Pub Date : 2016-09-01DOI: 10.17238/issn2409-0239.2016.3.4
S. N. Boyko, A. V. Isaev, S. V. Kosyakin, Yury S. Yaskin
The article describes original design methods of navigational antenna modules for the global navigation satellite system (GNSS) equipment. The uncased technology for antenna modules production using metamaterials in the antenna element improving its characteristics, special EBG-metamaterial and a method for its installation into the geodesic antenna module to reduce the multibeam effect, common application of an uncased antenna module with a navigational receiver are used. The approaches to the design of navigational modules result in overall dimensions minimization, production cost decrease, items manufacturability, and improved technical and operational characteristics.
{"title":"Navigational Antenna Modules of the GNSS Equipment","authors":"S. N. Boyko, A. V. Isaev, S. V. Kosyakin, Yury S. Yaskin","doi":"10.17238/issn2409-0239.2016.3.4","DOIUrl":"https://doi.org/10.17238/issn2409-0239.2016.3.4","url":null,"abstract":"The article describes original design methods of navigational antenna modules for the global navigation satellite system (GNSS) equipment. The uncased technology for antenna modules production using metamaterials in the antenna element improving its characteristics, special EBG-metamaterial and a method for its installation into the geodesic antenna module to reduce the multibeam effect, common application of an uncased antenna module with a navigational receiver are used. The approaches to the design of navigational modules result in overall dimensions minimization, production cost decrease, items manufacturability, and improved technical and operational characteristics.","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":"133764857","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/ISSN2409-0239.2016.3.12
S. I. Vatutin
Movement patterns of 24 GLONASS spacecraft and 6 highly elliptical augmentation spacecraft on the Tundra and QZSS orbits are generated. The programs for calculating the influence of geometric factor on the measurement accuracy of user coordinates in various geographical points by navigation spacecraft are developed in MathCAD. Moreover, a comparison of the geometric factors for the GLONASS constellation including 24 spacecraft and 6 spacecraft on highly elliptical orbits is made. It is shown that a highly elliptical augmentation of the GLONASS system reduces the geometric factor by 20–30% during the operation within 10–20 degrees field of view and significantly improves the geometric factor during the work in mountainous and urban environment. The results obtained can be used in designing a highly elliptical augmentation for the GLONASS system.
{"title":"Estimation of Geometric Factor for a User of GLONASS System with Highly Elliptical Augmentation","authors":"S. I. Vatutin","doi":"10.17238/ISSN2409-0239.2016.3.12","DOIUrl":"https://doi.org/10.17238/ISSN2409-0239.2016.3.12","url":null,"abstract":"Movement patterns of 24 GLONASS spacecraft and 6 highly elliptical augmentation spacecraft on the Tundra and QZSS orbits are generated. The programs for calculating the influence of geometric factor on the measurement accuracy of user coordinates in various geographical points by navigation spacecraft are developed in MathCAD. Moreover, a comparison of the geometric factors for the GLONASS constellation including 24 spacecraft and 6 spacecraft on highly elliptical orbits is made. It is shown that a highly elliptical augmentation of the GLONASS system reduces the geometric factor by 20–30% during the operation within 10–20 degrees field of view and significantly improves the geometric factor during the work in mountainous and urban environment. The results obtained can be used in designing a highly elliptical augmentation for the GLONASS system.","PeriodicalId":436954,"journal":{"name":"Rocket-Space Device Engineering and Information Systems","volume":"4 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":"122369554","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/ISSN2409-0239.2016.3.29
D. Shelestov, D. A. Tyurikov, A. Pnev, M. Gubin
. Utilization of methane optical frequency standard is promising for precision frequency measurements, in particular, it is a possible future mobile (and on-board) frequency standard with stability of 5 · 10 − 15 –5 · 10 − 16 , which will be used in frequency-time segment of GNS GLONASS. This paper deals with development of a digital frequency detector, designed to increase the methane standard short-term frequency stability. Accuracy of digital frequency counting algorithms is calculated. A numerical simulation of programmable logic device operation is conducted, which confirms the operability of a single channel synchronous-frequency detector with Allan variance of 1,4 · 10 − 13 per 1 s, and also provides a technology to increase the accuracy of the counting, allowing one to measure the Allan variance at 5,6 · 10 − 16 per 1 s.
{"title":"Digital Frequency Detecting Device for Mobile Methane Frequency Standard","authors":"D. Shelestov, D. A. Tyurikov, A. Pnev, M. Gubin","doi":"10.17238/ISSN2409-0239.2016.3.29","DOIUrl":"https://doi.org/10.17238/ISSN2409-0239.2016.3.29","url":null,"abstract":". Utilization of methane optical frequency standard is promising for precision frequency measurements, in particular, it is a possible future mobile (and on-board) frequency standard with stability of 5 · 10 − 15 –5 · 10 − 16 , which will be used in frequency-time segment of GNS GLONASS. This paper deals with development of a digital frequency detector, designed to increase the methane standard short-term frequency stability. Accuracy of digital frequency counting algorithms is calculated. A numerical simulation of programmable logic device operation is conducted, which confirms the operability of a single channel synchronous-frequency detector with Allan variance of 1,4 · 10 − 13 per 1 s, and also provides a technology to increase the accuracy of the counting, allowing one to measure the Allan variance at 5,6 · 10 − 16 per 1 s.","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":"127244020","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/issn2409-0239.2016.3.76
D. Klimov, V. A. Blagodyryov
The termovideosystem with possibility of use of thermoprotection and protection of objectives and devices with charging communication from influence of radiating factors for videocameras, the space vehicles located near to thermoloaded elements and carrier rockets for tracing of thermoconditions by means of video telemetry is considered. The thermocasing model, its key parametres and characteristics is presented. Expressions for selection of a thickness of a thermolayer depending on flying time of carrier rockets, and also a thickness of a thermolayer for preset time of influence of temperature are received. The example of thermoprotection videocameras with the set diameter of a eye of an objective and flying time of carrier rockets for a basic orbit is resulted. It is offered to use the periscopic device for protection against influence of radiating factors of lenses of objectives and devices with charging communication. Expressions for the size of mirrors of a periscope, and also for an angle of rotation of mirrors of periscopes are resulted at simultaneous use of two videocameras directed on one image box of object.
{"title":"ThermoVideoSystem for Installation on Spacecraft","authors":"D. Klimov, V. A. Blagodyryov","doi":"10.17238/issn2409-0239.2016.3.76","DOIUrl":"https://doi.org/10.17238/issn2409-0239.2016.3.76","url":null,"abstract":"The termovideosystem with possibility of use of thermoprotection and protection of objectives and devices with charging communication from influence of radiating factors for videocameras, the space vehicles located near to thermoloaded elements and carrier rockets for tracing of thermoconditions by means of video telemetry is considered. The thermocasing model, its key parametres and characteristics is presented. Expressions for selection of a thickness of a thermolayer depending on flying time of carrier rockets, and also a thickness of a thermolayer for preset time of influence of temperature are received. The example of thermoprotection videocameras with the set diameter of a eye of an objective and flying time of carrier rockets for a basic orbit is resulted. It is offered to use the periscopic device for protection against influence of radiating factors of lenses of objectives and devices with charging communication. Expressions for the size of mirrors of a periscope, and also for an angle of rotation of mirrors of periscopes are resulted at simultaneous use of two videocameras directed on one image box of object.","PeriodicalId":436954,"journal":{"name":"Rocket-Space Device Engineering and Information Systems","volume":"44 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":"128082829","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/ISSN2409-0239.2016.3.35
V. Selivanov, Yu.M. Gekhtin, V. Budak
. The operation analysis of a broad class of multi-angle video polarimeter systems is carried out. The problems of improving the polarization measurement reliability of the atmosphere and the underlying surface are considered. The possibilities of reducing the dimension of the display information are analyzed.
{"title":"The Tasks of Polarization Remote Sensing in Optical Band","authors":"V. Selivanov, Yu.M. Gekhtin, V. Budak","doi":"10.17238/ISSN2409-0239.2016.3.35","DOIUrl":"https://doi.org/10.17238/ISSN2409-0239.2016.3.35","url":null,"abstract":". The operation analysis of a broad class of multi-angle video polarimeter systems is carried out. The problems of improving the polarization measurement reliability of the atmosphere and the underlying surface are considered. The possibilities of reducing the dimension of the display information are analyzed.","PeriodicalId":436954,"journal":{"name":"Rocket-Space Device Engineering and Information Systems","volume":"192 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":"131446280","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/issn2409-0239.2016.3.54
A. Kalinin, N. Dugin, S. P. Moiseev, A. V. Polyakov, V. Vatutin, A. Ivashina
This article considers the capabilities of known methods of characteristics measurement for large ground-based antennas in the microwave range. In addition to the well-known radio-astronomical method, capable of measuring the power directivity pattern and absolute gain, a radio holographic antenna measurement method is considered. A significant advantage of the latter method is the ability to reconstruct the distribution of field amplitude and phase in the aperture, which enables one to conduct additional targeted adjustment of a parabolic antenna system in order to increase its gain. This adjustment is particularly relevant for the ongoing effort to upgrade larger parabolic antennas of ground-based command systems and utilize their higher frequency ranges. Measurement techniques of natural signals from extraterrestrial radio sources, as well as geostationary satellites, designed for fully steerable parabolic antennas are discussed. The paper presents experimental results of measurement of power directivity and field distribution patterns in aperture, received with radio-astronomical and radio-holographic methods from the largest Russian fully steerable ground-based antennas with reflectors from 25 to 70 meters large.
{"title":"Exploratory Test of Radio-Technical Characteristics of Antennas of Ground-Based Command Complexes","authors":"A. Kalinin, N. Dugin, S. P. Moiseev, A. V. Polyakov, V. Vatutin, A. Ivashina","doi":"10.17238/issn2409-0239.2016.3.54","DOIUrl":"https://doi.org/10.17238/issn2409-0239.2016.3.54","url":null,"abstract":"This article considers the capabilities of known methods of characteristics measurement for large ground-based antennas in the microwave range. In addition to the well-known radio-astronomical method, capable of measuring the power directivity pattern and absolute gain, a radio holographic antenna measurement method is considered. A significant advantage of the latter method is the ability to reconstruct the distribution of field amplitude and phase in the aperture, which enables one to conduct additional targeted adjustment of a parabolic antenna system in order to increase its gain. This adjustment is particularly relevant for the ongoing effort to upgrade larger parabolic antennas of ground-based command systems and utilize their higher frequency ranges. Measurement techniques of natural signals from extraterrestrial radio sources, as well as geostationary satellites, designed for fully steerable parabolic antennas are discussed. The paper presents experimental results of measurement of power directivity and field distribution patterns in aperture, received with radio-astronomical and radio-holographic methods from the largest Russian fully steerable ground-based antennas with reflectors from 25 to 70 meters large.","PeriodicalId":436954,"journal":{"name":"Rocket-Space Device Engineering and Information Systems","volume":"3 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":"129250106","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 : 2016-03-01DOI: 10.17238/issn2409-0239.2016.2.31
K. Sviridov
Negative influence of the atmospheric turbulence on the ERS systems is noted. Hardware and software technologies for partial correction of atmospheric influence are reviewed. A new algorithm for recovering the image undistorted by the atmosphere, which has a diffraction-limited resolution of the ERS telescope in its broad field of view, is proposed and proved. The offered algorithm makes easier and increases the rate for Earth remote sensing (ERS) images receiving. This algorithm enables to determine and reimburse its atmospheric distortions at digital statistic processing of the fragments of one registered image. The algorithm is a new and can be applied practically in the ERS systems.
{"title":"The Recovery Algorithm for Short-Exposure ERS Image, Space-Invariant to the Atmospheric Distortions","authors":"K. Sviridov","doi":"10.17238/issn2409-0239.2016.2.31","DOIUrl":"https://doi.org/10.17238/issn2409-0239.2016.2.31","url":null,"abstract":"Negative influence of the atmospheric turbulence on the ERS systems is noted. Hardware and software technologies for partial correction of atmospheric influence are reviewed. A new algorithm for recovering the image undistorted by the atmosphere, which has a diffraction-limited resolution of the ERS telescope in its broad field of view, is proposed and proved. The offered algorithm makes easier and increases the rate for Earth remote sensing (ERS) images receiving. This algorithm enables to determine and reimburse its atmospheric distortions at digital statistic processing of the fragments of one registered image. The algorithm is a new and can be applied practically in the ERS systems.","PeriodicalId":436954,"journal":{"name":"Rocket-Space Device Engineering and Information Systems","volume":"13 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123765162","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 : 2016-03-01DOI: 10.17238/issn2409-0239.2016.2.48
S. Medvedev, V. I. Shaposhnikov, O. A. Chekmazova
. The article contains the study of the algorithms of the weight impulse-type signal processing with linear frequency modulation in the radio engineering measurement system of parameters relative to the movement used for space vehicles docking. The aim of work is to increase the system working capacity due to eliminating the spurious signals reflected from the large-sized construction elements, for example from the International Space Station. Such spurious signals are received in the same time interval together with the useful signal that contains the data on the relative movement parameters. This can reduce the measurement accuracy of these parameters. In order to eliminate this effect, there was selected an broadband impulse signal with linear frequency modulation and digital processing of the received signal. Deterioration of the measurement accuracy caused by the sidelobes of the correlation function leads to the necessity to examine different ways of their reducing with the help of so called “mismatched reception” which has a distinctive feature of losses caused by the discrepancy. This work contains the research on measuring these losses depending upon the relation F KV /F DEV = K . Moreover, the best value of K when using this filter was found.
． 本文研究了空间飞行器对接相关运动参数无线电工程测量系统中线性调频加权脉冲型信号处理算法。工作的目的是通过消除大型构件(如国际空间站)反射的杂散信号来提高系统的工作能力。在相同的时间间隔内，与包含相对运动参数数据的有用信号一起接收这些杂散信号。这会降低这些参数的测量精度。为了消除这种影响，选择了宽带脉冲信号进行线性调频，并对接收信号进行数字处理。由于相关函数的副瓣导致测量精度的下降，因此有必要研究利用所谓的“不匹配接收”来降低其精度的不同方法，这种方法具有由差异引起的损失的显著特征。这项工作包含了根据F KV /F DEV = K关系测量这些损耗的研究。此外，还找到了使用该过滤器时K的最佳值。
{"title":"The Results of the Modeling and Estimate of the Characteristics of the Signals with Linear Frequency Modulation Reflected from the Spread Objects","authors":"S. Medvedev, V. I. Shaposhnikov, O. A. Chekmazova","doi":"10.17238/issn2409-0239.2016.2.48","DOIUrl":"https://doi.org/10.17238/issn2409-0239.2016.2.48","url":null,"abstract":". The article contains the study of the algorithms of the weight impulse-type signal processing with linear frequency modulation in the radio engineering measurement system of parameters relative to the movement used for space vehicles docking. The aim of work is to increase the system working capacity due to eliminating the spurious signals reflected from the large-sized construction elements, for example from the International Space Station. Such spurious signals are received in the same time interval together with the useful signal that contains the data on the relative movement parameters. This can reduce the measurement accuracy of these parameters. In order to eliminate this effect, there was selected an broadband impulse signal with linear frequency modulation and digital processing of the received signal. Deterioration of the measurement accuracy caused by the sidelobes of the correlation function leads to the necessity to examine different ways of their reducing with the help of so called “mismatched reception” which has a distinctive feature of losses caused by the discrepancy. This work contains the research on measuring these losses depending upon the relation F KV /F DEV = K . Moreover, the best value of K when using this filter was found.","PeriodicalId":436954,"journal":{"name":"Rocket-Space Device Engineering and Information Systems","volume":"36 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126297629","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 : 2016-03-01DOI: 10.17238/ISSN2409-0239.2016.2.38
I. Morozov, N. Danilin, N. Makukhin, A. Sergeev
Usage of the present global satellite communication systems of the general purpose for control of small-size spacecraft is considered to be a perspective and low-cost direction. The most suitable system to fulfill this task is the GLOBALSTAR system. For the first time a communication channel with this system was implemented on the nanosatellite TNS-0 No1 in 2005. The article shows the results of the comparative analysis of the experimental data received from TNS-0 No1 and a computer modeling of the mission conditions on the software package “Radio coverage zone of TNS-0”. Favourable communication conditions in which a technology for small-size spacecraft control with use of the GLOBALSTAR system is very effective, low-cost and operationally convenient, as well as realized both in stationary and mobile variants, are defined. It is determined that the area of space where communication can be possible is a so called “cone of communication” in which a small-size spacecraft, GLOBALSTAR spacecraft and ground gateways should be at one time. The article describes specific causes of lack of communication. Practical recommendations on increasing the amount and duration of communication sessions are given. A new way for communication channel organization using GLOBALSTAR satellite communication systems is proposed. The results of the ground tests are presented.
{"title":"Communication Canal of Small-Size Spacecraft on the Base of Space Communication System GLOBALSTAR","authors":"I. Morozov, N. Danilin, N. Makukhin, A. Sergeev","doi":"10.17238/ISSN2409-0239.2016.2.38","DOIUrl":"https://doi.org/10.17238/ISSN2409-0239.2016.2.38","url":null,"abstract":"Usage of the present global satellite communication systems of the general purpose for control of small-size spacecraft is considered to be a perspective and low-cost direction. The most suitable system to fulfill this task is the GLOBALSTAR system. For the first time a communication channel with this system was implemented on the nanosatellite TNS-0 No1 in 2005. The article shows the results of the comparative analysis of the experimental data received from TNS-0 No1 and a computer modeling of the mission conditions on the software package “Radio coverage zone of TNS-0”. Favourable communication conditions in which a technology for small-size spacecraft control with use of the GLOBALSTAR system is very effective, low-cost and operationally convenient, as well as realized both in stationary and mobile variants, are defined. It is determined that the area of space where communication can be possible is a so called “cone of communication” in which a small-size spacecraft, GLOBALSTAR spacecraft and ground gateways should be at one time. The article describes specific causes of lack of communication. Practical recommendations on increasing the amount and duration of communication sessions are given. A new way for communication channel organization using GLOBALSTAR satellite communication systems is proposed. The results of the ground tests are presented.","PeriodicalId":436954,"journal":{"name":"Rocket-Space Device Engineering and Information Systems","volume":"11951 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122472121","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 : 2016-03-01DOI: 10.17238/issn2409-0239.2016.2.60
A. S. Shchevelev, V. Kikot, A. Udalov
. The purpose of the research was to validate the choice of fiber-optic measuring instruments for space technology. It is shown that the information-measuring system meets the requirements of the system being operated in the special conditions of rocket and space engineering and of the objects of the ground space infrastructure. In addition, the task was to research the fiber-optic information-measuring system to determine the metrological characteristics and further evaluation of the system efficiency. The developed information-measuring system includes a fiber-optic strain and temperature sensors. The sensing tip of the fiber forms fiber bragg gratings (FBG). The temperature and strain readings are obtained by measuring the shift of the resonance FBG wavelength by the built-in spectrum analyzer. The results of the study showed that the sensitivity of the FBG was 11,2 pm/ ◦ C for the positive range (from 25 to 300 ◦ C) and 9,1 pm/ ◦ C — for the negative temperature range (from − 80 to 25 ◦ C). The deformation ratio of FBG in the range up to 1200 με (0,012 ε ) was K = 0,6 ± 0,3 [1 /με ]. The comparison of the calculated and experimental data showed minor discrepancy between the predicted and experimental values, which confirms the correctness of the constructive decision and system efficiency of the developed information-measurement system.
{"title":"The Information-Measuring System for Space Technology Monitoring","authors":"A. S. Shchevelev, V. Kikot, A. Udalov","doi":"10.17238/issn2409-0239.2016.2.60","DOIUrl":"https://doi.org/10.17238/issn2409-0239.2016.2.60","url":null,"abstract":". The purpose of the research was to validate the choice of fiber-optic measuring instruments for space technology. It is shown that the information-measuring system meets the requirements of the system being operated in the special conditions of rocket and space engineering and of the objects of the ground space infrastructure. In addition, the task was to research the fiber-optic information-measuring system to determine the metrological characteristics and further evaluation of the system efficiency. The developed information-measuring system includes a fiber-optic strain and temperature sensors. The sensing tip of the fiber forms fiber bragg gratings (FBG). The temperature and strain readings are obtained by measuring the shift of the resonance FBG wavelength by the built-in spectrum analyzer. The results of the study showed that the sensitivity of the FBG was 11,2 pm/ ◦ C for the positive range (from 25 to 300 ◦ C) and 9,1 pm/ ◦ C — for the negative temperature range (from − 80 to 25 ◦ C). The deformation ratio of FBG in the range up to 1200 με (0,012 ε ) was K = 0,6 ± 0,3 [1 /με ]. The comparison of the calculated and experimental data showed minor discrepancy between the predicted and experimental values, which confirms the correctness of the constructive decision and system efficiency of the developed information-measurement system.","PeriodicalId":436954,"journal":{"name":"Rocket-Space Device Engineering and Information Systems","volume":"736 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123856781","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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