Pub Date : 2016-12-01DOI: 10.17238/ISSN2409-0239.2016.4.41
A. Kalinin, V. Kalinin, M. Egorov, A. Akulov, M. Shirshov, A. E. Rogov
. This article discusses the current state of measuring technologies for the experimental study of radio characteristics of large antennas of ground control complexes in the centimeter wavelength range. The schematic diagrams and basic parameters of the prototypes of switching and correlational radiometers under development are presented, as well as the experimental results obtained with their use.
{"title":"Challenges of Hardware Development for Measurement of Large Antenna Characteristics by the Extraterrestrial Radio Sources","authors":"A. Kalinin, V. Kalinin, M. Egorov, A. Akulov, M. Shirshov, A. E. Rogov","doi":"10.17238/ISSN2409-0239.2016.4.41","DOIUrl":"https://doi.org/10.17238/ISSN2409-0239.2016.4.41","url":null,"abstract":". This article discusses the current state of measuring technologies for the experimental study of radio characteristics of large antennas of ground control complexes in the centimeter wavelength range. The schematic diagrams and basic parameters of the prototypes of switching and correlational radiometers under development are presented, as well as the experimental results obtained with their use.","PeriodicalId":436954,"journal":{"name":"Rocket-Space Device Engineering and Information Systems","volume":"174 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114258496","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 : 2016-12-01DOI: 10.17238/issn2409-0239.2016.4.16
V. V. Shavrin, V. I. Tislenko, V. Filimonov, V. Lebedev
An algorithm for constructing a multi-loop tracking system for radio navigation parameters of navigation satellite signals in the GNSS receivers of spacecraft is considered. The examined tracking scheme contains no discriminators for radio navigation parameters. The estimated delay, Doppler shift and phase are formed through the joint processing of quadrature signals of three correlators in the adaptive filter, consisting of several partial channels tuned to different values of the initial phase of the input signal. Quasi-optimal joint estimation of the parameters is performed using the Kalman sigma-point filter algorithm. The RMS error estimates and the probability of tracking failure for different signal-to-noise ratios are studied.
{"title":"Evaluation of the Radio Navigational Parameters of GNSS Signals in Coherent Adaptive Reception Mode Using the Kalman Sigma-Point Filter Algorithm","authors":"V. V. Shavrin, V. I. Tislenko, V. Filimonov, V. Lebedev","doi":"10.17238/issn2409-0239.2016.4.16","DOIUrl":"https://doi.org/10.17238/issn2409-0239.2016.4.16","url":null,"abstract":"An algorithm for constructing a multi-loop tracking system for radio navigation parameters of navigation satellite signals in the GNSS receivers of spacecraft is considered. The examined tracking scheme contains no discriminators for radio navigation parameters. The estimated delay, Doppler shift and phase are formed through the joint processing of quadrature signals of three correlators in the adaptive filter, consisting of several partial channels tuned to different values of the initial phase of the input signal. Quasi-optimal joint estimation of the parameters is performed using the Kalman sigma-point filter algorithm. The RMS error estimates and the probability of tracking failure for different signal-to-noise ratios are studied.","PeriodicalId":436954,"journal":{"name":"Rocket-Space Device Engineering and Information Systems","volume":"120 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126851668","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 : 2016-12-01DOI: 10.17238/issn2409-0239.2016.4.32
R. Andreev, Yu. M. Gektin, A. A. Zaytsev, M. B. Smelyanskiy
. Principal algorithms for processing of the images generated by the modern Russian Earth remote sensing (ERS) equipment MSU-GS (mounted on the geostationary spacecraft Elektro-L) in infrared range are presented in the article. The developed algorithms make it possible to perform signal correction, as well as compensate for an influence of a large number of factors: from operation features of electrical channels to alteration of temperature of the instrument case. The implementation of the algorithms reduces the difference in temperature equivalent to geometric and time noises to 0.1 K. It is necessary to mention that all algorithms are implemented in the standard complex for data processing obtained from MSU-GS.
{"title":"Special Algorithms for Radiometric Correction of ERS Images in Infrared Range","authors":"R. Andreev, Yu. M. Gektin, A. A. Zaytsev, M. B. Smelyanskiy","doi":"10.17238/issn2409-0239.2016.4.32","DOIUrl":"https://doi.org/10.17238/issn2409-0239.2016.4.32","url":null,"abstract":". Principal algorithms for processing of the images generated by the modern Russian Earth remote sensing (ERS) equipment MSU-GS (mounted on the geostationary spacecraft Elektro-L) in infrared range are presented in the article. The developed algorithms make it possible to perform signal correction, as well as compensate for an influence of a large number of factors: from operation features of electrical channels to alteration of temperature of the instrument case. The implementation of the algorithms reduces the difference in temperature equivalent to geometric and time noises to 0.1 K. It is necessary to mention that all algorithms are implemented in the standard complex for data processing obtained from MSU-GS.","PeriodicalId":436954,"journal":{"name":"Rocket-Space Device Engineering and Information Systems","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128528067","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 : 2016-12-01DOI: 10.17238/issn2409-0239.2016.4.65
V. Betanov, V. Larin
. The article deals with the concept of development of the basic engineering model of ballistic structure (BS) for the unmanned SC. The complete engineering model of the BS is a combination of the basic and the special models. Typically, such a model is needed to calculate the BS for a specific type of SC, which is the most frequent task in spacecraft design. The basis for development of the models are the so-called compliance matrixes for the factors of functional purpose (FFP) and BS. The latter are formed based on the statement of work (SOW) and the ballistic analysis data from the previous launches. The difference between the FFP data for the basic and the special engineering models (EM) lies in the difference of specific values of FFP and inclusion of additional values, characteristic for the SC under development, into the matrix. The proposed basic EM BS, based on the data of the functioning unmanned SC, makes it possible to calculate the majority of features of BS, greatly simplifying the process of designing new SC.
{"title":"Concept of Development of Basic Engineering Model for Ballistic Structure of Unmanned Spacecraft","authors":"V. Betanov, V. Larin","doi":"10.17238/issn2409-0239.2016.4.65","DOIUrl":"https://doi.org/10.17238/issn2409-0239.2016.4.65","url":null,"abstract":". The article deals with the concept of development of the basic engineering model of ballistic structure (BS) for the unmanned SC. The complete engineering model of the BS is a combination of the basic and the special models. Typically, such a model is needed to calculate the BS for a specific type of SC, which is the most frequent task in spacecraft design. The basis for development of the models are the so-called compliance matrixes for the factors of functional purpose (FFP) and BS. The latter are formed based on the statement of work (SOW) and the ballistic analysis data from the previous launches. The difference between the FFP data for the basic and the special engineering models (EM) lies in the difference of specific values of FFP and inclusion of additional values, characteristic for the SC under development, into the matrix. The proposed basic EM BS, based on the data of the functioning unmanned SC, makes it possible to calculate the majority of features of BS, greatly simplifying the process of designing new SC.","PeriodicalId":436954,"journal":{"name":"Rocket-Space Device Engineering and Information Systems","volume":"34 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123022457","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 : 2016-12-01DOI: 10.17238/issn2409-0239.2016.4.5
A. I. Zhodzishskiy, M. M. Berezentsev, O. V. Nesterov
{"title":"Current Issues of GNSS Civilian Usage in Russia","authors":"A. I. Zhodzishskiy, M. M. Berezentsev, O. V. Nesterov","doi":"10.17238/issn2409-0239.2016.4.5","DOIUrl":"https://doi.org/10.17238/issn2409-0239.2016.4.5","url":null,"abstract":"","PeriodicalId":436954,"journal":{"name":"Rocket-Space Device Engineering and Information Systems","volume":"62 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"117066855","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 : 2016-09-01DOI: 10.17238/ISSN2409-0239.2016.3.98
A. Selivanov
{"title":"Program Е-6: the First Soft Landing on the Moon and Transmission of the First Lunar Panorama","authors":"A. Selivanov","doi":"10.17238/ISSN2409-0239.2016.3.98","DOIUrl":"https://doi.org/10.17238/ISSN2409-0239.2016.3.98","url":null,"abstract":"","PeriodicalId":436954,"journal":{"name":"Rocket-Space Device Engineering and Information Systems","volume":"31 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114412574","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 : 2016-09-01DOI: 10.17238/ISSN2409-0239.2016.3.84
R.Yu. Dorofeev, D. Kozlov, I. Smirnov, A. Zhukov
. The paper discusses the results of system research of the functioning peculiarities and characteristics of a vibration electric field modulator. Modulator output signal values in electric field with intensity in the range of 0 ∼ 250 kV/m are obtained. The following main metrological characteristics of a microsystem vibration modulator are identified: sensitivity, sensitivity threshold, response time, and static pattern. The modulator is classified depending on the method for producing an output signal from the input value on the nature of dependency of the output signal on the input signal, type of action, and scope of use. In conclusion it is determined that it is possible to use the developed product for electric field control on the spacecraft in orbital conditions.
{"title":"Vibration Modulator for Electric Field Intensity Control in Orbital Conditions","authors":"R.Yu. Dorofeev, D. Kozlov, I. Smirnov, A. Zhukov","doi":"10.17238/ISSN2409-0239.2016.3.84","DOIUrl":"https://doi.org/10.17238/ISSN2409-0239.2016.3.84","url":null,"abstract":". The paper discusses the results of system research of the functioning peculiarities and characteristics of a vibration electric field modulator. Modulator output signal values in electric field with intensity in the range of 0 ∼ 250 kV/m are obtained. The following main metrological characteristics of a microsystem vibration modulator are identified: sensitivity, sensitivity threshold, response time, and static pattern. The modulator is classified depending on the method for producing an output signal from the input value on the nature of dependency of the output signal on the input signal, type of action, and scope of use. In conclusion it is determined that it is possible to use the developed product for electric field control on the spacecraft in orbital conditions.","PeriodicalId":436954,"journal":{"name":"Rocket-Space Device Engineering and Information Systems","volume":"115 19 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126375171","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 : 2016-09-01DOI: 10.17238/issn2409-0239.2016.3.63
А. Romanov, D. Shpotya
. This article justifies the importance of identification of critical technologies. Estimation of the most important engineering attributes using the project management approach, product lifecycles (PLC) and system engineering tools is considered to be the first important step before identification of critical technologies. Conventional system engineering instrument Quality Function Deployment (QFD) is emphasized as a basic tool. QFD consists of four phases (so called “Houses of quality”). The authors’ research showed that identification of critical technologies is possible during the second phase of QFD. The second phase must be initiated once the first phase is completed. The first phase possesses organizational and methodological disadvantages. Overcoming these disadvantages allowed the authors to propose an engineering technique named “Improved QFD” (IQFD). The authors describe the development process of the first PLC stage “concept development” of “Mayak” nanosatellite as a demonstration of IQFD functions: development of customer requirements, numeric fixing of correlations among engineering attributes in the House of Quality, utilization of determined weights of correlations during the final QFD ranking of each technical attribute. The IQFD ranking results are different from the QFD results. The analysis of the QFD and IQFD results and their comparison with an actual workflow of “Mayak” nanosatellite engineering verified and validated the correctness of the IQFD results and the inaccuracy of the QFD results.
{"title":"Basic Approach to Identification of Critical Technologies: Estimation of the Most Important Engineering Attributes of a Product","authors":"А. Romanov, D. Shpotya","doi":"10.17238/issn2409-0239.2016.3.63","DOIUrl":"https://doi.org/10.17238/issn2409-0239.2016.3.63","url":null,"abstract":". This article justifies the importance of identification of critical technologies. Estimation of the most important engineering attributes using the project management approach, product lifecycles (PLC) and system engineering tools is considered to be the first important step before identification of critical technologies. Conventional system engineering instrument Quality Function Deployment (QFD) is emphasized as a basic tool. QFD consists of four phases (so called “Houses of quality”). The authors’ research showed that identification of critical technologies is possible during the second phase of QFD. The second phase must be initiated once the first phase is completed. The first phase possesses organizational and methodological disadvantages. Overcoming these disadvantages allowed the authors to propose an engineering technique named “Improved QFD” (IQFD). The authors describe the development process of the first PLC stage “concept development” of “Mayak” nanosatellite as a demonstration of IQFD functions: development of customer requirements, numeric fixing of correlations among engineering attributes in the House of Quality, utilization of determined weights of correlations during the final QFD ranking of each technical attribute. The IQFD ranking results are different from the QFD results. The analysis of the QFD and IQFD results and their comparison with an actual workflow of “Mayak” nanosatellite engineering verified and validated the correctness of the IQFD results and the inaccuracy of the QFD results.","PeriodicalId":436954,"journal":{"name":"Rocket-Space Device Engineering and Information Systems","volume":"23 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115009710","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 : 2016-09-01DOI: 10.17238/ISSN2409-0239.2016.3.46
А. Chernov
. This article considers the problem of optimal allocation (scheduling) of target information (TI) reception sessions from the spacecraft of the ERS orbital constellation (OC) with a limited number of core ground segment (CGS) reception com-plexes (RC), and suggests its solution, taking into account the priorities of the TI and the possibility of simultaneous presence of several SC in the radio visibility zone (RVZ) of the receiving station (RS). The solution of the problem is carried out in two stages. The first step is to work out a criterion of efficiency of scheduling of the TI reception sessions. The criterion of effectiveness is based on the “weight matrix” (“priority matrix”), which determines the relative value of the TI reception sessions on the direct product of factors of the orbital constellation SC and all the CGS RC. The algorithm for the “weight matrix” calculation accommodates some a priori requirements of the OC operator, which he specifies for the end result of the scheduling. On the second stage the criterion of efficiency is used to set and solve the problem of optimal scheduling of the reception sessions [2]. The problems of the first and second stages are viewed as transportation problems of integer linear programming. Limita-tions and features of the problem of reception session scheduling make it possible to view it as the “assignment problem”, well known in integer linear programming. Examples of “weight matrix” calculation and optimal scheduling of reception sessions using the developed software are presented.
{"title":"Application of Linear Programming Methods in Scheduling of Reception Sessions of the Target Information from SC of ERS Orbital Constellation","authors":"А. Chernov","doi":"10.17238/ISSN2409-0239.2016.3.46","DOIUrl":"https://doi.org/10.17238/ISSN2409-0239.2016.3.46","url":null,"abstract":". This article considers the problem of optimal allocation (scheduling) of target information (TI) reception sessions from the spacecraft of the ERS orbital constellation (OC) with a limited number of core ground segment (CGS) reception com-plexes (RC), and suggests its solution, taking into account the priorities of the TI and the possibility of simultaneous presence of several SC in the radio visibility zone (RVZ) of the receiving station (RS). The solution of the problem is carried out in two stages. The first step is to work out a criterion of efficiency of scheduling of the TI reception sessions. The criterion of effectiveness is based on the “weight matrix” (“priority matrix”), which determines the relative value of the TI reception sessions on the direct product of factors of the orbital constellation SC and all the CGS RC. The algorithm for the “weight matrix” calculation accommodates some a priori requirements of the OC operator, which he specifies for the end result of the scheduling. On the second stage the criterion of efficiency is used to set and solve the problem of optimal scheduling of the reception sessions [2]. The problems of the first and second stages are viewed as transportation problems of integer linear programming. Limita-tions and features of the problem of reception session scheduling make it possible to view it as the “assignment problem”, well known in integer linear programming. Examples of “weight matrix” calculation and optimal scheduling of reception sessions using the developed software are presented.","PeriodicalId":436954,"journal":{"name":"Rocket-Space Device Engineering and Information Systems","volume":"18 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128030100","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 : 2016-09-01DOI: 10.17238/ISSN2409-0239.2016.3.89
V. Alybin, A. Semochkin
This article deals with development considerations and parameters of solid-state power amplifiers (SSPA) for onboard command and measurement systems (OCMS). The paper suggests solutions of problems common for spacecraft: reliability control, input power increase, efficiency, reduction of weight dimension characteristics, improvement of radiation resistance, etc. Matters of redundancy and output power switching without efficiency loss are discussed; trends of SSPA development and the image of future SSPA are formulated.
{"title":"Onboard Microwave Solid-State Power Amplifiers for Future Command and Measurement Systems","authors":"V. Alybin, A. Semochkin","doi":"10.17238/ISSN2409-0239.2016.3.89","DOIUrl":"https://doi.org/10.17238/ISSN2409-0239.2016.3.89","url":null,"abstract":"This article deals with development considerations and parameters of solid-state power amplifiers (SSPA) for onboard command and measurement systems (OCMS). The paper suggests solutions of problems common for spacecraft: reliability control, input power increase, efficiency, reduction of weight dimension characteristics, improvement of radiation resistance, etc. Matters of redundancy and output power switching without efficiency loss are discussed; trends of SSPA development and the image of future SSPA are formulated.","PeriodicalId":436954,"journal":{"name":"Rocket-Space Device Engineering and Information Systems","volume":"12 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122757375","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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