Pub Date : 2021-12-24DOI: 10.26732//j.st.2021.4.02
S. A. Kabanov, D. S. Kabanov
The article discusses the process of controlling the angular motion of the spoke of a large-sized space-based reflector, taking into account bending vibrations. Currently, large antennas are actively used for receiving and transmitting data. When launching large structures into space, the problem arises of reliably deployment the spokes, since they are packed in a small volume to be able to be installed in a launch vehicle. Due to the possibility of various abnormal situations, such as jamming of elements, engagement of the net, it is necessary to re-deployment the antenna. Therefore, it is important to develop control algorithms that can reliably solve the problems of direct and reverse motion. In the process of deployment and bringing together the elements of the reflector, various deformations appear in the structure. When the antenna spokes are brought together, lateral oscillations make the largest contribution to the oscillatory of the transient process. Currently, elastically deformed elements are used to deployment large-sized reflectors, and a control program is also used. This prevents the control from being adjusted when the deployment conditions change. The paper investigates the possibility of minimizing the vibrations of a structure during its deployment by using optimal control algorithms in real time. The forward and reverse motion of the antenna elements is performed by means of a two-criteria hierarchy optimization. The results of numerical simulation of the optimal rotation of the reflector spoke are presented. The proposed algorithm allows you to choose the optimal control in emergency situations for various types of large reflectors.
{"title":"Optimal deployment of the spoke of a largesized transformable reflector according to the hierarchy of criteria","authors":"S. A. Kabanov, D. S. Kabanov","doi":"10.26732//j.st.2021.4.02","DOIUrl":"https://doi.org/10.26732//j.st.2021.4.02","url":null,"abstract":"The article discusses the process of controlling the angular motion of the spoke of a large-sized space-based reflector, taking into account bending vibrations. Currently, large antennas are actively used for receiving and transmitting data. When launching large structures into space, the problem arises of reliably deployment the spokes, since they are packed in a small volume to be able to be installed in a launch vehicle. Due to the possibility of various abnormal situations, such as jamming of elements, engagement of the net, it is necessary to re-deployment the antenna. Therefore, it is important to develop control algorithms that can reliably solve the problems of direct and reverse motion. In the process of deployment and bringing together the elements of the reflector, various deformations appear in the structure. When the antenna spokes are brought together, lateral oscillations make the largest contribution to the oscillatory of the transient process. Currently, elastically deformed elements are used to deployment large-sized reflectors, and a control program is also used. This prevents the control from being adjusted when the deployment conditions change. The paper investigates the possibility of minimizing the vibrations of a structure during its deployment by using optimal control algorithms in real time. The forward and reverse motion of the antenna elements is performed by means of a two-criteria hierarchy optimization. The results of numerical simulation of the optimal rotation of the reflector spoke are presented. The proposed algorithm allows you to choose the optimal control in emergency situations for various types of large reflectors.","PeriodicalId":33896,"journal":{"name":"Kosmicheskie apparaty i tekhnologii","volume":" ","pages":""},"PeriodicalIF":0.0,"publicationDate":"2021-12-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"44313237","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}
The article discusses the study of the effect of a change in the radius of the ball in the injecting of the sample on the curve in the coordinates «load – indentation depth», the deviation of the indentation depth during elastoplastic indentation from the indentation depth with the elastic indentation and the amount of the axial deformation of the ball. The study was conducted using the Ansys Mechanical APDL program implementing the fenite element method. In the process of the study, it was found that with a change in the radius of the ball, there is no obvious change in the behavior of the sample material, and the deviation of the indentation depth during the elastoplastic indulgence from the indentation depth during the elastic indentation is not dependent on the size of the ball radius. There was also an effect of changing the radius of the ball on the size of the axial deformation of the ball and proposed a formula for determining the size of the axial deformation of the ball for the ball of any diameter, which will determine the actual depth of the ball into the ball when using the balls of different radius.
{"title":"Determination of the optimum ball radius for researching materials using ball indenting","authors":"N. N. Avtonomov, A. Tololo","doi":"10.26732/j.st.2021.4.06","DOIUrl":"https://doi.org/10.26732/j.st.2021.4.06","url":null,"abstract":"The article discusses the study of the effect of a change in the radius of the ball in the injecting of the sample on the curve in the coordinates «load – indentation depth», the deviation of the indentation depth during elastoplastic indentation from the indentation depth with the elastic indentation and the amount of the axial deformation of the ball. The study was conducted using the Ansys Mechanical APDL program implementing the fenite element method. In the process of the study, it was found that with a change in the radius of the ball, there is no obvious change in the behavior of the sample material, and the deviation of the indentation depth during the elastoplastic indulgence from the indentation depth during the elastic indentation is not dependent on the size of the ball radius. There was also an effect of changing the radius of the ball on the size of the axial deformation of the ball and proposed a formula for determining the size of the axial deformation of the ball for the ball of any diameter, which will determine the actual depth of the ball into the ball when using the balls of different radius.","PeriodicalId":33896,"journal":{"name":"Kosmicheskie apparaty i tekhnologii","volume":" ","pages":""},"PeriodicalIF":0.0,"publicationDate":"2021-12-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"48925185","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}
E. B. Korotkov, O. Shirobokov, S. Matveev, Z. A. Yudina
The paper reports a brief description of spacecraft operating conditions, the main reasons of heating and thermal gradient appearance and need to reassign the thermal energy. Active thermal control systems and their advantages are considered, spacecraft for which the use of this type of thermal control systems is a priority. The electric pumping unit is pointed as a key unit of active thermal control systems. The electric pump unit is considered from the as the electromechanical system, its key elements are pointed. A description of the preferred pump types is reported and the types of active thermal control systems are briefly discussed. The foreign and domestic operating experience of spacecraft electric pumping units, the features of their designs are considered, the most common types of key elements are determined. Based on the results of the review, it is concluded that the most relevant layout of the electric pump unit is a centrifugal electrical pump with a brushless DC motor and hydrodynamic bearings. It is also indicated that the electric pump unit is a product with a long lifetime, which complicates the task of monitoring the technical condition in order to prevent failure.
{"title":"Overview of electric pump units for spacecraft thermal control systems","authors":"E. B. Korotkov, O. Shirobokov, S. Matveev, Z. A. Yudina","doi":"10.26732/j.st.2021.4.03","DOIUrl":"https://doi.org/10.26732/j.st.2021.4.03","url":null,"abstract":"The paper reports a brief description of spacecraft operating conditions, the main reasons of heating and thermal gradient appearance and need to reassign the thermal energy. Active thermal control systems and their advantages are considered, spacecraft for which the use of this type of thermal control systems is a priority. The electric pumping unit is pointed as a key unit of active thermal control systems. The electric pump unit is considered from the as the electromechanical system, its key elements are pointed. A description of the preferred pump types is reported and the types of active thermal control systems are briefly discussed. The foreign and domestic operating experience of spacecraft electric pumping units, the features of their designs are considered, the most common types of key elements are determined. Based on the results of the review, it is concluded that the most relevant layout of the electric pump unit is a centrifugal electrical pump with a brushless DC motor and hydrodynamic bearings. It is also indicated that the electric pump unit is a product with a long lifetime, which complicates the task of monitoring the technical condition in order to prevent failure.","PeriodicalId":33896,"journal":{"name":"Kosmicheskie apparaty i tekhnologii","volume":" ","pages":""},"PeriodicalIF":0.0,"publicationDate":"2021-12-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"48087275","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}
Reducing the time for carrying out the strength analysis of a structure in the process of manufacturing shaping tooling using modern tools of virtual computer design and modeling, namely mathematical 3D modeling in a small-scale production with the use of additive technologies, is the main task. With the help of numerical discretization, the investigated model is divided into a finite set of elements, which can take any form of the element and be defined in different reference systems. This will make it possible to predict approximately numerically the behavior of the material during its deformation under the action of the given loads applied to the 3D model. The use of additive technologies with the use of modern computer modeling, which is based on software, is an urgent task. This approach will make it possible to develop equipment with a complex geometric shape, bypassing the stage of writing control programs and performing labor-intensive operations for the primary processing of the product. This method is based on the process of constructing a 3D model of the shaping tooling that repeats the shape of the reflective surface of the reflector, using modified high-temperature engineering plastics. The process of evaluating the effectiveness of the developed model is shown on the basis of strength calculations, safety factor, deformation, static stress and displacement. The results of the work can be used in the design and manufacture of dimensionally stable products of complex geometric shapes from non-metallic materials used in the aerospace industry.
{"title":"Development and modeling of non-metallic form-forming rigger for manufacture of polymer composition reflectors for satellite antennas","authors":"M. A. Dremukhin, V. N. Nagovitsin","doi":"10.26732/j.st.2021.4.01","DOIUrl":"https://doi.org/10.26732/j.st.2021.4.01","url":null,"abstract":"Reducing the time for carrying out the strength analysis of a structure in the process of manufacturing shaping tooling using modern tools of virtual computer design and modeling, namely mathematical 3D modeling in a small-scale production with the use of additive technologies, is the main task. With the help of numerical discretization, the investigated model is divided into a finite set of elements, which can take any form of the element and be defined in different reference systems. This will make it possible to predict approximately numerically the behavior of the material during its deformation under the action of the given loads applied to the 3D model. The use of additive technologies with the use of modern computer modeling, which is based on software, is an urgent task. This approach will make it possible to develop equipment with a complex geometric shape, bypassing the stage of writing control programs and performing labor-intensive operations for the primary processing of the product. This method is based on the process of constructing a 3D model of the shaping tooling that repeats the shape of the reflective surface of the reflector, using modified high-temperature engineering plastics. The process of evaluating the effectiveness of the developed model is shown on the basis of strength calculations, safety factor, deformation, static stress and displacement. The results of the work can be used in the design and manufacture of dimensionally stable products of complex geometric shapes from non-metallic materials used in the aerospace industry.","PeriodicalId":33896,"journal":{"name":"Kosmicheskie apparaty i tekhnologii","volume":" ","pages":""},"PeriodicalIF":0.0,"publicationDate":"2021-12-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"46691668","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}
The vast majority of spacecraft use solar panels as their primary energy source. The widespread using of solar cells is due to the simplicity of the design, reliability, environmental safety and minimal impact on the electronics and radio elements of the spacecraft. The development of new, larger spacecraft is driven by increasing demands on their functionality. These requirements lead to the need to provide more and more payload capacity of the spacecraft, the growth of its mass. There are solar batteries with different types of substrate: flexible, semi-rigid and rigid. Many years of experience in the development and application of solar panels have led to the fact that domestic spacecraft in most designs use solar panels with a semi-rigid substrate consisting of pipes, fittings and strings. This design of the substrate has characteristics at the level of world analogues. The increase in the mass of the payload can be compensated by a decrease in the mass of the power supply system. Thus, to improve the mass-dimensional characteristics, it is possible to optimize the design of the main load-bearing elements-pipes, which implies a more efficient use of the material (reducing the margin of safety with constant rigidity of the frame). The paper presents the results of the study of the possibility of modernizing the structure of the frames of planar solar cells, increasing their mass-dimensional characteristics. The studies were carried out by computational and experimental methods, and experimental samples of pipes were manufactured and released. As a result of the work, a frame made of triangular pipes and fittings was developed, and the mass and mechanical characteristics of the frame were determined.
{"title":"Solar battery frame made of pipes triangular cross-section","authors":"M. Volkov, V. V. Dvirny","doi":"10.26732/j.st.2021.3.05","DOIUrl":"https://doi.org/10.26732/j.st.2021.3.05","url":null,"abstract":"The vast majority of spacecraft use solar panels as their primary energy source. The widespread using of solar cells is due to the simplicity of the design, reliability, environmental safety and minimal impact on the electronics and radio elements of the spacecraft. The development of new, larger spacecraft is driven by increasing demands on their functionality. These requirements lead to the need to provide more and more payload capacity of the spacecraft, the growth of its mass. There are solar batteries with different types of substrate: flexible, semi-rigid and rigid. Many years of experience in the development and application of solar panels have led to the fact that domestic spacecraft in most designs use solar panels with a semi-rigid substrate consisting of pipes, fittings and strings. This design of the substrate has characteristics at the level of world analogues. The increase in the mass of the payload can be compensated by a decrease in the mass of the power supply system. Thus, to improve the mass-dimensional characteristics, it is possible to optimize the design of the main load-bearing elements-pipes, which implies a more efficient use of the material (reducing the margin of safety with constant rigidity of the frame). The paper presents the results of the study of the possibility of modernizing the structure of the frames of planar solar cells, increasing their mass-dimensional characteristics. The studies were carried out by computational and experimental methods, and experimental samples of pipes were manufactured and released. As a result of the work, a frame made of triangular pipes and fittings was developed, and the mass and mechanical characteristics of the frame were determined.","PeriodicalId":33896,"journal":{"name":"Kosmicheskie apparaty i tekhnologii","volume":" ","pages":""},"PeriodicalIF":0.0,"publicationDate":"2021-09-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"43786531","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 article discusses the process of deployment a two-link spoke of a large-sized transformable space-based reflector. In view of the high costs of carrying out field tests, the construction of correct mathematical models is an urgent task. Currently, the creation of large-sized systems is actively developing. Such systems consist of several interconnected links. When delivered to a given orbit, the large-sized system is folded for placement in the launch vehicle. After entering the orbit, it is deployed to the specified operating state. A mathematical model has been developed for the deployment of the spoke, improved in terms of taking into account the separation of parameters depending on the length and time, which makes it possible to study the arising vibrations of the structure. It is important to take into account the backlash in the connections. Even small gaps in the spoke link connections can lead to a manifold increase in the stabilization time of the system. The developed mathematical model makes it possible to consider various conditions for linking links, change the mass-dimensional parameters and materials of the spoke. The results of modeling are presented, showing the correctness of mathematical models. Conclusions are made about the admissibility of using mathematical models for spokes consisting of a larger number of links.
{"title":"Modeling the deployment of a two-link spoke of a large-sized space reflector taking into account the backlash","authors":"F. Mitin, E. N. Nikulin","doi":"10.26732/j.st.2021.3.03","DOIUrl":"https://doi.org/10.26732/j.st.2021.3.03","url":null,"abstract":"This article discusses the process of deployment a two-link spoke of a large-sized transformable space-based reflector. In view of the high costs of carrying out field tests, the construction of correct mathematical models is an urgent task. Currently, the creation of large-sized systems is actively developing. Such systems consist of several interconnected links. When delivered to a given orbit, the large-sized system is folded for placement in the launch vehicle. After entering the orbit, it is deployed to the specified operating state. A mathematical model has been developed for the deployment of the spoke, improved in terms of taking into account the separation of parameters depending on the length and time, which makes it possible to study the arising vibrations of the structure. It is important to take into account the backlash in the connections. Even small gaps in the spoke link connections can lead to a manifold increase in the stabilization time of the system. The developed mathematical model makes it possible to consider various conditions for linking links, change the mass-dimensional parameters and materials of the spoke. The results of modeling are presented, showing the correctness of mathematical models. Conclusions are made about the admissibility of using mathematical models for spokes consisting of a larger number of links.","PeriodicalId":33896,"journal":{"name":"Kosmicheskie apparaty i tekhnologii","volume":" ","pages":""},"PeriodicalIF":0.0,"publicationDate":"2021-09-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"48059769","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}
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. The radio electronic devices of the onboard equipment of the spacecraft are 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 groundbased experimental testing. The article discusses the stages of information support for the development of spacecraft onboard equipment, showing the ways to improve the technology of ground-based experimental testing of spacecraft onboard equipment. It is shown that at the present stage of development of the space industry, it has become possible to introduce the methodology of mathematical planning of an experiment into engineering practice. A backlog of applied work on radio-electronic topics h as appeared, showing the possibility of revealing in a full factorial experiment the influence of internal uncontrollable parameters (factors) of electronic components on the experimental results. This removed the obstacle to the implementation of the capabilities of the method in research and improvement of radio electronic devices onboard equipment.
{"title":"Stages of information support of development of on-board equipment for spacecraft","authors":"A. A. Kovel","doi":"10.26732/j.st.2021.3.06","DOIUrl":"https://doi.org/10.26732/j.st.2021.3.06","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. The radio electronic devices of the onboard equipment of the spacecraft are 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 groundbased experimental testing. The article discusses the stages of information support for the development of spacecraft onboard equipment, showing the ways to improve the technology of ground-based experimental testing of spacecraft onboard equipment. It is shown that at the present stage of development of the space industry, it has become possible to introduce the methodology of mathematical planning of an experiment into engineering practice. A backlog of applied work on radio-electronic topics h as appeared, showing the possibility of revealing in a full factorial experiment the influence of internal uncontrollable parameters (factors) of electronic components on the experimental results. This removed the obstacle to the implementation of the capabilities of the method in research and improvement of radio electronic devices onboard equipment.","PeriodicalId":33896,"journal":{"name":"Kosmicheskie apparaty i tekhnologii","volume":" ","pages":""},"PeriodicalIF":0.0,"publicationDate":"2021-09-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"44422934","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}
Z. A. Kazantsev, A. M. Eroshenko, L. A. Babkina, A. Lopatin
Solar arrays supply electrical power to spacecraft equipment and also provide charging of electrochemical batteries used in the shadow sections of the orbit. Photovoltaic converters of light energy of solar radiation form the basis of the solar battery. Their principle of operation is based on the phenomenon of the photoelectric effect. The article provides an overview of the development of solar cells and the classification of modern designs of solar cells for spacecraft. The review considers stationary and deployable solar batteries used both on the first spacecraft and on space stations. The classification of solar cell designs is made taking into account their characteristic features. These features are the rigidity of the supporting structure, the method of placement in the starting position and the method of orientation towards the light source. The classification covered rigid panel solar arrays, flexible substrate solar panels, inflatable solar arrays, self-expanding solar arrays, and solar concentrator panels. In each design group of this classification, corresponding examples of solar cells are presented. The presented review and classification makes it possible to track trends in the development of solar array designs for spacecraft.
{"title":"Analysis of design of spacecraft solar arrays","authors":"Z. A. Kazantsev, A. M. Eroshenko, L. A. Babkina, A. Lopatin","doi":"10.26732/j.st.2021.3.01","DOIUrl":"https://doi.org/10.26732/j.st.2021.3.01","url":null,"abstract":"Solar arrays supply electrical power to spacecraft equipment and also provide charging of electrochemical batteries used in the shadow sections of the orbit. Photovoltaic converters of light energy of solar radiation form the basis of the solar battery. Their principle of operation is based on the phenomenon of the photoelectric effect. The article provides an overview of the development of solar cells and the classification of modern designs of solar cells for spacecraft. The review considers stationary and deployable solar batteries used both on the first spacecraft and on space stations. The classification of solar cell designs is made taking into account their characteristic features. These features are the rigidity of the supporting structure, the method of placement in the starting position and the method of orientation towards the light source. The classification covered rigid panel solar arrays, flexible substrate solar panels, inflatable solar arrays, self-expanding solar arrays, and solar concentrator panels. In each design group of this classification, corresponding examples of solar cells are presented. The presented review and classification makes it possible to track trends in the development of solar array designs for spacecraft.","PeriodicalId":33896,"journal":{"name":"Kosmicheskie apparaty i tekhnologii","volume":" ","pages":""},"PeriodicalIF":0.0,"publicationDate":"2021-09-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"45715853","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}
At present, modern spacecraft use high-precision equipment that is sensitive to influence impacts. In this regard, there is a need to create shock-free trigger devices for mechanisms for holding and releasing movable structural elements. These tasks determined the vector of development of electromechanical trigger devices that do not contain pyrotechnic devices in their design. Along with the new tasks, there are constant problems of rocket and space technology – the improvement of mass-dimensional characteristics. However, pyrotechnic elements force the use of massive housings and brackets for structures that can withstand a sharp increase in pressure and the impact of the executive parts. The use of universal pyropatrons does not always allow optimizing the design of the retention mechanism. Also, one of the disadvantages of working with pyrotechnic media is the increased risk of working. The paper presents the results of a study of the possibility of modernizing the design of trigger devices, improving their mechanical and electrical characteristics. The research was carried out using calculated and experimental methods, and experimental samples of trigger devices were manufactured and released. As a result of the work, an upgraded trigger device was developed, better electrical characteristics were achieved, power consumption was reduced (the response time was reduced), mass-dimensional characteristics were improved, and the number of structural parts was reduced.
{"title":"Modernization of the electromechanical equipment the trigger device: description of the design and testing","authors":"M. Volkov","doi":"10.26732/j.st.2021.3.02","DOIUrl":"https://doi.org/10.26732/j.st.2021.3.02","url":null,"abstract":"At present, modern spacecraft use high-precision equipment that is sensitive to influence impacts. In this regard, there is a need to create shock-free trigger devices for mechanisms for holding and releasing movable structural elements. These tasks determined the vector of development of electromechanical trigger devices that do not contain pyrotechnic devices in their design. Along with the new tasks, there are constant problems of rocket and space technology – the improvement of mass-dimensional characteristics. However, pyrotechnic elements force the use of massive housings and brackets for structures that can withstand a sharp increase in pressure and the impact of the executive parts. The use of universal pyropatrons does not always allow optimizing the design of the retention mechanism. Also, one of the disadvantages of working with pyrotechnic media is the increased risk of working. The paper presents the results of a study of the possibility of modernizing the design of trigger devices, improving their mechanical and electrical characteristics. The research was carried out using calculated and experimental methods, and experimental samples of trigger devices were manufactured and released. As a result of the work, an upgraded trigger device was developed, better electrical characteristics were achieved, power consumption was reduced (the response time was reduced), mass-dimensional characteristics were improved, and the number of structural parts was reduced.","PeriodicalId":33896,"journal":{"name":"Kosmicheskie apparaty i tekhnologii","volume":" ","pages":""},"PeriodicalIF":0.0,"publicationDate":"2021-09-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"44544196","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}
The development of space transport systems for the delivery of payloads and the study of the lunar surface is an important scientific and technical challenge. The article considers a near-lunar space tether system consisting of a station and a microsatellite. The station is considered as a rigid body having a cylindrical shape, and the microsatellite is considered as a spherical rigid body. The tether is considered as a weightless inextensible rod of variable length. The station moves in a near-lunar orbit, which is influenced by the Earth's gravity. The process of deployment of a radially directed near-lunar tether system is considered. The equations of motion of the space tether system are obtained using Newton's second law and the theorem on the change in the angular momentum. To release the tether and bring the orbital tether system to a working state, the article proposes to use the control program of tethers tension force, which ensures the deployment of the tether system to a position close to the vertical. A comparison of the motion of the tether system along the unperturbed lunar orbit and along the perturbed one, taking into account the gravitational influence of the Earth, is made. To substantiate the theoretical results, a numerical simulation was carried out, based on the results of which a conclusion was made about the influence of the Earth's gravity on the amplitude of oscillations of the microsatellite relative to the local vertical.
{"title":"Analysis of the process of deployment of a lunar tether system taking into account the Earth's gravity","authors":"T. Ledkova, Y. Zabolotnov","doi":"10.26732/j.st.2021.3.04","DOIUrl":"https://doi.org/10.26732/j.st.2021.3.04","url":null,"abstract":"The development of space transport systems for the delivery of payloads and the study of the lunar surface is an important scientific and technical challenge. The article considers a near-lunar space tether system consisting of a station and a microsatellite. The station is considered as a rigid body having a cylindrical shape, and the microsatellite is considered as a spherical rigid body. The tether is considered as a weightless inextensible rod of variable length. The station moves in a near-lunar orbit, which is influenced by the Earth's gravity. The process of deployment of a radially directed near-lunar tether system is considered. The equations of motion of the space tether system are obtained using Newton's second law and the theorem on the change in the angular momentum. To release the tether and bring the orbital tether system to a working state, the article proposes to use the control program of tethers tension force, which ensures the deployment of the tether system to a position close to the vertical. A comparison of the motion of the tether system along the unperturbed lunar orbit and along the perturbed one, taking into account the gravitational influence of the Earth, is made. To substantiate the theoretical results, a numerical simulation was carried out, based on the results of which a conclusion was made about the influence of the Earth's gravity on the amplitude of oscillations of the microsatellite relative to the local vertical.","PeriodicalId":33896,"journal":{"name":"Kosmicheskie apparaty i tekhnologii","volume":" ","pages":""},"PeriodicalIF":0.0,"publicationDate":"2021-09-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"45418412","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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