-2019-1-47-57
A. I. Gornostaev, J. A. M. R. I. S. Systems”
{"title":"PROBLEMS OF UNIFICATION OF MULTI-CHANNEL INTERFACE TEMPERATURE CONTROL MODULE FOR MEASURING INSTRUMENTS OF SPACECRAFT","authors":"A. I. Gornostaev, J. A. M. R. I. S. Systems”","doi":"10.26732/2618-7957-2019-1-47-57","DOIUrl":"https://doi.org/10.26732/2618-7957-2019-1-47-57","url":null,"abstract":"","PeriodicalId":33896,"journal":{"name":"Kosmicheskie apparaty i tekhnologii","volume":"10 21 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2019-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"69097316","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: 10.26732/2618-7957-2019-3-164-170
A. Azin, S. Kuznetsov, S. Ponomarev, S. Ponomarev, S. Rikkonen
In the article the results of new piezoelectric step-engine research are presented. The original construct of piezoelectric step-engine is contained in special engineering lever called grab device that can organize back and forward rod’s motion with only one piezo element activity. To choose the effective process of piezoelectric step-engine work the mathematical model was created. This mathematical model describes inner piezoelectric step-engine process like a non-linear vibrational system. The mathematical model identifies speed of piezoelectric step-engine elements over the vibration period with different frequency, load level and voltage. The prototype of piezoelectric step-engine was produced. Experimental issues were conducted. Piezoelectric step-engine’s technical specifications are positioning accuracy over 10–6 meter, speed of movement over 10 mm per minute with weight of load to 1 kg and voltage to 100 Volt. On the results of experimental research it is defined that mathematical model enables to model working process of piezoelectric stepengine with an error not more than 10 %. This research verifies viability of proposed construction and provides the way to increase output power of piezoelectric step-engine.
{"title":"Mathematical modeling of piezoelectric step-engine work","authors":"A. Azin, S. Kuznetsov, S. Ponomarev, S. Ponomarev, S. Rikkonen","doi":"10.26732/2618-7957-2019-3-164-170","DOIUrl":"https://doi.org/10.26732/2618-7957-2019-3-164-170","url":null,"abstract":"In the article the results of new piezoelectric step-engine research are presented. The original construct of piezoelectric step-engine is contained in special engineering lever called grab device that can organize back and forward rod’s motion with only one piezo element activity. To choose the effective process of piezoelectric step-engine work the mathematical model was created. This mathematical model describes inner piezoelectric step-engine process like a non-linear vibrational system. The mathematical model identifies speed of piezoelectric step-engine elements over the vibration period with different frequency, load level and voltage. The prototype of piezoelectric step-engine was produced. Experimental issues were conducted. Piezoelectric step-engine’s technical specifications are positioning accuracy over 10–6 meter, speed of movement over 10 mm per minute with weight of load to 1 kg and voltage to 100 Volt. On the results of experimental research it is defined that mathematical model enables to model working process of piezoelectric stepengine with an error not more than 10 %. This research verifies viability of proposed construction and provides the way to increase output power of piezoelectric step-engine.","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":"69097076","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: 10.26732/2618-7957-2019-1-13-21
V. V. Dvirniy, G. Krushenko, G. V. Dvirniy, A. Shevchuk, M. V. Elfimova, M. S. Kuznetsova, J. A. M. R. I. S. Systems”, Siberian Fire
{"title":"FEATURES OF COMPONENTS OF SPACECRAFT THERMAL CONTROL SYSTEMS","authors":"V. V. Dvirniy, G. Krushenko, G. V. Dvirniy, A. Shevchuk, M. V. Elfimova, M. S. Kuznetsova, J. A. M. R. I. S. Systems”, Siberian Fire","doi":"10.26732/2618-7957-2019-1-13-21","DOIUrl":"https://doi.org/10.26732/2618-7957-2019-1-13-21","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":"69096448","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: 10.26732/2618-7957-2019-1-41-46
E. V. Organova, J. A. M. R. I. S. Systems”, E. V. Ermakovich
{"title":"THE REASONS OF IMPROVEMENT OF MANUFACTURING TECHNIQUES OF BLOCKS OF THE RADIO-ELECTRONIC EQUIPMENT OF SPACECRAFTS USING A POLYPARAXILYLENE COVERING IN THE COURSE OF IMPLEMENTATION AND WORKING OFF","authors":"E. V. Organova, J. A. M. R. I. S. Systems”, E. V. Ermakovich","doi":"10.26732/2618-7957-2019-1-41-46","DOIUrl":"https://doi.org/10.26732/2618-7957-2019-1-41-46","url":null,"abstract":"","PeriodicalId":33896,"journal":{"name":"Kosmicheskie apparaty i tekhnologii","volume":"12 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2019-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"69097251","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: 10.26732/2618-7957-2019-1-28-40
A. Shevchuk, J. A. M. R. I. S. Systems”, G. V. Dvirniy, G. Krushenko, V. V. Dvirniy, M. V. Elfimova, Siberian Fire
{"title":"OPTICAL SYSTEM OF PERSPECTIVE LED-BASED SOLAR SIMULATOR FOR SPACECRAFT GROUND TESTING APPLICATIONS","authors":"A. Shevchuk, J. A. M. R. I. S. Systems”, G. V. Dvirniy, G. Krushenko, V. V. Dvirniy, M. V. Elfimova, Siberian Fire","doi":"10.26732/2618-7957-2019-1-28-40","DOIUrl":"https://doi.org/10.26732/2618-7957-2019-1-28-40","url":null,"abstract":"","PeriodicalId":33896,"journal":{"name":"Kosmicheskie apparaty i tekhnologii","volume":"35 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2019-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"69097187","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: 10.26732/2618-7957-2019-3-121-131
V. B. Taygin, А. V. Lopatin
The paper discusses the existing design of mirror antennas used on spacecraft. The requirements are formulated under which the reliable performance of antennas is ensured under operating conditions. Innovative construction of the space high frequency axisymmetric mirror antenna of an ultralight class is presented. Antenna’s body consists of several conjugate carbon fiber shells. Antenna’s design technology which gives an opportunity to create the shell of a reflector with minimal deflection from a full-paraboloid is developed. Using the finite element method, a parametric modal analysis of the antenna is performed. Based on this analysis, geometric parameters were determined that provide optimal mechanical and mass characteristics of the structure. The calculation results were used to create a prototype mirror antenna. It is shown that the created antenna possesses the parameters required for generation of the high-directional electromagnetic emission of Q and V frequency domain. Successful ground experimental perfection of the construction of the antenna is made. It included the stages of mechanical, thermal vacuum, and radio engineering tests. The proposed design can be used to create advanced spacecraft.
{"title":"Design of the mirror antenna of a spacecraft with the ultralight high precision size-stable reflector","authors":"V. B. Taygin, А. V. Lopatin","doi":"10.26732/2618-7957-2019-3-121-131","DOIUrl":"https://doi.org/10.26732/2618-7957-2019-3-121-131","url":null,"abstract":"The paper discusses the existing design of mirror antennas used on spacecraft. The requirements are formulated under which the reliable performance of antennas is ensured under operating conditions. Innovative construction of the space high frequency axisymmetric mirror antenna of an ultralight class is presented. Antenna’s body consists of several conjugate carbon fiber shells. Antenna’s design technology which gives an opportunity to create the shell of a reflector with minimal deflection from a full-paraboloid is developed. Using the finite element method, a parametric modal analysis of the antenna is performed. Based on this analysis, geometric parameters were determined that provide optimal mechanical and mass characteristics of the structure. The calculation results were used to create a prototype mirror antenna. It is shown that the created antenna possesses the parameters required for generation of the high-directional electromagnetic emission of Q and V frequency domain. Successful ground experimental perfection of the construction of the antenna is made. It included the stages of mechanical, thermal vacuum, and radio engineering tests. The proposed design can be used to create advanced spacecraft.","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":"69096921","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: 10.26732/2618-7957-2019-3-132-139
D. Ivanov, S. V. Meus, A. B. Nuralieva, A. Ovchinnikov, M. Ovchinnikov, D. Roldugin, S. Tkachev, A. Shestoperov, S. Shestakov, E. N. Yakimov
The paper covers the attitude control and determination algorithms of the satellite equipped with two flexible appendages. One of the appendages is an antenna. It is connected to the satellite bus inelastically. The antenna itself is a major disturbance factor. Its dimensions by far exceed the dimensions of the bus, and the eigen frequencies of the antenna oscillations are low. The second appendage is a solar panel. The spacecraft moves on the geostationary orbit. The panel is connected via the one degree of freedom hinge. It rotates with the constant rate to provide continuous solar panel attitude towards the Sun. Attitude control and determination is achieved with the hardware installed on the satellite bus only. Moreover, the oscillations of the flexible elements have no natural damping. The control and determination algorithms are provided that stabilize the satellite bus and reduce the flexible appendages oscillations alongside. Special control algorithm is proposed that does not excite the oscillations and lowers the computational burden on the onboard computer. Different eigen forms are considered to represent the error in the appendages models.
{"title":"Attitude control and determination algorithms for the spacecraft with two flexible appendages","authors":"D. Ivanov, S. V. Meus, A. B. Nuralieva, A. Ovchinnikov, M. Ovchinnikov, D. Roldugin, S. Tkachev, A. Shestoperov, S. Shestakov, E. N. Yakimov","doi":"10.26732/2618-7957-2019-3-132-139","DOIUrl":"https://doi.org/10.26732/2618-7957-2019-3-132-139","url":null,"abstract":"The paper covers the attitude control and determination algorithms of the satellite equipped with two flexible appendages. One of the appendages is an antenna. It is connected to the satellite bus inelastically. The antenna itself is a major disturbance factor. Its dimensions by far exceed the dimensions of the bus, and the eigen frequencies of the antenna oscillations are low. The second appendage is a solar panel. The spacecraft moves on the geostationary orbit. The panel is connected via the one degree of freedom hinge. It rotates with the constant rate to provide continuous solar panel attitude towards the Sun. Attitude control and determination is achieved with the hardware installed on the satellite bus only. Moreover, the oscillations of the flexible elements have no natural damping. The control and determination algorithms are provided that stabilize the satellite bus and reduce the flexible appendages oscillations alongside. Special control algorithm is proposed that does not excite the oscillations and lowers the computational burden on the onboard computer. Different eigen forms are considered to represent the error in the appendages models.","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":"69096965","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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