Готові списки джерел за темами / CubeSat Constellation

Добірка наукової літератури з теми "CubeSat Constellation"

Автор: Grafiati

Опубліковано: 14 березня 2023

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Статті в журналах з теми "CubeSat Constellation"

Meftah, Mustapha, Fabrice Boust, Philippe Keckhut, Alain Sarkissian, Thomas Boutéraon, Slimane Bekki, Luc Damé, et al. "INSPIRE-SAT 7, a Second CubeSat to Measure the Earth’s Energy Budget and to Probe the Ionosphere." Remote Sensing 14, no. 1 (January 1, 2022): 186. http://dx.doi.org/10.3390/rs14010186.

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INSPIRE-SAT 7 is a French 2-Unit CubeSat (11.5 × 11.5 × 22.7 cm) primarily designed for Earth and Sun observation. INSPIRE-SAT 7 is one of the missions of the International Satellite Program in Research and Education (INSPIRE). Twice the size of a 4 × 4 Rubik’s Cube and weighing about 3 kg, INSPIRE-SAT 7 will be deployed in Low Earth Orbit (LEO) in 2023 to join its sister satellite, UVSQ-SAT. INSPIRE-SAT 7 represents one of the in-orbit demonstrators needed to test how two Earth observation CubeSats in orbit can be utilized to set up a satellite constellation. This new scientific and technological pathfinder CubeSat mission (INSPIRE-SAT 7) uses a multitude of miniaturized sensors on all sides of the CubeSat to measure the Earth’s energy budget components at the top-of-the-atmosphere for climate change studies. INSPIRE-SAT 7 contains also a High-Frequency (HF) payload that will receive HF signals from a ground-based HF transmitter to probe the ionosphere for space weather studies. Finally, this CubeSat is equipped with several technological demonstrators (total solar irradiance sensors, UV sensors to measure solar spectral irradiance, a new Light Fidelity (Li-Fi) wireless communication system, a new versatile telecommunication system suitable for CubeSat). After introducing the objectives of the INSPIRE-SAT 7 mission, we present the satellite definition and the mission concept of operations. We also briefly show the observations made by the UVSQ-SAT CubeSat, and assess how two CubeSats in orbit could improve the information content of their Earth’s energy budget measurements. We conclude by reporting on the potential of future missions enabled by CubeSat constellations.

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TURCU, Danuț, and Gheorghe Adrian STAN. "PURPOSE OF USING CUBESAT SATELLITE TECHNOLOGIES IN THE MILITARY DOMAIN." STRATEGIES XXI - Security and Defense Faculty 17, no. 1 (November 1, 2021): 272–78. http://dx.doi.org/10.53477/2668-2001-21-34.

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The increasing usage of space capabilities in the military domain highly requires the development of Nanosatellite polar constellations. In this paper we will analyze the main features of small satellites constellations that could be useful in military purposes. The Nanosatellite or CubeSat technology aim at miniaturization, high modularity and software defined payload, allowing the functionality of entire military space applications and services portfolio, at major low financial costs, translating its scalability and flexibility into a capability. In addition, the efficient combination between low latency and high throughput bandwidth, integrated in federated mega-constellation architectures, transforms CubeSat satellite networks into resilient platforms for development of advanced technologies (5G, IoT), according with the military requirements standards.

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Chadalavada, Pardhasai, and Atri Dutta. "Regional CubeSat Constellation Design to Monitor Hurricanes." IEEE Transactions on Geoscience and Remote Sensing 60 (2022): 1–8. http://dx.doi.org/10.1109/tgrs.2021.3124473.

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Nag, Sreeja, Joseph L. Rios, David Gerhardt, and Camvu Pham. "CubeSat constellation design for air traffic monitoring." Acta Astronautica 128 (November 2016): 180–93. http://dx.doi.org/10.1016/j.actaastro.2016.07.010.

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Kääb, Andreas, Bas Altena, and Joseph Mascaro. "River-ice and water velocities using the Planet optical cubesat constellation." Hydrology and Earth System Sciences 23, no. 10 (October 22, 2019): 4233–47. http://dx.doi.org/10.5194/hess-23-4233-2019.

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Abstract. The PlanetScope constellation consists of ∼150 optical cubesats that are evenly distributed like strings of pearls on two orbital planes, scanning the Earth's land surface once per day with an approximate spatial image resolution of 3 m. Subsequent cubesats on each of the orbital planes image the Earth surface with a nominal time lag of approximately 90 s between them, which produces near-simultaneous image pairs over the across-track overlaps of the cubesat swaths. We exploit this short time lag between subsequent Planet cubesat images to track river ice floes on northern rivers as indicators of water surface velocities. The method is demonstrated for a 60 km long reach of the Amur River in Siberia, and a 200 km long reach of the Yukon River in Alaska. The accuracy of the estimated horizontal surface velocities is of the order of ±0.01 m s−1. The application of our approach is complicated by cloud cover and low sun angles at high latitudes during the periods where rivers typically carry ice floes, and by the fact that the near-simultaneous swath overlaps, by design, do not cover the complete Earth surface. Still, the approach enables direct remote sensing of river surface velocities for numerous cold-region rivers at a number of locations and occasionally several times per year – which is much more frequent and over much larger areas than currently feasible. We find that freeze-up conditions seem to offer ice floes that are generally more suitable for tracking, and over longer time periods, compared with typical ice break-up conditions. The coverage of river velocities obtained could be particularly useful in combination with satellite measurements of river area, and river surface height and slope.

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Gomez Jenkins, Marco, David Krejci, and Paulo Lozano. "CubeSat constellation management using Ionic Liquid Electrospray Propulsion." Acta Astronautica 151 (October 2018): 243–52. http://dx.doi.org/10.1016/j.actaastro.2018.06.007.

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Kidd, Chris, Toshi Matsui, William Blackwell, Scott Braun, Robert Leslie, and Zach Griffith. "Precipitation Estimation from the NASA TROPICS Mission: Initial Retrievals and Validation." Remote Sensing 14, no. 13 (June 22, 2022): 2992. http://dx.doi.org/10.3390/rs14132992.

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This paper describes the initial results of precipitation estimates from the Time-Resolved Observations of Precipitation structure and storm Intensity with a Constellation of Smallsats (TROPICS) Millimeter-wave Sounder (TMS) using the Precipitation Retrieval and Profiling Scheme (PRPS). The TROPICS mission consists of a Pathfinder CubeSat and a constellation of six CubeSats, providing a low-cost solution to the frequent sampling of precipitation systems across the Tropics. The TMS instrument is a 12-channel cross-track scanning radiometer operating at frequencies of 91.655 to 204.8 GHz, providing similar resolutions to current passive microwave sounding instruments. These retrievals showcase the potential of the TMS instrument for precipitation retrievals. The PRPS has been modified for use with the TMS using a database based upon observations from current sounding sensors. The results shown here represent the initial postlaunch version of the retrieval scheme, as analyzed for the Pathfinder CubeSat launched on 30 June 2021. In terms of monthly precipitation estimates, the results fall within the mission specifications and are similar in performance to retrievals from other sounding instruments. At the instantaneous scale, the results are very promising.

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Tsitas, S. R., and J. Kingston. "6U CubeSat commercial applications." Aeronautical Journal 116, no. 1176 (February 2012): 189–98. http://dx.doi.org/10.1017/s0001924000006692.

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AbstractRecent work by Tsitas and Kingston(1)has demonstrated that an 8kg 6U CubeSat can be designed to perform Earth observation missions equivalent to those of 50-150kg microsatellites. Their design is reviewed and its commercial potential is compared to the 156kg RapidEye spacecraft. Three other commercial applications of this design are described. These are: a standard spacecraft for space scientists and astronomers; the spacecraft component of anNnation 5 spectral band disaster monitoring constellation and a night imaging satellite. Nanosatellites should now be considered for commercial missions previously thought to require microsatellites.

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Mazzarella, Luca, Christopher Lowe, David Lowndes, Siddarth Koduru Joshi, Steve Greenland, Doug McNeil, Cassandra Mercury, Malcolm Macdonald, John Rarity, and Daniel Kuan Li Oi. "QUARC: Quantum Research Cubesat—A Constellation for Quantum Communication." Cryptography 4, no. 1 (February 27, 2020): 7. http://dx.doi.org/10.3390/cryptography4010007.

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Quantum key distribution (QKD) offers future proof security based on fundamental laws of physics. Long-distance QKD spanning regions such as the United Kingdom (UK) may employ a constellation of satellites. Small satellites, CubeSats in particular, in low Earth orbit are a relatively low-cost alternative to traditional, large platforms. They allow the deployment of a large number of spacecrafts, ensuring greater coverage and mitigating some of the risk associated with availability due to cloud cover. We present our mission analysis showing how a constellation comprising 15 low-cost 6U CubeSats can be used to form a secure communication backbone for ground-based and metropolitan networks across the UK. We have estimated the monthly key rates at 43 sites across the UK, incorporating local meteorological data, atmospheric channel modelling and orbital parameters. We have optimized the constellation topology for rapid revisit and thus low-latency key distribution.

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Zanette, Luca, Leonardo Reyneri, and Giuseppe Bruni. "Swarm system for CubeSats." Aircraft Engineering and Aerospace Technology 90, no. 2 (March 5, 2018): 379–89. http://dx.doi.org/10.1108/aeat-07-2016-0119.

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Purpose This paper aims to present an innovative system able to establish an inter-satellite communication crosslink and to determine the mutual physical positioning for CubeSats belonging to a swarm. Design/methodology/approach Through a system involving a smart antenna array managed by a beamforming control strategy, every CubeSat of the swarm can measure the direction of arrival (DOA) and the distance (range) to estimate the physical position of the received signal. Moreover, during the transmission phase, the smart antenna shapes the beam to establish a reliable and directive communication link with the other spacecraft and/or with the ground station. Furthermore, the authors introduce a deployable structure fully developed at Politecnico di Torino that is able to increase the external surface of CubeSats: this surface allows to gain the interspace between elements of the smart antenna. Findings As a consequence, the communication crosslink, the directivity and the detection performance of the DOA system in terms of directivity and accuracy are improved. Practical implications Moreover, the deployable structure offers a greater usable surface, so a larger number of solar panels can be used. This guarantees up to 25 W of average power supply for the on-board systems and for transmission on a one-unit (1U) CubeSat (10 × 10 × 10 cm). Originality/value This paper describes the physical implementation of the antenna array system on a 1U CubeSat by using the deployable structure developed. Depending on actuators and ability that every CubeSat disposes, various interaction levels between elements can be achieved, thus making the CubeSat constellation an efficient and valid solution for space missions.

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Більше джерел

Дисертації з теми "CubeSat Constellation"

Smalarz, Bradley Ryan. "CubeSat Constellation Analysis for Data Relaying." DigitalCommons@CalPoly, 2011. https://digitalcommons.calpoly.edu/theses/650.

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Current CubeSat communication technology limits the amount of time, and number of accesses with ground stations. It has been proposed to use a constellation of CubeSats to improve relay performance and increase the number of accesses between a CubeSat and ground stations. By using the spatial and temporal analysis features of STK, coupled with the STK/Matlab interface a robust tool was created to analyze the performance of CubeSat constellations based on a store-and-forward communications model which is not currently supported by the STK Engine. Utilizing the Connect messaging format through a socket connection on the local machine, a Matlab graphical user interface, called SATCAT, was constructed in order to provide a user with the ability to control many aspects of the STK Engine externally. A function was created to use three Time Ordered Access (TOA) reports from STK to determine how long it would take for data to be relayed from a target to a ground station through a constellation of CubeSats. Three sample scenarios were created to demonstrate the use and performance analysis capabilities of SATCAT. The performance of a single CubeSat was analyzed and compared to the performance of a three CubeSat constellation and a thirty-seven CubeSat constellation. It was shown that a constellation of three CubeSats decreased the average relay time from 328 minutes to 149 minutes and a constellation of thirty-seven CubeSats further reduced the average relay time to only 3 minutes. While decreasing the average relay time, the constellation of three CubeSats also increased the number of accesses over a twenty-four hour period from 6 to 36, and the constellation of thirty-seven CubeSats allowed for 564 accesses.

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White, Michael T. "CubeSat Constellation Design for Intersatellite Linking." Scholar Commons, 2019. https://scholarcommons.usf.edu/etd/7987.

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This thesis investigates the concept of controlling a CubeSat constellation in low-Earth orbit. Low-Earth orbits are considered because the torque used for satellite control is supplied with magnetorquers, and the closer the satellite is to Earth’s magnetic field the more control gain can be supplied. Also, this is the expected orbit altitude of future CubeSat constellations to enable communications. Controlling a CubeSat relies on attitude determination. This means being able to estimate its attitude relative to a given reference frame. To determine the attitude, we propose to use a star tracker and a Kalman filter. A star tracker scans the stars in the satellite’s view, correlates the object to a database, to return an attitude measurement. The measurement is then processed using the Kalman filter. The attitude estimate is then used as the reference input for the controller. Once the attitude of the satellites is determined, a controller can be implemented; assuming the system is controllable and observable. These parameters are verified by adding enough actuators and sensors, respectively. The novelty of this thesis is constructing a controller that will take three satellites and their attitude estimates and arrange them broadside to a target. For simplicity, the arrangement will be a linear formation, and the target and satellite constellation will all be near-field communication. The goal is to place the satellite constellation in an attitude for an intersatellite link to be established. This is a proposed solution to better budget power and computational constraints associated with CubeSats. In addition to adjusting the topology of the system, a communication method must be considered for the data to be distributed across the system requiring an antenna design to implement the communication method. Both issues are discussed in the thesis; however, the focus is the controller design for attitude control. The control approach is a multi-input multi-output (MIMO) sliding fuzzy controller. The focus of the analysis is attitude control for communication while maintaining the constellation in a linear formation. The results shown this controller to be a valid proof of concept.

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Lee, Zachary Thomas. "CubeSat constellation implementation and management using differential drag." Thesis, Massachusetts Institute of Technology, 2017. http://hdl.handle.net/1721.1/112471.

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Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2017.
Cataloged from PDF version of thesis.
Includes bibliographical references (pages 107-117).
Space missions often require the use of several satellites working in coordination with each other. Industry examples include Planet, which is working to develop a constellation of over 100 Cube Satellites (CubeSats) to obtain global imagery data daily, and Astro Digital, which seeks to implement a constellation of multispectral imaging satellites to image the entire Earth every three to four days [1, 2]. CubeSat constellations are also being considered for applications such as secure laser communication relays and for weather sensing with short revisit times [3, 4]. Such missions require several CubeSats with regular spacing within an orbital plane to achieve their objectives. However, an appropriately arranged constellation can be particularly difficult to implement for CubeSats. Cold gas propulsion systems with the ability to provide tens of meters per second of delta-V (for a 3U CubeSat) exist and can be used for constellation management on timescales of weeks [5, 6, 7, 8, 9]. Monopropellant systems also currently exist for CubeSats, but, like cold gas systems, they can require significant power, mass, volume, and thermal management resources, and they also carry more risk [9, 10]. Launch services providers often limit acceptance of pressurized vessels, which can limit launch opportunities for CubeSats with cold gas or monopropellant propulsion systems. Although electric propulsion systems can provide up to 100 m/s delta-V for a 3U CubeSat, they also have mass, volume, cost, and power impacts, and they typically require timescales on the order of weeks to months to cause significant changes [6, 11, 9]. In low Earth orbit, there is sufficient drag to perturb satellite orbits. Though it varies widely based on conditions, at 500 kilometer (km) altitude, the acceleration due to drag on a 3U CubeSat can be around 15 [mu]m/s² per unit area [12]. Over time, this is enough acceleration to change a satellite's orbit. By controlling the attitude of a satellite, the profile area can be changed. By manipulating the profile area, the drag force can be changed, and satellites can be moved relative to each other within an orbital plane. Using differential drag at 550 km altitude, a 3U CubeSat can.move its true anomaly 180 degrees relative to another in the same orbital plane in about 100 days. Previous work with differential drag for constellation management has focused on linearized control schemes for formation flight. However, the linearized equations used for close-proximity flight are not valid for maximum-separation missions [13, 14, 15]. While some work does exist on maximum-separation missions, conditions are simplified or details on the estimation and control scheme are omitted or inadequate [8, 16, 17, 18, 19]. This work uses an unscented Kalman filter to estimate mean orbital elements and a novel control scheme to first offset and then match relative mean semi-major axes. The separation of mean semi-major axes creates different mean motions such that allow for the relative mean anomalies to be controlled. Simulation results demonstrate that differential drag can be used to control and maintain satellites within 0.5 degrees of the desired mean anomaly relative to other satellites. For two satellites in the same orbital plane at 500 km altitude seeking to maximize separation, 0.5 degrees corresponds to an angle that can be traversed in under 10 seconds. For Earth observation mission, this has a negligible effect on revisit times and can be considered an acceptable result.
by Zachary Thomas Lee.
S.M.

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Kennedy, Andrew Kitrell. "Resource optimization algorithms for an automated coordinated CubeSat constellation." Thesis, Massachusetts Institute of Technology, 2015. http://hdl.handle.net/1721.1/101497.

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Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2015.
Cataloged from PDF version of thesis.
Includes bibliographical references (pages 119-125).
We present and analyze the performance of two algorithms that plan and coordinate activities for a resource-constrained Earth-observing CubeSat constellation. The first algorithm is the Resource-Aware SmallSat Planner (RASP), which performs low-level planning of observation and communication activities for a single satellite while simultaneously keeping the satellite's onboard resources within specified bounds. RASP utilizes a Mixed Integer Linear Program based formulation and Depth First Search for construction of consistent onboard activity timelines. The second algorithm is the Limited Communication Constellation Coordinator (LCCC), which performs high level coordination of observations across the constellation through a distributed, "weak" consensus mechanism. The performance of the algorithms is tested with a 24 hour simulation of an eighteen satellite constellation over multiple orbital geometries and inter-satellite communication contexts. The orbital geometries include a modified Walker Star constellation and an "ad hoc" constellation defined by historical launches of CubeSats. The multiple communication contexts simulate different methods for sharing observation planning information between the satellites, and include sharing through inter-satellite crosslinks, downlink and uplink to ground stations, connection to a commercial communications constellation, and no sharing at all. Five analyses of the algorithms' performance were conducted, including average revisit times achieved, the numbers of communications links executed, how effectively planning information was shared, the resource margins maintained by the satellites, and the average execution time for the planner. Information sharing significantly aided in balancing revisit times across multiple Earth regions and three sensor choices, reducing the disparity in average revisit times between sensors from 514 minutes to 10 minutes for the Walker case and 617 to 11 minutes for he Ad Hoc case. Significantly more crosslink opportunities were available on average for the Walker satellites than for Ad Hoc (89.2 versus 47.7) and more crosslinks were executed for the Walker case (30.3 versus 20.8). Crosslink was found to be less effective than downlink at sharing planning information across the constellation, with a lower average latency (186 minutes versus 434, Walker) and better average initial timeliness (-35 minutes versus -287, Walker). Information sharing through both a commercial constellation and downlink outperformed sharing through just downlink or just crosslink, with an average latency and initial timeliness of 77 and 74 minutes (Walker). Average data storage and energy storage margins were kept high, as desired, for both constellations, at around 85 and 70 %. RASP planning time was found to scale roughly with the square of planning window length, but stays under a minute in all cases tested (achieving a maximum of 37.71 seconds).
by Andrew Kitrell Kennedy.
S.M.

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Mtshemla, Kanyisa Sipho. "Mission design of a CubeSat constellation for in-situ monitoring applications." Thesis, Cape Peninsula University of Technology, 2017. http://hdl.handle.net/20.500.11838/2633.

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Thesis (MEng (Electrical Engineering))--Cape Peninsula University of Technology, 2017.
Real-time remote monitoring of Africa’s resources, such as water quality, by using terrestrial sensors is impeded by the limited connectivity over the vast rural areas of the continent. Without such monitoring, the effective management of natural resources, and the response to associated disasters such as flooding, is almost impossible. A constellation of nanosatellites could provide near real-time connectivity with ground-based sensors that are distributed across the continent. This study evaluates the high level development of a mission design for a near real-time remote monitoring CubeSat constellation and ground segment for in-situ monitoring in regions of interest on the African continent. This would facilitate management of scarce resources using a low-cost constellation. To achieve this, the design concept and operation of a Walker constellation are examined as a means of providing connectivity to a low bit rate sensor network distributed across geographic areas of interest in South Africa, Algeria, Kenya and Nigeria. The mission requirements include the optimisation of the constellation to maintain short revisit times over South Africa and an investigation of the required communications link to perform the operations effectively. STK software is used in the design and evaluation of the constellations and the communications system. The temporal performance parameters investigated are access and revisit times of the constellations to the geographic areas mentioned. The types of constellation configurations examined, involved starting with a system level analysis of one satellite. This seed satellite has known orbital parameters. Then a gradual expansion of two to twelve satellites in one, two and three orbital planes follows. VHF, UHF and S-band communication links are considered for low data rate in-situ monitoring applications. RF link budgets and data budgets for typical applications are determined. For South Africa, in particular, a total of 12 satellites evenly distributed in a two-plane constellation at an inclination of 39° provide the optimal solution and offer an average daily revisit time of about 5 minutes. This constellation provides average daily access time of more than 16 hours per day. A case study is undertaken that decribes a constellation for the provision of maritime vessel tracking in the Southern African oceans using the Automated Information System (AIS). This service supports the Maritime Domain Awareness (MDA) initiative implemented by the South African Government, under its Operation Phakisa.
National Research Foundation (NRF) French South African Institute of Technology (F’SATI)

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Pirkle, Scott J. "Design of a Martian Communication Constellation of CubeSats." DigitalCommons@CalPoly, 2020. https://digitalcommons.calpoly.edu/theses/2275.

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Spacecraft operating on the Martian surface have used relay satellites as a means of improving communication capabilities, mainly in terms of bandwidth and availability. However, the spacecraft used to achieve this have been large spacecraft (1000s of kilograms) and were not designed with relay capability as the design priority. This thesis explores the possibility of using a CubeSat-based constellation as a communications network for spacecraft operating on the Martian surface. Brute-force techniques are employed to explore the design space of possible constellations. An analysis of constellation configurations that provide complete, continuous coverage of the Martian surface is presented. The stability of these constellations are analyzed, and recommendations are made for stable configurations and the orbital maintenance thereof. Link budget analysis is used to determine the communications capability of each constellation, and recommendations are made for sizing each communication element. The results of these three analyses are synthesized to create an architecture generation tool. This tool is used to identify mission architectures that suit a variety of mission requirements, and these architectures are presented. The primary recommended architecture utilizes 18 CubeSats in three orbital planes with six additional larger relay satellites to provide an average of over one terabit/sol downlink and 100 kbps uplink capability.

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Kampmeier, Jennifer Lauren. "Continuous Solar Observation from Low Earth Orbit with a Two-Cubesat Constellation." Thesis, University of Colorado at Boulder, 2018. http://pqdtopen.proquest.com/#viewpdf?dispub=10746150.

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The goal of this work is to assess the feasibility of using a two-CubeSat constellation to make continuous solar science measurements from low Earth orbit. There is a growing interest in using CubeSats for scientific missions since they are relatively inexpensive, can be manufactured quickly, and they have a standard form factor. CubeSats have increased access to space, and there is a growing interest in the solar science community to be able to conduct remote sensing solar science missions from a CubeSat platform. By using a constellation separated by differential drag, this mission concept enables continuous measurements of the sun, allowing scientists to have a complete record despite the spacecraft's eclipse periods. In this thesis, I have developed a two-body propagator that takes various inputs for starting altitude, density model, attitude, and spacecraft configuration to enable investigation over a large trade space. Following the model development, I ran a series of simulations to explore the feasibility of this concept, finding that there are many combinations of parameters that produce a feasible mission design. I show that the model is validated by altitude decay data from the MinXSS CubeSat, I will discuss areas of the design that require further study, and I explore the logical next steps for future development of this concept.

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ZANETTE, LUCA. "Communication Networks in CubeSat Constellations: Analysis, Design and Implementation." Doctoral thesis, Politecnico di Torino, 2018. http://hdl.handle.net/11583/2704132.

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CubeSat constellations are redefining the way we approach to space missions, from the particular impact on scientific mission possibilities, constellations potential is growing with the increasing accessibility in terms of low development and launch costs and higher performances of the available technologies for CubeSats. In this thesis we focus on communication networks in CubeSat constellations: the project consist of developing a clustering algorithm able to group small satellites in order to create an optimized communication network by considering problems related to mutual access time and communication capabilities we reduce the typical negative effects of clustering algorithms such as ripple effect of re-clustering and optimizing the cluster-head formation number. The network creation is exploited by our proposed hardware system, composed by a phased array with up to 10dB gain, managed by a beamforming algorithm, to increase the total data volume transferable from a CubeSat constellation to the ground station. The total data volume earned vary from 40% to a peak of 99% more, depending on the constellation topology analyzed.

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Nelson, Jacqueline M. "Persistent military satellite communications coverage using a cubesat constellation in low earth orbit." Honors in the Major Thesis, University of Central Florida, 2010. http://digital.library.ucf.edu/cdm/ref/collection/ETH/id/1465.

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This item is only available in print in the UCF Libraries. If this is your Honors Thesis, you can help us make it available online for use by researchers around the world by following the instructions on the distribution consent form at http://library.ucf.edu/Systems/DigitalInitiatives/DigitalCollections/InternetDistributionConsentAgreementForm.pdf You may also contact the project coordinator, Kerri Bottorff, at kerri.bottorff@ucf.edu for more information.
Bachelors
Engineering and Computer Science
Electrical Engineering

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Grujicic, Julian. "A feasibility study for a satellite VHF Data Exchange System (VDES)." Thesis, KTH, Rymdteknik, 2019. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-262890.

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Transportation across the globe's oceans increases every year and is expected to keep increasing in the following decades. Consequently, there is a need to establish communication over the horizon through the Automatic Identification System (AIS) and the Very High Frequency (VHF) Data Exchange System (VDES), still in development, to track and communicate with vessels all over the globe regardless of the distance from shore. In this Master thesis a feasibility study for the development of a system that fulfils that need is proposed consisting of a Low Earth Orbit (LEO) constellation providing VDES communication continuously all over the globe. A system engineering approach has been followed, identifying stakeholders and producing system requirements setting up a framework for the system. The key stakeholders were found to be the customers/users, the satellite provider, the satellite operator, the service provider and the payload provider. Furthermore, possible use-cases were presented and a system architecture was defined to outline the system, dividing the system into three segments: the space segment, the ground segment and the launch segment. In addition, design proposals for a satellite constellation and a typical satellite in such a constellation were implemented. The satellite constellation was proposed to consist of 91 satellites at an orbit altitude of around 550 km in polar orbits of common inclination, this was regarding a minimum elevation angle of 10 degrees. The satellite is recommended to consist of a 6 U CubeSat using as payload the existing airborne transponder R5A from Saab TransponderTech, it builds on the Software Defined Radio (SDR) technology and is to be further developed for VDES applications. Moreover, a link- and a data budget were implemented. Different launch options were addressed concluding that launching as secondary payload on a ride-share mission or as primary payload on a small satellite launch vehicle are the preferable options. A market analysis has been made providing details on how many AIS/VDES satellites that have been launched into LEO and by which service provider, as well as further details on small/nano satellites of extra interest to this work. A short risk evaluation was also done, identifying the most evident risks with developing, operating and disposing the system. In addition, Saab's potential role in the development of satellite VDES is discussed. In conclusion to this work it has been shown that it is possible to build a global continuous satellite constellation in LEO utilising as payload an SDR-platform to provide VDES services to vessels at open seas.
Transport globalt till havs ökar varje år och förväntas fortsätta att öka de följande årtiondena. Följaktligen finns ett behov av att etablera över horisonten kommunikation genom det automatiska identifieringssystemet (AIS) och det väldigt högfrekventa datautbytessystemet (VDES), under utveckling, för att spåra och kommunicera med fartyg över hela världen oberoende av avståndet från land. I detta examensarbete har en förstudie utförts för utvecklingen av ett system som uppfyller detta behov. Systemet föreslås bestå av en låg jordbana satellitkonstellation som kontinuerligt tillhandahåller VDES-kommunikation över hela världen. Ett systemtekniskt tillvägagångssätt har följts, intressenter har identifierats och utifrån dessa har systemkrav tagits fram. De viktigaste intressenterna befanns vara användare/kunder, satellitleverantören, satellitoperatören, tjänsteleverantören och nyttolastleverantören. Vidare lyftes olika möjliga användningsområden för systemet fram och en systemarkitektur framställdes vari systemet delades in i tre segment: rymdsegmentet, marksegmentet och uppskjutningssegmentet. Dessutom genomfördes designförslag för en satellitkonstellation samt en typisk satellit i en sådan konstellation. Satellitkonstellationen föreslogs bestå av 91 satelliter på en altitud på omkring 550 km i polära banor med gemensam inklination, detta var gällande för en minimum elevationsvinkel på 10 grader. Satelliten rekommenderades bestå av en 6 U CubeSat med den befintliga luftburna transpondern R5A från Saab TransponderTech som nyttolast, vilken bygger på mjukvaruradioteknik och är tänkt att vidareutvecklas för VDES-applikationer. Vidare, implementerades en länk- och data budget. Olika uppskjutningsmöjligheter undersöktes, varav slutsatsen att uppskjutning som sekundär nyttolast på ett delningsuppdrag eller som primär nyttolast medhjälp av ett mindre uppskjutningsfordon anpassat för små satelliter var de föredragna alternativen. Även en marknadsanalys har genomförts, där det redogjorts för hur många AIS / VDES - satelliter som har uppskjutits i LEO och av vilken tjänsteleverantör, samt ytterligare detaljer om små / nano satelliter av extra intresse för arbetet. En kort riskbedömning har också gjorts, där de mest uppenbara riskerna med utveckling, drift och undanröjande av systemet identifierats. Dessutom diskuteras Saabs möjliga roll i utvecklingen av satellit VDES. Slutsatsen av detta arbete har visat att det är möjligt att bygga en global kontinuerlig satellitkonstellation i låg jordbana med en mjukvaruradio som nyttolast som tillhandahåller VDES-tjänster till fartyg på öppna hav.

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Книги з теми "CubeSat Constellation"

Stakem, Patrick. Cubesat Constellations, Clusters, and Swarms. Independently Published, 2017.

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Частини книг з теми "CubeSat Constellation"

Sushir, S., K. Ullas, Komal Prasad, and Vipul V. Kumar. "Antenna Deployment Mechanism for a 3U CubeSat Project." In Computer Aided Constellation Management and Communication Satellites, 17–29. Singapore: Springer Nature Singapore, 2023. http://dx.doi.org/10.1007/978-981-19-8555-3_3.

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Waghmare, Rahul G., V. Suresh Kumar, K. R. Yogesh Prasad, Suman R. Valke, L. Suvarna, N. Ramalakshmi, and D. Venkataramana. "Development of Payload Data Transmitter Using 8-bit Microcontroller and FM Transceiver for CubeSats." In Computer Aided Constellation Management and Communication Satellites, 31–38. Singapore: Springer Nature Singapore, 2023. http://dx.doi.org/10.1007/978-981-19-8555-3_4.

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Gonzales Palacios, Orlando Francois, Ricardo Erick Diaz Vargas, Patrick H. Stakem, and Carlos Enrique Arellano Ramirez. "Koch Snowflake Fractal Antenna Design in the Deep Space Bands for a Constellation of Cubesat Explorers." In Proceedings of CECNet 2021. IOS Press, 2021. http://dx.doi.org/10.3233/faia210419.

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This paper presents the design and simulation of a Koch curve fractal antenna, developed according to the second iteration of the Koch snowflake fractal for S-band, C-band, X-band and Ku-band. The simulated antenna shows good performance for the operating frequencies and desirable gain, bandwidth and VSWR parameters. Being a compact antenna, it has a size, geometry and characteristics that go in accord with the CubeSat’s structure standards. The antenna was fabricated on a 1.5 mm thick FR-4 substrate. The VSWR achieved values are lower than 1.4 for the frequencies used (2.1 GHz to 2.4 GHz and 7.4 GHz to 8.9 GHz) with a simulated omnidirectional radiation pattern. A maximum gain of 6.8 dBi was achieved. As this antenna works optimally in the S, C and X bands, it is adequate for deep space applications, especially in low-power consumption systems. This approach would be ideal for constellations of Cubesat explorers.

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Ivanov, Danil, and Mikhail Ovchinnikov. "Constellations and formation flying." In Cubesat Handbook, 135–46. Elsevier, 2021. http://dx.doi.org/10.1016/b978-0-12-817884-3.00006-0.

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Allahvirdi-Zadeh, Amir, Ahmed El-Mowafy, and Kan Wang. "Precise Orbit Determination of CubeSats Using Proposed Observations Weighting Model." In International Association of Geodesy Symposia. Berlin, Heidelberg: Springer Berlin Heidelberg, 2022. http://dx.doi.org/10.1007/1345_2022_160.

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AbstractCubeSats can be used for many space missions and Earth science applications if their orbits can be determined precisely. The Precise Orbit Determination (POD) methods are well developed for large LEO satellites during the last two decades. However, CubeSats are built from Commercial Off-The-Shelf (COTS) components and have their own characteristics, which need more investigations. In this paper, precise orbits of 17 3U-CubeSats in the Spire Global constellation are determined using both the reduced-dynamic and the kinematic POD methods. The limitations in using elevation-dependent weighting models for CubeSats POD are also discussed and, as an alternative approach, a weighting model based on the Signal-to-Noise Ratio (SNR) has been proposed. One-month processing of these CubeSats revealed that around 40% of orbits can be determined at the decimeter accuracy, while 50% have accuracy at centimeters. Such precise orbits fulfil most mission requirements that require such POD accuracy. Internal validation methods confirmed the POD procedure and approved the distinction of weighting based on SNR values over the elevation angles.

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Тези доповідей конференцій з теми "CubeSat Constellation"

Buck, Christopher. "Cubesat Constellation Concepts for Swath Altimetry." In IGARSS 2019 - 2019 IEEE International Geoscience and Remote Sensing Symposium. IEEE, 2019. http://dx.doi.org/10.1109/igarss.2019.8898067.

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Swenson, Charles M., Jacob Gunther, and Chad Fish. "Supporting communication needs of CubeSat constellation missions." In 2014 United States National Committee of URSI National Radio Science Meeting (USNC-URSI NRSM). IEEE, 2014. http://dx.doi.org/10.1109/usnc-ursi-nrsm.2014.6928054.

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Blommaert, Joris, Gerard Habay, Luca Maresi, Helene Strese, Alessandro Zuccaro Marchi, Benoit Deper, Mikko Viitala, et al. "CSIMBA: Towards a Smart-Spectral Cubesat Constellation." In IGARSS 2019 - 2019 IEEE International Geoscience and Remote Sensing Symposium. IEEE, 2019. http://dx.doi.org/10.1109/igarss.2019.8898081.

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Sermanoukian Molina, Iván, Lluís Montilla Rodríguez, David González Díez, Miquel Sureda Anfres, Jorge Mata Diaz, and Juan José Alins Delgado. "Mission analysis of nanosatellite constellations with OpenSatKit." In Symposium on Space Educational Activities (SSAE). Universitat Politècnica de Catalunya, 2022. http://dx.doi.org/10.5821/conference-9788419184405.006.

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CubeSat reliability is still considered an obstacle due to the sizeable fail rates generally attributed to the dead-on-arrival cases and early subsystem malfunctions. Thus, as CubeSats' primary purpose moves from technological demonstrations and university projects to missions where a significant risk of failure is not acceptable, an inexpensive method to emulate low Earth orbit constellations is being researched. The results presented have been developed in the framework of the PLATHON research project, which intends to develop a hardware-in-the-loop emulation platform for nanosatellite constellations with optical inter-satellite communication and ground-to-satellite links. Consequently, a crucial aspect of this project is to have a sufficiently precise orbital propagator with real-time manoeuvring control and graphical representation. NASA's OpenSatKit, a multi-faceted open-source platform with an inbuilt propagator known as 42, has been chosen to analyse the programme's feasibility in order to create a constellation testing bench. As an initial development of a software-in-the-loop application, the pre- processing of files has been automated; enhanced Attitude Determination and Control System manoeuvres have been added and configured through bidirectional socket interfaces, and the results format has been modified to be easily post-processed with MATLAB and Simulink

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Braun, Scott, Christopher Velden, Tom Greenwald, Derrick Herndon, Ralf Bennartz, Mark DeMaria, Galina Chirokova, et al. "Overview of the NASA TROPICS CubeSat Constellation Mission." In CubeSats and NanoSats for Remote Sensing II, edited by Charles D. Norton and Thomas S. Pagano. SPIE, 2018. http://dx.doi.org/10.1117/12.2320333.

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Knight, Tristan, Axel Rousse, Clémence Allietta, and Benjamin Bérat. "TOLOSAT project: Gravimetry and communication." In Symposium on Space Educational Activities (SSAE). Universitat Politècnica de Catalunya, 2022. http://dx.doi.org/10.5821/conference-9788419184405.009.

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The use of Constellations for weather science, security and disaster monitoring is a major challenge for space application services. Satellite to satellite communication using existing constellations has not been extensively explored yet. It can improve the communication times for small-satellite missions which have limited access to ground stations. Thus, a mission to demonstrate the feasibility of this link is required. Another element of interest in space application is Earth Observation, especially in the context of Climate Change. Gravimetry allows an understanding of mass transport in the Earth System through the remote sensing of the time variation of the Earth gravity field. CubeSats are low-cost small-scale and hence lower risk solutions to Earth Observation missions. University CubeSats have shown their success in demonstration and scientific missions, and have a great potential in providing students with practice and application on real space systems. In this context, the student associations ASTRE and SUPAERO CubeSat Club have joined in a CubeSat program called TOLOSAT, with the hope of demonstrating such technologies. Gathering 70 students from Toulouse, the team was split into subsystems in accordance with the concurrent engineering principles. The work performed followed recommendations from experts from the French National Centre for Space Studies (CNES) and the industry. The TOLOSAT payloads have to test and demonstrate new means of measuring gravity and addressing communication issues. Firstly, for the gravimetry mission, our approach relies solely on GNSS to compute the gravity field, avoiding expensive gravimeters. For the communication mission: the Iridium constellation will be used as an intermediate between the CubeSat and the ground station. Off-the-shelf components such as patch antennas are planned to prove their efficiency in orbit. This would improve the coverage and the communication window. The preliminary design was completed. TOLOSAT was designed as a 3-unit nanosatellite, on a 97.4° inclined, 500km high orbit. Margins were also ensured to allow a third payload to be defined in the future, that will be used for finance and partnerships. Detailed designs are still required, but the educational purposes have been fulfilled, in terms of discovery of the development of space missions as well as in the teamwork culture. The team is now moving on to a new phase, dedicated to a more detailed conception with an on-going focus on the introduction to students to technical - but not only - fields of knowledge applied to space systems

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Bedon, Hector, Carlos Negron, Jorge Llantoy, Carlos Miguel Nieto, and Cem Ozan Asma. "Preliminary internetworking simulation of the QB50 cubesat constellation." In 2010 IEEE Latin-American Conference on Communications (LATINCOM). IEEE, 2010. http://dx.doi.org/10.1109/latincom.2010.5640977.

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Altena, Bas, and Andreas Kaab. "Glacier ice loss monitored through the Planet cubesat constellation." In 2017 9th International Workshop on the Analysis of Multitemporal Remote Sensing Images (MultiTemp). IEEE, 2017. http://dx.doi.org/10.1109/multi-temp.2017.8035235.

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Adlakha, Paras, Dhananjay Notnani, Rohan Chandra, Monish Mathur, Servesh Chaturvedi, and Dr M. Raja. "Designing and Simulating a CubeSat constellation for Mars Exploration." In AIAA Scitech 2021 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2021. http://dx.doi.org/10.2514/6.2021-0694.

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Swenson, Charles M., Alan Marchant, Chad Fish, and Erik Syrstad. "CubeSat sensors and constellation missions for advancing space science." In 2014 United States National Committee of URSI National Radio Science Meeting (USNC-URSI NRSM). IEEE, 2014. http://dx.doi.org/10.1109/usnc-ursi-nrsm.2014.6928086.

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