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Gotowa bibliografia na temat „Satellite”

Autor: Grafiati

Data publikacji: 4 czerwca 2021

Data aktualizacji: 15 czerwca 2024

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Artykuły w czasopismach na temat "Satellite"

Shen, Ziyu, Wenbin Shen, Xinyu Xu, Shuangxi Zhang, Tengxu Zhang, Lin He, Zhan Cai, Si Xiong i Lingxuan Wang. "A Method for Measuring Gravitational Potential of Satellite’s Orbit Using Frequency Signal Transfer Technique between Satellites". Remote Sensing 15, nr 14 (12.07.2023): 3514. http://dx.doi.org/10.3390/rs15143514.

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We introduce an approach for the direct measurement of the gravitational potential (GP) along the trajectory of a satellite, with a specific focus on Low-Earth Orbit (LEO) satellites. A LEO satellite communicates with several Geosynchronous Equatorial Orbit (GEO) satellites via frequency signal links. The GP difference can be measured in real-time using the gravitational frequency shift approach by equipping both LEO and GEO satellites with precise atomic clocks. Since the GP at the high orbits of the GEO satellites can be precisely determined by the present gravitational field model EGM2008, the GP along the LEO satellite’s trajectory can be determined. In this study, simulation experiments were conducted, featuring a GRACE-type satellite as the LEO satellite in communication with three equidistant GEO satellites. The results indicated that the accuracy of the GP measurements along the LEO satellite’s trajectory primarily depends on the precision of the onboard atomic clocks. Supposing optical atomic clocks attain an instability level of 1×10−17τ−1/2 (τ in seconds), we determined the GP distribution covered by the LEO satellite’s trajectories with 30-day observations. Then, we determined a gravitational field at the centimeter level based on the GP distribution. The GP data derived from the trajectory of a LEO satellite can be utilized to establish temporal gravitational fields, which have broad applications in different disciplines.

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Wu, Huanqin, Maocai Wang, Zhiming Song, Xiaoyu Chen, Guangming Dai, Wei Zheng i Qingrui Zhou. "Random Error Analysis of Launch and Injection Positions for Distributed Multi Micro-nano Satellite System". Journal of Physics: Conference Series 2640, nr 1 (1.11.2023): 012014. http://dx.doi.org/10.1088/1742-6596/2640/1/012014.

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Abstract Accurate satellite orbit calculation has always been a focus in the aerospace field. Especially, the error distribution of the orbit involving various internal and external factors in the satellite launch process has an important influence on the effectiveness of the satellite cluster. To qualitatively and quantitatively analyze the cooperative efficiency of multi-satellite clusters involving various random errors, this paper analyzes the random error sources in the launch process of micro-nano satellites and studies the distribution law of these satellite orbit position errors. Based on the parameter estimation and the central limit theorem of probability theory, the expression of the error function for the satellite’s orbit position is also constructed. In addition, the probability distribution model of the satellites in a certain range is designed, and the relationship between the number of satellites and the overall errors is proposed. Finally, the result is verified by the simulation experiment, which provides the rationale behind the position and altitude adjustment and constellation optimization of micro-nano satellites.

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Tong, Minglei, Song Li, Xiaoxiang Wang i Peng Wei. "Inter-Satellite Cooperative Offloading Decision and Resource Allocation in Mobile Edge Computing-Enabled Satellite–Terrestrial Networks". Sensors 23, nr 2 (6.01.2023): 668. http://dx.doi.org/10.3390/s23020668.

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Mobile edge computing (MEC)-enabled satellite–terrestrial networks (STNs) can provide task computing services for Internet of Things (IoT) devices. However, since some applications’ tasks require huge amounts of computing resources, sometimes the computing resources of a local satellite’s MEC server are insufficient, but the computing resources of neighboring satellites’ MEC servers are redundant. Therefore, we investigated inter-satellite cooperation in MEC-enabled STNs. First, we designed a system model of the MEC-enabled STN architecture, where the local satellite and the neighboring satellites assist IoT devices in computing tasks through inter-satellite cooperation. The local satellite migrates some tasks to the neighboring satellites to utilize their idle resources. Next, the task completion delay minimization problem for all IoT devices is formulated and decomposed. Then, we propose an inter-satellite cooperative joint offloading decision and resource allocation optimization scheme, which consists of a task offloading decision algorithm based on the Grey Wolf Optimizer (GWO) algorithm and a computing resource allocation algorithm based on the Lagrange multiplier method. The optimal solution is obtained by continuous iterations. Finally, simulation results demonstrate that the proposed scheme achieves relatively better performance than other baseline schemes.

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Utami, Vi Bauty Riska, Imam MPB i Shinta Romadhona. "Analysis the impact of sun outage and satellite orbit at performance of the telkom 3S satellite communication system". JURNAL INFOTEL 13, nr 3 (31.08.2021): 134–42. http://dx.doi.org/10.20895/infotel.v13i3.626.

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Satellites of communication are located at altitude of thousands kilometers above the earth's surface, so the signal is transmitted by satellite to earth station is very susceptible to interference. Every March and September equinox or when the sun crosses the Earth's equator for several days, earth station occurs a naturally interference called by sun outage. At this time, satellite and the sun reach the closest distance because satellite's position is same direction with the sun. This interference makes the signal received by earth station weaken and even disappears due to temperature noise which increases drastically. Loss of signal on the downlink side caused by noise greatly affects to the performance of satellite communication system. This study aims to analyze the effect of sun outage and satellite orbit to determine sun outage period on the performance of Telkom 3S satellite communication system. The results obtained that indicate the signal quality is represented by degradation in the Carrier to Noise Ratio (C/N) from 14,777 dB to 6,0 dB, Energy bits per Noise Ratio (Eb/No) from 11,515 dB to 2,738 dB, and increase the Bit Error Rate (BER) from 8,29×10-7 to 11,08×10-3. In addition, sun outage makes lost of satellite communication traffic and affecting link availability to 99,855324%. Meanwhile, the result from satellite orbit calculation for sun outage period based on ITU-R S.1525 standard and based by satellite’s handbook. Keywords – Telkom 3S satellite, sun outage, C/N, Eb/No, BER, link availability, sun outage period.

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Shakila Hosseinzadeh Kondori, Mustafa Helvacı. "Satellite Temperature Modeling in Geostationary Orbit Using COMSOL". Tuijin Jishu/Journal of Propulsion Technology 44, nr 5 (29.11.2023): 127–39. http://dx.doi.org/10.52783/tjjpt.v44.i5.2440.

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In our world, communication satellites are becoming more and more significant. They are costly to create, launch, operate, and maintain, thus these costs are crucial. Due to the fact that electronic and satellite components can only operate within a limited temperature range, it is crucial to understand and manage the satellite's temperature in order to maximize efficiency both before and during the mission. This study considers GEO and comparable satellites with the goal of showing satellite temperature. We ignored the entire satellite's internal structure and focused only on the external heat generated by its surface (main body and solar panels). COMSOL is used in this project that is a simulation platform. Finally, the results have been displayed for the model at different times.

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Papiya, Sumaiya Janefar, Dr Bobby Barua i Mehnaz Hossain. "Prospects Challenges of Bangabandhu Satellite-2". International Journal of Advanced Networking and Applications 14, nr 02 (2022): 5342–52. http://dx.doi.org/10.35444/ijana.2022.14204.

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The development of the Bangabandhu Satellite-1 has changed the direction of Bangladesh's satellite communication research. Bangladesh's dream project was the Bangabandhu Satellite 1. This satellite's primary goal is to maintain effective internet and communication services in remote places. First of all, we must concentrate to the depth of satellite communication system and its process to reach any conclusion. Our main goal of the research is to recognize a feasibility review on Bangabandhu satellite-2. So, for the feasibility studies we reviewed the most promising technical parts of Bangabandhu satellite-1. Here, we only focused the certain parts of the satellite such as coding, modulation, battery, purpose of ground station and the benefits of the satellite communication system. Then we moved on the main parts of the Bangabandhu satellite-2. As, Bangabandhu satellite-1 was Geosynchronous equatorial orbit (GEO) communication satellite and Bangabandhu satellite-2 will be Low Earth Orbit (LEO) observation satellite (LEO) so, some of configurations between them might be changed. Furthermore, we largely focused on Facts, efficiency, performance and noticeable difference between two satellites.

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Williamson, M. "Satellites rock! [satellite radio]". IEE Review 49, nr 11 (1.12.2003): 34–37. http://dx.doi.org/10.1049/ir:20031104.

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Wei, Hui, Jiancheng Li, Shoujian Zhang i Xinyu Xu. "Cycle Slip Detection and Repair for Dual-Frequency LEO Satellite GPS Carrier Phase Observations with Orbit Dynamic Model Information". Remote Sensing 11, nr 11 (29.05.2019): 1273. http://dx.doi.org/10.3390/rs11111273.

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Cycle slip detection and repair are crucial for precise GPS-derived orbit determination of the low-Earth orbit (LEO) satellites. We present a new approach to detect and repair cycle slips for dual-frequency LEO satellite GPS observations. According to Newton’s equation of motion, the second-order time difference of the LEO satellite’s position (STP) is only related to the sampling interval and the satellite’s acceleration, which can be precisely obtained from the known orbit dynamic models. Then, several kinds of second-order time-difference geometry-free (STG) phase combinations, taking full advantage of the correlation between the satellite orbit variations and the dynamic model, with different level of ionospheric residuals, are proposed and adopted together to detect and fix cycle slips. The STG approach is tested with some LEO satellite GPS datasets. Results show that it is an effective cycle slip detection and repair method for LEO satellite GPS observations. This method also has some important features. Firstly, the STG combination is almost independent of the pseudorange. Secondly, this method is effective for LEO satellites, even in real-time application. Thirdly, this method is suitable for ground-based GPS receivers if we know the acceleration of the receivers.

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Wu, Shiyu, Dongkai Yang, Yunlong Zhu i Feng Wang. "Improved GNSS-Based Bistatic SAR Using Multi-Satellites Fusion: Analysis and Experimental Demonstration". Sensors 20, nr 24 (11.12.2020): 7119. http://dx.doi.org/10.3390/s20247119.

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The Global Navigation Satellite System (GNSS)-based Bistatic Synthetic Aperture Radar (SAR) is getting more and more attention in remote sensing for its all-weather and real-time global observation capability. Its low range resolution results from the narrow signal bandwidth limits in its development. The configuration difference caused by the illumination angle and movement direction of the different satellites makes it possible to improve resolution by multi-satellite fusion. However, this also introduces new problems with the resolution-enhancing efficiency and increased computation brought about by the fusion. In this paper, we aim at effectively improving the resolution of the multi-satellite fusion system. To this purpose, firstly, the Point Spread Function (PSF) of the multi-satellite fusion system is analyzed, and focusing on the relationship between the fusion resolution and the geometric configuration and the number of satellites. Numerical simulation results show that, compared with multi-satellite fusion, dual-satellite fusion is a combination with higher resolution enhancement efficiency. Secondly, a method for dual-satellite fusion imaging based on optimized satellite selection is proposed. With the greedy algorithm, the selection is divided into two steps: in the first step, according to geometry configuration, the single-satellite with the optimal 2-D resolution is selected as the reference satellite; in the second step, the angles between the azimuthal vector of the reference satellite and the azimuthal vector of the other satellites were calculated by the traversal method, the satellite corresponding to the intersection angle which is closest to 90° is selected as the auxiliary satellite. The fused image was obtained by non-coherent addition of the images generated by the reference satellite and the auxiliary satellite, respectively. Finally, the GPS L1 real orbit multi-target simulation and experimental validation were conducted, respectively. The simulation results show that the 2-D resolution of the images produced by our proposed method is globally optimal 15 times and suboptimal 8 times out of 24 data sets. The experimental results show that the 2-D resolution of our proposed method is optimal in the scene, and the area of the resolution unit is reduced by 70.1% compared to the single-satellite’s images. In the experiment, there are three navigation satellites for imaging, the time taken to the proposed method was 66.6% that of the traversal method. Simulations and experiments fully demonstrate the feasibility of the method.

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Yun, Seok-Teak, i Seung-Hyun Kong. "Forecasting Methods of Battery Charge and Discharge Current Profile for LEO Satellites". Electronics 10, nr 23 (1.12.2021): 2999. http://dx.doi.org/10.3390/electronics10232999.

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The orbital characteristics of low Earth orbit (LEO) satellite systems prevent continuous monitoring because ground access time is limited. For this reason, the development of simulators for predicting satellite states for the entire orbit is required. Power-related prediction is one of the important LEO satellite simulations because it is directly related to the lifespan and mission of the satellite. Accurate predictions of the charge and discharge current of a power system’s battery are essential for fault management design, mission design, and expansion of LEO satellites. However, it is difficult to accurately predict the battery power demand and charging of LEO satellites because they have nonlinear characteristics that depend on the satellite’s attitude, season, orbit, mission, and operating period. Therefore, this paper proposes a novel battery charge and discharge current prediction technique using the bidirectional long short-term memory (Bi-LSTM) model for the development of a LEO satellite power simulator. The prediction performance is demonstrated by applying the proposed technique to the KOM-SAT-3A and KOMSAT-5 satellites operating in real orbits. As a result, the prediction accuracy of the proposed Bi-LSTM shows root mean square error (RMSE) within 2.3 A, and the prediction error well outperforms the most recent the probability-based SARIMA model.

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Rozprawy doktorskie na temat "Satellite"

Anderson, Jason Lionel. "Autonomous Satellite Operations For CubeSat Satellites". DigitalCommons@CalPoly, 2010. https://digitalcommons.calpoly.edu/theses/256.

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In the world of educational satellites, student teams manually conduct operations daily, sending commands and collecting downlinked data. Educational satellites typically travel in a Low Earth Orbit allowing line of sight communication for approximately thirty minutes each day. This is manageable for student teams as the required manpower is minimal. The international Global Educational Network for Satellite Operations (GENSO), however, promises satellite contact upwards of sixteen hours per day by connecting earth stations all over the world through the Internet. This dramatic increase in satellite communication time is unreasonable for student teams to conduct manual operations and alternatives must be explored. This thesis first introduces a framework for developing different Artificial Intelligences to conduct autonomous satellite operations for CubeSat satellites. Three different implementations are then compared using Cal Poly's CP6 CubeSat and the University of Tokyo's XI-IV CubeSat to determine which method is most effective.

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Appleby, Graham M. "Satellite laser ranging and the ETALON Geodetic satellites". Thesis, Aston University, 1996. http://publications.aston.ac.uk/13270/.

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The technique of Satellite Laser Ranging is today a mature, important tool with applications in many area of geodynamics, geodesy and satellite dynamics. A global network of some 40 stations regularly obtains range observations with sub-cm precision to more than twelve orbiting spacecraft. At such levels of precision it is important to minimise potential sources of range bias in the observations, and part of the thesis is a study of subtle effects caused by the extended nature of the arrays of retro-reflectors on the satellites. We develop models that give a precise correction of the range measurements to the centres of mass of the geodetic satellites Lageos and Etalon, appropriate to a variety of different ranging systems, and use the Etalon values, which were not determined during pre-launch tests, in an extended orbital analysis. We have fitted continuous 2.5 year orbits to range observations of the Etalons from the global network of stations, and analysed the results by mapping the range residuals from these orbits into equivalent corrections to orbital elements over short time intervals. From these residuals we have detected and studied large un-modelled along-track accelerations associated with periods during which the satellites are undergoing eclipse by the Earth's shadow. We also find that the eccentricity residuals are significantly different for the two satellites, with Etalon-2 undergoing a year-long eccentricity anomaly similar in character to that experienced at intervals by Lageos-1. The nodal residuals show that the satellites define a very stable reference frame for Earth rotation determination, with very little drift-off during the 2.5 year period. We show that an analysis of more than about eight years of tracking data would be required to derive a significant value for 2. The reference frame defined by the station coordinates derived from the analyses shows very good agreement with that of ITRF93.

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Sharifi, Mohammad A. "Satellite gradiometry using a satellite pair". [S.l. : s.n.], 2004. http://www.bsz-bw.de/cgi-bin/xvms.cgi?SWB11406716.

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Score, Robert H. "An examination of XM satellite subscriber's perceptions of satellite radio compared to traditional AM/FM radio". Instructions for remote access. Click here to access this electronic resource. Access available to Kutztown University faculty, staff, and students only, 2002. http://www.kutztown.edu/library/services/remote_access.asp.

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Thesis (M.S.)--Kutztown University of Pennsylvania, 2002.
Source: Masters Abstracts International, Volume: 45-06, page: 2720. Typescript. Abstract precedes thesis as preliminary leaves 1-2. Includes bibliographical references (leaves 34-35).

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Morimoto, Todd A., Thomas E. Nowitzky i Steven A. Grippando. "OPERATING A LIGHTWEIGHT, EXPENSIVE LOW EARTH ORBITING SATELLITE". International Foundation for Telemetering, 1994. http://hdl.handle.net/10150/608842.

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International Telemetering Conference Proceedings / October 17-20, 1994 / Town & Country Hotel and Conference Center, San Diego, California
An increasing number of satellite users and manufacturers are looking to lightweight, inexpensive satellites as substitutes to traditional large, expensive satellites with multiple payloads. Neither the Department of Defense nor the commercial sector can bear the financial or reputational consequences associated with massive program failures. With the low cost and weight of these new satellites, users can achieve mission success without great risk. One example of this new class of inexpensive spacecraft is the RADCAL (RADar CALibration) satellite. Detachment 2, Space & Missile Systems Center at Sunnyvale, CA operates the satellite. RADCAL is a 200-pound polar orbiting satellite with an average altitude of 450 miles. It is primarily used by 77 worldwide radars to calibrate their systems to within five meter accuracy. Also flying on board RADCAL is a communication payload for remote field users with small radios. The RADCAL program has satisfied all mission requirements. However, with the limited size and cost come certain challenges, both in the satellite and on the ground. Pre-launch testing was not as comprehensive as with more expensive programs; anomalies have arisen that require extensive workarounds. Data management is not a straightforward task, and it is sometimes difficult and inexact to track satellite performance. These challenges are presented with their solutions in the following discussion; this paper addresses the functional, operational, and testing aspects associated with the RADCAL satellite.

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Zaheer, Muhammad. "Kinematic orbit determination of low Earth orbiting satellites, using satellite-to-satellite tracking data and comparison of results with different propagators". Thesis, KTH, Geodesi och geoinformatik, 2014. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-142627.

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The GPS data from Challenging Mini-satellite Payload (CHAMP) is used for its orbit determination for the epoch day of January 1st 2002. The orbit of CHAMP is computed from the GPS data and ionospheric effects are removed by frequency combination. Further, the orbits of CHAMP for the same epoch day are computed using the satellite tool kit (STK) employing simplified general perturbations (SGP4) and a high precision orbit propagator (HPOP). Results from both techniques (GPS computed orbit and STK computed orbit) are compared. Furthermore, orbits computed using GPS data are also compared with jet propulsion laboratory’s published CHAMP spacecraft orbit and we have found that root mean square difference in ECEF position X component is below 0.01km other than some spikes at poles. The standard deviation of the difference in ECEF position X coordinate is 11.7m. The accuracy of our computed satellite positions (using GPS data) is about 12 metres for other than polar areas. However there are some occasional spikes, especially at poles, having maximum errors (about 0.055 km).

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Xi, Xiaojin. "Analytical representation for ephemeris with short time-span : application to the longitude of Titan". Thesis, Paris Sciences et Lettres (ComUE), 2018. http://www.theses.fr/2018PSLEO015/document.

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Les éphémérides issues d'intégrations numériques qui peuvent être facilement téléchargées des sites de l'IMCCE ou du JPL, ont une très bonne précision pour les observations récentes. En même temps, un autre type d'éphémérides, celles analytiques comme TASS, décrivent en détail le système dynamique par une représentation en combinaison de fréquences propres. Notre but est d'associer ces deux types d'éphémérides pour l'utiliser dans les études de la rotation des satellites naturelles. Cela signifie qu'il faut reconstruire des éphémérides à long terme et de haute précision montrant les caractéristiques du système comme les fréquences propres à partir des intégrations numériques. La principale difficulté est d'éviter l'intervalle de temps limité des éphémérides numériques. Dans notre travail, nous partons de la représentation des éléments d'orbite de Titan sur 10 000 ans issues de TASS comme exemple et comme standard. Nous expérimentons comment obtenir les fréquences propres sur 1000 ans d'éphémérides de TASS, et comment obtenir la représentation analytique de la longitude moyenne de Titan sur cet intervalle limité. A cause de cette durée de 1000 ans, au lieu de l'analyse en fréquence, nous utilisons la méthode des moindres carrées, en particulier pour les termes à longue période. L'efficacité et l’exactitude de l'ensemble de la méthode sont vérifiées en comparant les représentations de la longitude moyenne de Titan issue de TASS par la méthode des moindres carrées et par la représentation standard de TASS sur 10 000 ans. Finalement et c'est ce qui importe, nous obtenons une représentation du mouvement de Titan pour les 1000 ans d'éphémérides du JPL. Il existe une différence de 60 km dans l'amplitude du terme principal entre les représentations du JPL et de TASS. Cette différence est considérée comme issue du système. L'intervalle de temps limité des éphémérides influence les fréquences propres et induit des erreurs dans les termes à longues périodes comme contenant la longitude du nœud de Titan. Pour toutes les autres composantes ou presque, leurs amplitudes et phases sont similaires à celles de TASS. L'erreur de représentation est inférieure à 100 km sur 1000 ans et la déviation standard est de 26 km environ
The numerical integration ephemeris, which are convenient to download from online service of IMCCE, or Horizons of JPL have very good precision based on recent observations. Meanwhile, another kind, the analytical ephemeris like TASS, describes in detail the dynamical system by combination representation of proper frequencies. We plan to make a connection between those two different type ephemeris, that it ’s benefited us to study the rotation of natural satellites with its high precision ephemeris, those instantaneous positions, velocity, and those system characteristics like proper frequencies. The main difficulty is to avoid the shortcoming of the limited interval of observation ephemeris.In our work, we take the combination representation of Titan with 10,000 years TASS ephemeris as an example and standard. Then, we experiment to obtain both the analytical representation of the mean longitude of Titan and the proper frequencies involved in it with 1,000 years TASS ephemeris by analysis frequency. Due to limited timespan, we extend the method with a least square method, especially for the long period terms. We verify the effectiveness and exactness of the whole method in rebuilt the combination representation.Finally and most important, we get the combination representation of Titan with 1000 years JPL ephemeris. Between the solution of JPL and the representation of TASS, there exists a 60 km difference in the amplitude of the major component, that is considered as a system difference. The limited interval ephemeris makes the influence of the proper frequency, which brings the error into the long period term like the one from the node of Titan. For nearly all other components, those amplitudes and phases are similar with the relative terms of TASS. The error of our representation is less than 100 kilometres over 1,000 years and the standard deviation is about 26 kilometres

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Wolf, Robert. "Satellite orbit and ephemeris determination using inter satellite links". [S.l.] : [s.n.], 2001. http://deposit.ddb.de/cgi-bin/dokserv?idn=961611820.

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Bezuidenhout, Quintus. "Satellite communications strategy selection for optimal LEO satellite communication". Thesis, Stellenbosch : Stellenbosch University, 2012. http://hdl.handle.net/10019.1/71930.

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Thesis (MScEng)--Stellenbosch University, 2012.
ENGLISH ABSTRACT: A low earth orbit satellite system can be useful in numerous communication applications where physical connections are not possible. Communication time available from any point on earth to the satellite is less than one hour per day. This one hour is fragmented into smaller time slots due to the satellite orbiting. This is not much time to transfer data and there is even less time available to transfer data when there are other external factors affecting the system. It is thus crucial to optimise the satellite communications link so that more data can be transferred per orbit. The goal of this thesis is to improve the performance of a low earth orbit satellite communication channel by varying certain parameters of the system, such as the protocol used, modulation scheme, packet size, transmission power etc. and then to observe how these parameters influence the system. The protocols that were chosen to be implemented are CSMA-CA, CSMA-CA with DSSS technology and Round-Robin Polling. A simulator for each protocol was designed with the Opnet platform, so that specific parameters could be changed and the results observed, in order to optimise the communications link between the satellite and ground stations. The results showed that there is no particular configuration of modulation scheme, packet size, transmission power etc. presenting the best overall solution for LEO satellite communications. It must be considered what the specific LEO satellite application would be used for and the characteristics required by that specific application. A suitable configuration must subsequently be chosen from the set of configurations available to satisfy most of the application requirements.
AFRIKAANSE OPSOMMING: ’n Satelliet met ’n lae wentelbaan kan gebruik word in verskeie kommunikasie toepassings waar fisiese verbindinge nie noodwendig moontlik is nie. Die kommunikasietyd van enige punt van aarde af na die satelliet, is minder as een uur per dag. Hierdie tyd word nog verder verklein omdat die satelliet besig is om, om die aarde te wentel. ’n Uur is glad nie baie tyd om data oor te dra nie en in realiteit is daar nog minder tyd beskikbaar as daar eksterne faktore op die sisteem inwerk. Dus is dit baie belangrik om die satelliet kommunikasiekanaal te optimiseer sodat soveel moontlik data as moontlik oorgedra kan word per omwenteling. Die doel van hierdie tesis is om die deurset van die kommunikasiekanaal van n lae wentelbaan satelliet te optimiseer, deur verskeie parameters te verander soos, protokol wat gebruik word, modulasie skema, pakkie grootte, transmissiekrag ens. en dan waar te neem hoe dit die sisteem beïnvloed. Die protokolle wat geïmplementeer is, is CSMA-CA, CSMA-CA met DSSS tegnologie en Round-Robin Polling. ’n Simulator vir elke protokol was ontwerp in die Opnet simulasie platform, sodat die spesifieke parameters verander kon word om die resultate te bestudeer met die doel om die kommunikasiekanaal tussen die satelliet en grond stasies optimaal te benut. Die resultate het bewys dat daar geen spesifieke konfigurasie van modulasie skema, pakkie grootte, transmissiekrag ens. is wat die algehele beste oplossing is nie. Die spesifieke applikasie waarvoor die lae wentelbaan satelliet gaan gebruik word moet geanaliseer word sowel as die spesifieke karakteristieke van daai applikasie. Daarvolgens moet n unieke konfigurasie opgestel word wat meeste van die applikasie se behoeftes bevredig.

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Sharifi, Mohammad A. "Satellite to satellite tracking in the space-wise approach". [S.l. : s.n.], 2006. http://nbn-resolving.de/urn:nbn:de:bsz:93-opus-28337.

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Książki na temat "Satellite"

Stefan, Kalmár, Museum für Gegenwartskunst Zürich i Consortium (Art center : Dijon, France), red. Satellite. Zürich: Museum für Gegenwartskunst, 1998.

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H, Vonder Haar Thomas, red. Satellite meteorology: An introduction. San Diego: Academic Press, 1995.

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Committe, International Radio Consultative. Handbook: Satellite communications : fixed-satellite service. Geneva: International Telecommunication Union, 1988.

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International Radio Consultative Committee., red. Handbook, satellite communications: Fixed-satellite service. Geneva: International Telecommunication Union, 1988.

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Satellite geodesy. Wyd. 2. Berlin: Walter de Gruyter, 2003.

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Center, Goddard Space Flight, i United States. National Environmental Satellite, Data, and Information Service., red. Mission overview, GOES: Geostationary Operational Environmental Satellite. [Greenbelt, Md.]: NASA Goddard Space Flight Center, 1997.

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P, Rainger, red. Satellite broadcasting. Chichester [West Sussex]: Wiley, 1985.

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Center, Lewis Research, red. Communications satellite: NASA's advanced communications technology satellite. [Cleveland, Ohio]: NASA Lewis Research Center, 1997.

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Union, International Telecommunication. Mobile satellite services and radiodetermination satellite service. Geneva: International Telecommunication Union, 1998.

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Center, NASA Glenn Research, red. Communications satellite: NASA's advanced communications technology satellite. Cleveland, Ohio: NASA Glenn Research Center, 1999.

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Części książek na temat "Satellite"

Pelton, Joseph N. "Satellite Orbits for Communications Satellites". W Handbook of Satellite Applications, 93–114. New York, NY: Springer New York, 2013. http://dx.doi.org/10.1007/978-1-4419-7671-0_5.

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Pelton, Joseph N. "Satellite Orbits for Communications Satellites". W Handbook of Satellite Applications, 99–120. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-23386-4_5.

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Pelton, Joseph N. "Satellite Orbits for Communications Satellites". W Handbook of Satellite Applications, 1–22. New York, NY: Springer New York, 2015. http://dx.doi.org/10.1007/978-1-4614-6423-5_5-3.

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Inglis, Andrew F. "Satellite Program Distribution Geosynchronous Satellites". W Behind the Tube, 392–438. London: Routledge, 2023. http://dx.doi.org/10.4324/9781003454601-8.

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Marjoribanks, Roger. "satellite images Satellite Imagery". W Geological Methods in Mineral Exploration and Mining, 137–42. Berlin, Heidelberg: Springer Berlin Heidelberg, 2010. http://dx.doi.org/10.1007/978-3-540-74375-0_8.

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Weik, Martin H. "satellite". W Computer Science and Communications Dictionary, 1513. Boston, MA: Springer US, 2000. http://dx.doi.org/10.1007/1-4020-0613-6_16581.

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Maitra, Amit, i Joseph N. Pelton. "Mobile Satellite Communications and Small Satellites". W Handbook of Small Satellites, 1–16. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-20707-6_38-1.

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Maitra, Amit, i Joseph N. Pelton. "Mobile Satellite Communications and Small Satellites". W Handbook of Small Satellites, 721–36. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-36308-6_38.

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Ilk, Karl Heinz. "Satellite-to-Satellite-Tracking (SST)". W Satellitengeodäsie, 215–31. Berlin, Heidelberg: Springer Berlin Heidelberg, 2021. http://dx.doi.org/10.1007/978-3-662-62369-5_12.

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Shi, Chuang, i Na Wei. "Satellite Navigation for Digital Earth". W Manual of Digital Earth, 125–60. Singapore: Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-32-9915-3_4.

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Abstract Global navigation satellite systems (GNSSs) have been widely used in navigation, positioning, and timing. China’s BeiDou Navigation Satellite System (BDS) would reach full operational capability with 24 Medium Earth Orbit (MEO), 3 Geosynchronous Equatorial Orbit (GEO) and 3 Inclined Geosynchronous Satellite Orbit (IGSO) satellites by 2020 and would be an important technology for the construction of Digital Earth. This chapter overviews the system structure, signals and service performance of BDS, Global Positioning System (GPS), Navigatsionnaya Sputnikovaya Sistema (GLONASS) and Galileo Navigation Satellite System (Galileo) system. Using a single GNSS, positions with an error of ~ 10 m can be obtained. To enhance the positioning accuracy, various differential techniques have been developed, and GNSS augmentation systems have been established. The typical augmentation systems, e.g., the Wide Area Augmentation System (WAAS), the European Geostationary Navigation Overlay Service (EGNOS), the global differential GPS (GDGPS) system, are introduced in detail. The applications of GNSS technology and augmentation systems for space-time geodetic datum, high-precision positioning and location-based services (LBS) are summarized, providing a reference for GNSS engineers and users.

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Streszczenia konferencji na temat "Satellite"

Specht, Cezary, i Paweł Dąbrowski. "Runaway PRN11 GPS satellite". W Environmental Engineering. VGTU Technika, 2017. http://dx.doi.org/10.3846/enviro.2017.244.

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The paper discusses the position of the orbit of PRN11 GPS satellite. Visual analysis of the current GPS constellation showed considerable deviation of PRN11 GPS satellite orbital parameters relative to other orbital plane D satellites. Short comparison of available GPS almanac format was included. Two almanacs per year since the launch of the PRN11 satellites in 1999 were obtained. Parameters of right ascension of ascending node and rate of right ascension of ascending node were taken into investigation. The results confirmed the fact of constant and progressive separation of the orbit from home orbital plane D since the very beginning of the satellite mission. The simulation of long-term persistence of the current trend in the postion of the PRN11 ascending node was presented.

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Yun, Sang-Hyuk, Hyo-Sung Ahn, Sun-Ju Park, Ok-Chul Jung i Dae-Won Chung. "Ground Antenna Scheduling Algorithm for Multi-Satellite Tracking". W ASME 2011 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2011. http://dx.doi.org/10.1115/detc2011-48042.

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In this paper, we address the optimal ground antenna scheduling problem for multiple satellites when multiple satellites have visibility conflicts at a ground station. Visibility conflict occurs when multiple satellites have either overlapping visibilities at a ground station or difference with time of loss of signal (LOS) of a satellite and time of acquisition of signal (AOS) of another satellite is less than reconfiguration time of ground station. Each satellite has a priority value that is a weight function with various factors. Multi-antenna scheduling (MAS) algorithm 1 and Multi-antenna scheduling (MAS) algorithm 2 are proposed to find the optimal schedule of multi-antenna at a ground station using pre-assigned priority values of satellites. We use the depth first search (DFS) method to search the optimal schedule in MAS algorithm 1 and MAS algorithm 2. Through the simulations, we confirm the efficiency of these algorithms by comparing with greedy algorithm.

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McMullen, Matthew G., Tamara Alexander i Adam Huang. "Small Satellite Formations via Higher Velocity Deployment". W ASME 2010 International Mechanical Engineering Congress and Exposition. ASMEDC, 2010. http://dx.doi.org/10.1115/imece2010-40010.

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Small satellites can be constructed at a fraction of the cost of a full-size satellite. One full-size satellite can be replaced with a multitude of small satellites, which offers a benefit in covering more area at the same time, achievable through formations. However, the shortcoming to the smaller size is usually a lack of thrusting capabilities. Furthermore, current designs for small satellite deployment mechanisms are only capable of low deployment velocities (on the order of meters per second). Prior research in using a pneumatic launcher shows that it is possible to achieve higher deployment velocities (75–125 m/s). This is beneficial in that it opens the possibility for limited but useful orbit placement and small satellite formations. Achieving a formation is done by reformulating the classical orbital mechanics equations to find the required deployment velocity vectors that yield the desired formation.

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Senes, Maxime, Kristen Lagadec, Baptiste Brault i Bertrand Raffier. "A Passive Device for Postmortem Detumbling/Antitumbling of LEO Satellites, to Facilitate Active Removal". W ESA 12th International Conference on Guidance Navigation and Control and 9th International Conference on Astrodynamics Tools and Techniques. ESA, 2023. http://dx.doi.org/10.5270/esa-gnc-icatt-2023-093.

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To limit the risk of cascading collisions, we will need active debris removal missions to retrieve satellites that die before they can be deorbited. It is well understood that sudden fatal failures can cause a dead satellite to tumble uncontrollably, but it also happens that even properly decommissioned satellites are not immune to spontaneous self-tumbling due to momentum buildup from solar radiation pressure torque, making removal much more challenging. The availability of a detumbling/antitumbling device ensuring passive stabilization of dead satellites could greatly reduce the risk and cost of debris removal missions. We present a totally passive magnetic damping device attached to a satellite's structure, where a rotor fitted with magnets is free to rotate inside a metallic housing. Even if the satellite is tumbling, the rotor stays aligned with the geomagnetic field: the differential angular rate between the rotor and the satellite will create eddy currents in the housing and thus dissipate rotational energy, eventually stopping the tumbling motion. Detailed sizing and simulation activities have demonstrated that one such small (h < Phi < 5cm diameter) and lightweight (m < 100 grams) device was capable of detumbling a medium-to-large satellite (5000 kg.m² of inertia) with a detumbling time constant of a few weeks. We present the current development status, including the results of vibration tests with two representative prototypes built around two competing technologies for the rotor bearing. These steps pave the way for the final development stages of a universally available detumbling function that can be a game-changer for reducing the future burden of taking care of defunct LEO satellites.

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Paul, Johns, Abdul Salam PM, Rajeev P, Santhosh J. Nalluveettil i Jothiramalingam A. "Development of INLS 3U Uni-Pod Nano Satellite (CubeSat) Dispenser System for 3U Class Satellites". W AeroCON 2024. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2024. http://dx.doi.org/10.4271/2024-26-0458.

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<div class="section abstract"><div class="htmlview paragraph">With the present state of the art technology, size and mass of the satellites have come down. This necessitated the need for a low shock separation system that does not have mass attached to the separated satellite. Development of Nano satellites with mass of the order of 1 to 24 kg has become popular among scientific/ academic institutions for carrying out scientific experiments. INLS 3U Uni-Pod System (Nano satellite dispenser system) is a satellite dispensing system designed by ISRO for accommodating four 3U class Nano satellites in a single structure where each satellite is deployed independently by separate actuation commands. INLS stands for ISRO's Nano satellite Launch System. The INLS 3U Uni-Pod separation system successfully flown in ISRO’s Launch Vehicle mission for deployment of three satellites from abroad. CubeSat separation system consists of a structure housing the satellite, Holding and release mechanism (HDRM), rattling arresting mechanism, satellite ejection mechanism and movement arresting/ locking mechanism. The system was designed and developed for accommodating four satellites with a maximum mass of 6.0 kg, meeting the CubeSat Design Specification (CDS). Wire fusing system is used as HDRM. Helical compression spring with pusher plate is used for ejecting the satellite. Mechanism with double torsion spring is used for rattling arresting. The system was tested in ground conditions and in thermo-vacuum environment (-15°C & +60°C) nearly 40 times and found meeting the design specifications. The actuation time, separation time, electrical specifications, separation velocity and rates are designed at par with the internationally available commercial systems. The satellite ejection time is within one second from command. Confirmation of satellite separation is through micro switches and reed switches. The system can be mounted in two configurations, viz rail mounting and back mounting.</div></div>

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Adam, Steve, i Mike Farrell. "High Resolution Satellite Imagery: From Spies to Pipeline Management". W 2000 3rd International Pipeline Conference. American Society of Mechanical Engineers, 2000. http://dx.doi.org/10.1115/ipc2000-152.

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In the past, high resolution satellite imagery was the domain of national security organizations. However, this has recently changed with the launch of Space Imaging’s IKONOS satellite. Launched on September 24, 1999 it is the world’s first commercial high resolution satellite, collecting data at 1-meter black/white and 4-meter multi-spectral. 2000 has the scheduled launch of at least two more commercial high resolution satellites. If these satellites are successfully launched, a buyer will be able to acquire imagery every day of the year (barring cloud cover). As an added convenience, an image user no longer has to buy a massive swath of imagery. For example, IKONOS scenes as narrow as 5km (3 miles) can be purchased. This development has opened the door for corridor applications and has been thoroughly and successfully implemented by TransCanada Pipelines in mapping over 1500km of their mainline.

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Meng, Jingxiong, Yan Chen i Junfeng Zhao. "Simulator Development for Vehicle Localization Using Low Earth Orbit Satellites". W WCX SAE World Congress Experience. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2024. http://dx.doi.org/10.4271/2024-01-2846.

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<div class="section abstract"><div class="htmlview paragraph">This paper investigates the utilization of Low Earth Orbit (LEO) satellites for vehicle localization and conducts a comparative analysis with traditional Global Navigation Satellite Systems (GNSS)-based methods. With the rise of LEO satellite constellations, such as Starlink, LEO-based vehicle localization may offer solutions to GNSS-related challenges. With a large number of satellites and short communication distance, the LEO-based method has great potential to improve accuracy, reduce warm-up time, and provide a robust localization solution for vehicle applications. In this paper, a dedicated LEO satellite simulator is presented, adaptable to various LEO constellations, making it relevant for evolving technologies beyond older LEO systems like Orbcomm or Iridium. The simulator includes satellite trajectory generation, observable satellite identification, and vehicle localization. The LEO simulator was also seamlessly integrated with the Carla simulator for real-time online vehicle localization assessments. Comprehensive tests were conducted with the simulation tools to evaluate LEO satellite-based vehicle localization performance across different satellite counts. Results indicate the potential of LEO satellites for precise and reliable vehicle localization, even in challenging environments. Additionally, the discussion revolves around integrating diverse GNSS-based methods into the LEO simulator, offering a versatile platform for hybrid satellite-based localization research. This study underscores the promise of LEO satellites in enhancing vehicle localization accuracy and stability, contributing to autonomous driving technology and safety advancements.</div></div>

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Kumar Maurya, Ashutosh, Uma Yadav, Mukesh Kumar i Javalkar Dinesh Kumar. "Developing and deploying a satellite communication ground station: Design and Implementation". W International Conference on Cutting-Edge Developments in Engineering Technology and Science. ICCDETS, 2024. http://dx.doi.org/10.62919/gsaa7128.

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Amidst the proliferation of satellites encircling the Earth, the establishment of an extensive ground station network assumes paramount importance for effective reception of satellite-transmitted data. This paper delves into the intricacies surrounding the deployment of a ground station tailored for Low Earth Orbit (LEO) satellites, situated in Suceava city. It outlines a straightforward and economical ground station solution while showcasing a practical demonstration of satellite data reception. Given the urban setting of the ground station and the utilization of omnidirectional antennas, the paper also scrutinizes the station's radio horizon and radio compatibility with the surroundings.

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Mihalčinová, Nikola, i Miriam Jarošová. "Meteorological satellite as an important source of meteorological information for aviation". W Práce a štúdie. University of Žilina, 2021. http://dx.doi.org/10.26552/pas.z.2021.1.15.

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This paper is focused on the use of information provided from meteorological satellites in air transport, its development and current status. The work defines general knowledge in the field of meteorology such as the history of meteorological satellites, the division of orbits and current meteorological satellites in orbits. The work also includes the characteristics of measured quantities and monitoring methods. The practical contribution of this work is the analysis of satellite images in Europe. Finally, the work deals with the future use of meteorological satellites and the development of new satellites.

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Ronalds, Beverley F., i Elvin I. H. Heng. "Subsea and Platform Options for Satellite Field Developments". W ASME 2003 22nd International Conference on Offshore Mechanics and Arctic Engineering. ASMEDC, 2003. http://dx.doi.org/10.1115/omae2003-37042.

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As offshore infrastructure matures, satellite field developments are becoming increasingly common. The essential components of a satellite production facility are the well(s), by which reservoir fluids flow to the seabed or surface, and a means of export of the produced fluids. In addition, various auxiliary facilities may be required. These may include: drilling and workover equipment; processing, control and metering systems; and power and utilities to support these operations and ensure their safe performance. These supporting functions may be shared between the host, the satellite and mobile vessels in many ways. Various satellite production arrangements are compared in detail in the paper, utilising a database of North Sea subsea and surface satellites. With satellite developments being employed in ever-deeper waters and over longer step-out distances, prudent selection between subsea or surface options is vital to achieving favourable field economics.

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Raporty organizacyjne na temat "Satellite"

Schug, Klaus. Satellite Local Area Network Inter-Satellite Link. Fort Belvoir, VA: Defense Technical Information Center, czerwiec 2000. http://dx.doi.org/10.21236/ada387200.

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COLORADO UNIV AT BOULDER. Satellite Oceanography. Fort Belvoir, VA: Defense Technical Information Center, styczeń 1994. http://dx.doi.org/10.21236/ada277286.

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España Fontán, Paula, i Maria Angeles Gomez Flechoso. Effects of the orbit orientation on the evolution of dwarf satellite galaxies. Fundación Avanza, maj 2023. http://dx.doi.org/10.60096/fundacionavanza/2492022.

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Cosmological models propose a hierarchical scenario for galaxy evolution, where dwarf galaxies are accreted in the halo of larger ones. We study the effect of the satellite’s orbital orientation on the planar alignment of satellite galaxies.

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Hansen, Elaine, Dave Beckwith, Brian Egaas, Steve Levin-Stankevich i Jennifer Michels. Three Corner Satellite. Fort Belvoir, VA: Defense Technical Information Center, wrzesień 2002. http://dx.doi.org/10.21236/ada410043.

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Horan, Stephen. 3 Corner Satellite. Fort Belvoir, VA: Defense Technical Information Center, listopad 2002. http://dx.doi.org/10.21236/ada410185.

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Danielson, D. A., C. P. Sagovac, B. Neta i L. W. Early. Semianalytic Satellite Theory. Fort Belvoir, VA: Defense Technical Information Center, styczeń 1995. http://dx.doi.org/10.21236/ada531136.

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Schultz, J. F., S. J. Czuchlewski i C. R. Quick. Satellite-based laser windsounder. Office of Scientific and Technical Information (OSTI), sierpień 1997. http://dx.doi.org/10.2172/549682.

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Liaw, D. C., i E. H. Abed. Tethered Satellite System Stability. Fort Belvoir, VA: Defense Technical Information Center, styczeń 1989. http://dx.doi.org/10.21236/ada454743.

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Counselman, C. C. Millimeter-Accuracy Satellite Navigation. Fort Belvoir, VA: Defense Technical Information Center, kwiecień 1991. http://dx.doi.org/10.21236/ada237736.

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Bernier, M. Un satellite très prometteur. Natural Resources Canada/CMSS/Information Management, 1985. http://dx.doi.org/10.4095/217302.

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