Rocket-Space Device Engineering and Information Systems最新文献_第2页

Sampling Theorem and Practical Usage of Entire Functions for Signal Representation on the Receiving Side 接收端信号表示全函数的采样定理和实际应用

Rocket-Space Device Engineering and Information Systems Pub Date : 2018-03-01 DOI: 10.30894/issn2409-0239.2018.5.1.81.85

A. I. Troshchenkov

引用次数: 0

Calculation of Antenna Gain via 3D Radiation Pattern and Estimation of Their Mutual Influence 基于三维辐射方向图的天线增益计算及其相互影响的估计

Rocket-Space Device Engineering and Information Systems Pub Date : 2018-03-01 DOI: 10.30894/issn2409-0239.2018.5.1.75.80

V. I. Tolkachev, O. G. Pikalov, S. V. Pan’chev, I. Novikov

引用次数: 0

A Method of Analytical Calculation of SER and BER for APSK Modulation in the Nonlinear Channel with AWGN 非线性AWGN信道中APSK调制SER和BER的解析计算方法

Rocket-Space Device Engineering and Information Systems Pub Date : 2017-11-01 DOI: 10.17238/ISSN2409-0239.2017.4.83

A. Strukov

引用次数: 0

Sixth Technological Way in Space Device Engineering 空间装置工程第六技术途径

Rocket-Space Device Engineering and Information Systems Pub Date : 2017-11-01 DOI: 10.17238/ISSN2409-0239.2017.4.64

A. Romanov, А. Tyulin

引用次数: 1

Small Satellites Clusters — a New Type of Space Objects 小型卫星群——一种新型空间物体

Rocket-Space Device Engineering and Information Systems Pub Date : 2017-11-01 DOI: 10.17238/issn2409-0239.2017.4.45

A. Y. Potyupkin, N. Danilin, A. Selivanov

引用次数: 2

Comparative Analysis of Global Augmentations to the GLONASS System GLONASS系统全球增强的比较分析

Rocket-Space Device Engineering and Information Systems Pub Date : 2017-11-01 DOI: 10.17238/ISSN2409-0239.2017.4.3

S. I. Vatutin, A. Biryukov, I. Kurkov

{"title":"Comparative Analysis of Global Augmentations to the GLONASS System","authors":"S. I. Vatutin, A. Biryukov, I. Kurkov","doi":"10.17238/ISSN2409-0239.2017.4.3","DOIUrl":"https://doi.org/10.17238/ISSN2409-0239.2017.4.3","url":null,"abstract":". This article considers two possible directions of the GLONASS system expansion to improve the accuracy on a global scale, namely, the creation of a second GLONASS orbital constellation comprising 24 additional navigation satellites in three intermediate planes and the creation of a high-orbit augmentation to the GLONASS system comprising 18 navigation satellites with six subsatellite traces on circular geosynchronous inclined orbits with three satellites on each track. It is shown that in a wide range of shading angles the dual GLONASS has a clear advantage over the GLONASS system with a high-orbit augmentation by the maximum time fraction criterion for the provision of the guaranteed positioning precision when the position dilution of precision is less than 6. Based on the available experimental data of high-orbit spacecraft launch using upper-stage rockets, it is shown that doubling the GLONASS grouping has lower costs than creating a global high-orbital satellite augmentation. The dual GLONASS has a three times lower dispersion in positioning accuracy at different longitudes with the same latitude of the observation point than the GLONASS with a high-orbital augmentation. The paper proposes a method for augmentation of the GLONASS orbital constellation by using additional distance-measurement maximum length sequences having a low cross-correlation with the current distance-measurement code.","PeriodicalId":436954,"journal":{"name":"Rocket-Space Device Engineering and Information Systems","volume":"50 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-11-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134061691","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}

引用次数: 1

Simulation Results of the Global Coverage Area of the Medium Earth Orbit Segment of the COSPAS–SARSAT System COSPAS-SARSAT系统中地球轨道段全球覆盖面积模拟结果

Rocket-Space Device Engineering and Information Systems Pub Date : 2017-11-01 DOI: 10.17238/ISSN2409-0239.2017.4.24

D. Antonov, A. Romanov

{"title":"Simulation Results of the Global Coverage Area of the Medium Earth Orbit Segment of the COSPAS–SARSAT System","authors":"D. Antonov, A. Romanov","doi":"10.17238/ISSN2409-0239.2017.4.24","DOIUrl":"https://doi.org/10.17238/ISSN2409-0239.2017.4.24","url":null,"abstract":". The results of the mathematical simulation of the coverage area of the MEOSAR of the COSPAS–SARSAT system for the planned date of the full operation capability (FOC) are presented (FOC is expected to begin in 2020) in this article. It is shown that the globality of the coverage area of the MEOSAR segment for the planned data by means of the standalone stations cannot be achieved because of the slow moving distress beacons in the system. The paper demonstrates that the integration of the ground stations of one National Administration into one station with the geographically distributed antennas, as well as a specialized procedure of schedule planning, are a potential solution to the problem of achieving the globality of the coverage area of the MEOSAR segment of COSPAS–SARSAT program. Based on the example of the planned Russian MEOLUT with 12 antennas (6 antennas in Moscow and 6 antennas in the Russian Far East), the article shows that it is possible to optimize the coverage area, which increases the coverage in the Russian Far East and in the Pacific Region (that might have problems with the MEOSAR coverage) owning to the decrease in the coverage area in Western Europe (where there is a sufficient number of other MEOLUTs). Potentially, the optimization of the MEOLUTs schedules and a shift of their coverage areas in the zones of the insufficient MEOSAR coverage can help to achieve the global service of MEOSAR.","PeriodicalId":436954,"journal":{"name":"Rocket-Space Device Engineering and Information Systems","volume":"91 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-11-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115172689","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}

引用次数: 0

Elimination of Weighted Differences Bias in Pseudoranges Obtained by a Dual-Frequency SRNS Receiver GPS+GLONASS 双频SRNS接收机GPS+GLONASS伪距加权差分偏差的消除

Rocket-Space Device Engineering and Information Systems Pub Date : 2017-11-01 DOI: 10.17238/ISSN2409-0239.2017.4.15

V. E. Vovasov, D. N. Chunin

引用次数: 0

Import Substitution or Import Independence. Searching for the Alternatives when Creating Radio Electronic Equipment 进口替代或进口独立。在创建无线电电子设备时寻找替代方案

Rocket-Space Device Engineering and Information Systems Pub Date : 2017-11-01 DOI: 10.17238/ISSN2409-0239.2017.4.89

K. V. Egorov, S. P. Tyazhkun, V. D. Khodzhaev

{"title":"Import Substitution or Import Independence. Searching for the Alternatives when Creating Radio Electronic Equipment","authors":"K. V. Egorov, S. P. Tyazhkun, V. D. Khodzhaev","doi":"10.17238/ISSN2409-0239.2017.4.89","DOIUrl":"https://doi.org/10.17238/ISSN2409-0239.2017.4.89","url":null,"abstract":". The paper offers an alternative way for solving some issues of import independence in the field of radio electronic equipment in the space industry. The offered solution is based on the system approach when considering the range of the electronic component base (ECB) not as independent components, but the elements of a higher level system. Moreover, the article shows that coping or functional reproducing even the local subset of foreign ECB is economically and technically unpromising. The radio electronic equipment for aerospace purposes does not need outstanding technological parameters of ECB. Although, unification and stability of technological processes are required to provide a high reliability of the products. In addition, succession and unification of the interfaces of wire lines, sensors, sensor-converting equipment, and algorithmic base is needed. Under such conditions, the influence of weight, dimensions, power consumption, and reliability of the above-mentioned devices on the parameters of the onboard system is constantly growing. Consideration of these design features makes it possible to have a well-grounded confidence in the success not in literal import substitution, but in providing import independence, which is achieved using the items with the maximum influence on the parameters of the upper level systems.","PeriodicalId":436954,"journal":{"name":"Rocket-Space Device Engineering and Information Systems","volume":"7 5 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-11-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130832891","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}

引用次数: 0

Obtaining Optical Images of LEO Space Objects during Satellite Monitoring on the Crossing Courses 低轨空间物体在卫星监测过程中的光学图像获取

Rocket-Space Device Engineering and Information Systems Pub Date : 2017-11-01 DOI: 10.17238/issn2409-0239.2017.4.35

V. Lagutkin, A. Luk’yanov

{"title":"Obtaining Optical Images of LEO Space Objects during Satellite Monitoring on the Crossing Courses","authors":"V. Lagutkin, A. Luk’yanov","doi":"10.17238/issn2409-0239.2017.4.35","DOIUrl":"https://doi.org/10.17238/issn2409-0239.2017.4.35","url":null,"abstract":". The possibilities of using space sensors to obtain images of LEO space objects with the linear resolution at the level of 10–20 cm are considered in the article. A combined simulation of the passive orbital movement on time intervals of one and two years of a subset of LEO space objects and a hypothetical space sensor for various inclinations of its orbit is carried out. The statistics of rendezvous at the flight on the crossing courses of the space sensor with space objects is calculated on the distances about tens of kilometers taking into account the restriction for the maximum phase angle of observation (an angle: Sun–object–sensor) and the conditions of the lack of the Earth’s background. It is shown that one space sensor in a passive flight can carry out photography from the distances no more than 50 km within one year — not less than 80 %, within two years — not less than 90% of the space objects of interest. The basic principles of the operation of the space sensor are formulated. It is offered to use a sweeping method applied in the space systems of Earth remote sensing for the realization of such principles. The features and difficulties of the application of this method for photography of the space objects, which are flying by with big angular speeds, are considered. The option of the shape of the retargeted controlled on-board optoelectronic camera with the instrumental resolution at the level of 0.4 angular seconds for the space sensor to obtain images of space objects at the flight on the crossing courses is presented.","PeriodicalId":436954,"journal":{"name":"Rocket-Space Device Engineering and Information Systems","volume":"6 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-11-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133132066","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}

引用次数: 0