Gotowe bibliografie tematyczne / CubeSat

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Gotowa bibliografia na temat „CubeSat”

Autor: Grafiati

Data publikacji: 4 czerwca 2021

Data aktualizacji: 14 marca 2023

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Artykuły w czasopismach na temat "CubeSat"

De Leon, Michael B., Ulysses B. Ante, Madelene S. Velasco, Arvin Oliver S. Ng, Joseph Alfred V. Garcia, Fred P. Liza, Rigoberto C. Advincula i John Ryan C. Dizon. "3D-Printing for Cube Satellites (CubeSats): Philippines‘ Perspectives". Engineering Innovations 1 (25.03.2022): 13–27. http://dx.doi.org/10.4028/p-35niy3.

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The increase in space exploration missions in recent years gave way to the development of a volume-efficient and cost-effective nanosatellite like the cube satellite (CubeSat) which can be developed and fabricated in a relatively short time. With its size and design, CubeSat parts like casings can be produced and assembled through 3D printing to produce inexpensive satellites. Research in this area is undeniably important to maximize the rapid development of CubeSats. While progress has been made, challenges remain in applying 3D printing technology in the development of CubeSats. In this paper, the current status regarding the advancement of 3D printing for CubeSat applications is discussed. First, important issues about the common materials for CubeSat and potentially 3D printing materials for CubeSats are addressed. Second, 3D printing CubeSat parts through the feasible structure design models by combining material and parameter designs are explored from a wide range of references. And also, 3D printing of cube satellite parts by DOST AMCen and STAMINA4Space has also been demonstrated. Lastly, an outlook on the future direction of the 3D printed CubeSat for the Philippines space program is provided.Keywords: Cube satellite, CubeSat, 3D printing, high-performance polymers

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Menchinelli, Alessandro, Francesca Ingiosi, Ludovico Pamphili, Paolo Marzioli, Riccardo Patriarca, Francesco Costantino i Fabrizio Piergentili. "A Reliability Engineering Approach for Managing Risks in CubeSats". Aerospace 5, nr 4 (15.11.2018): 121. http://dx.doi.org/10.3390/aerospace5040121.

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Besides large-scale space missions, the spread of CubeSats for a variety of applications is increasingly requiring the development of systematic approaches for risk management. Being these applications are based on components with low TRL (Technology Readiness Level) or with limited performance data, it is required to define approaches which ensure a systematic perspective. This paper aims to present a reliability engineering approach based on FMECA (Failure Mode, Effects, and Criticality Analysis) to manage CubeSat reliability data and prioritize criticalities early in the design phase. The approach firstly proposes an alpha-numeric coding system to support the identification and labeling of failure modes for typical CubeSats’ items. Subsequently, each FMECA coefficient (i.e., Severity, Occurrence, Detectability) has been linked to the CubeSat’s structural properties, reducing subjectivity by means of techno-centric proxy indicators. The approach has been validated in the design phases of a 6-Units university CubeSat for the observation of M-Dwarf stars and binary systems. The performed analysis supported the design process and allowed to identify the major criticalities of the CubeSat design, as demonstrated in the extended case study included in the paper. The formalized method could be applied to design procedures for nano-satellites, as well as being expanded for research and development in a variety of space missions.

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Sibanda, Matthew, i Robert Ryk van Zyl. "Practical electromagnetic compatibility studies of a CubeSat". Journal of Engineering, Design and Technology 14, nr 4 (3.10.2016): 770–80. http://dx.doi.org/10.1108/jedt-04-2014-0025.

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Purpose Incorporating electromagnetic compatibility (EMC) in the design life of traditional satellites is entrenched in the satellite industry. However, EMC treatment of CubeSats has not been widely pursued, for various possible reasons. CubeSats are a young technology platform initially intended for students and researchers at universities to create awareness and excitement amongst them for space technology. This and other factors limited the need for stringent EMC planning. As CubeSats mature in complexity, the success of future missions will rely on incorporating proper EMC designs in their development. This paper aims to address the experimental investigation of known EMC culprits within a CubeSat’s context. Design/methodology/approach Electromagnetic interference suppression effectiveness of cable trays in CubeSats, as well as crosstalk in high-speed/frequency data links, is investigated, using the PC/104 connector stack. Some recommendations for improving the EMC and, therefore, enhancing satellite mission success are provided. Findings It was found that, if physically feasible in the CubeSat, cable trays are significant radiation suppressors. A further investigation into crosstalk between pins of the PC/104 connector stack showed that grounding a pin in between two signal pins leads to a significant reduction in the coupled signal. Originality/value This paper addresses EMC within the context of a CubeSat and outlines experiments done resulting in cost-effective methods of reducing interference by using already available material (such as unused signal pins available in the PC/104 connector).

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Alanazi, Abdulaziz, i Jeremy Straub. "Engineering Methodology for Student-Driven CubeSats". Aerospace 6, nr 5 (13.05.2019): 54. http://dx.doi.org/10.3390/aerospace6050054.

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CubeSats are widely used by universities and research institutions all over the world. Their popularity is generally attributed to the use of low-cost components, free student labor and simple design. They have been shown to encourage Science, Technology, Engineering and Math (STEM) students to become involved in designing, implementing and testing a real functioning spacecraft system. Projects like this encourage students from different disciplines to team up to design and build CubeSats, providing interdisciplinary work experience. Participating students vary in their expertise in developing such systems. Some will work on the project for years while others are not willing to spend two or three consecutive semesters developing a CubeSat project. Despite their simplicity in design and low cost, CubeSats are considered great engineering systems for exploring space. Nevertheless, a large number of CubeSat projects fail due to having an unclear mission, ambiguous system requirements and a lack of documentation. Students need to have a clear vision of how to build a real CubeSat system that can be launched and that can function in space. Thus, this paper proposes engineering methodologies and tools to help students develop CubeSat systems. These tools can help students with planning, collecting, eliciting and documenting the requirements in a well-defined manner. This paper focuses on student-driven CubeSat projects designed by students and faculty members. Additionally, data is presented in this paper to identify the challenges and needs of CubeSat developers. Plans for future work are also discussed.

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Lu, Sining, Panagiotis Ioannis Theoharis, Raad Raad, Faisel Tubbal, Angelos Theoharis, Saeid Iranmanesh, Suhila Abulgasem, Muhammad Usman Ali Khan i Ladislau Matekovits. "A Survey on CubeSat Missions and Their Antenna Designs". Electronics 11, nr 13 (27.06.2022): 2021. http://dx.doi.org/10.3390/electronics11132021.

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CubeSats are a class of miniaturized satellites that have become increasingly popular in academia and among hobbyists due to their short development time and low fabrication cost. Their compact size, lightweight characteristics, and ability to form a swarm enables them to communicate directly with one another to inspire new ideas on space exploration, space-based measurements, and implementation of the latest technology. CubeSat missions require specific antenna designs in order to achieve optimal performance and ensure mission success. Over the past two decades, a plethora of antenna designs have been proposed and implemented on CubeSat missions. Several challenges arise when designing CubeSat antennas such as gain, polarization, frequency selection, pointing accuracy, coverage, and deployment mechanisms. While these challenges are strongly related to the restrictions posed by the CubeSat standards, recently, researchers have turned their attention from the reliable and proven whip antenna to more sophisticated antenna designs such as antenna arrays to allow for higher gain and reconfigurable and steerable radiation patterns. This paper provides a comprehensive survey of the antennas used in 120 CubeSat missions from 2003 to 2022 as well as a collection of single-element antennas and antenna arrays that have been proposed in the literature. In addition, we propose a pictorial representation of how to select an antenna for different types of CubeSat missions. To this end, this paper aims is to serve both as an introductory guide on CubeSats antennas for CubeSat enthusiasts and a state of the art for CubeSat designers in this ever-growing field.

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Villela, Thyrso, Cesar A. Costa, Alessandra M. Brandão, Fernando T. Bueno i Rodrigo Leonardi. "Towards the Thousandth CubeSat: A Statistical Overview". International Journal of Aerospace Engineering 2019 (10.01.2019): 1–13. http://dx.doi.org/10.1155/2019/5063145.

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CubeSats have become an interesting innovation in the space sector. Such platforms are being used for several space applications, such as education, Earth remote sensing, science, and defense. As of May 31st, 2018, 855 CubeSats had been launched. Remote sensing application is the main sector in which CubeSats are being used, corresponding to about 45% of all applications. This fact indicates the commercial potential of such a platform. Fifty eight countries have already been involved with developing CubeSats. The most used CubeSat configuration is 3U (about 64%), followed by 1U (18%), while 6U platforms account for about 4%. In this paper, we present an analysis of the current situation regarding CubeSats worldwide, through the use of a dataset built to encompass information about these satellites. The overall success rate of the CubeSat missions is increasing over time. Moreover, considering CubeSat missions as a Bernoulli experiment, and excluding launch failures, the current success rate was estimated, as a parameter of a binomial distribution, to be about 75%. By using a logistic model and considering that the launchings keep following the current tendency, one can expect that one thousand CubeSats will be launched in 2021, within 95% certainty.

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Meftah, Mustapha, Fabrice Boust, Philippe Keckhut, Alain Sarkissian, Thomas Boutéraon, Slimane Bekki, Luc Damé i in. "INSPIRE-SAT 7, a Second CubeSat to Measure the Earth’s Energy Budget and to Probe the Ionosphere". Remote Sensing 14, nr 1 (1.01.2022): 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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Benson, Ilia, Adam Kaplan, James Flynn i Sharlene Katz. "Fault-Tolerant and Deterministic Flight-Software System For a High Performance CubeSat". International Journal of Grid and High Performance Computing 9, nr 1 (styczeń 2017): 92–104. http://dx.doi.org/10.4018/ijghpc.2017010108.

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We describe the design and implementation of a complete flight-software operating system (OS) for a high-performance CubeSat carrying a third-party payload. This CubeSat's mission is to carry out research experiments on this payload while in low earth orbit. These experiments may be specified and prepared on the ground while the CubeSat is already in flight, and later uploaded via communication link. Experimental results collected by the CubeSat may likewise be downloaded to the ground. The CubeSat must collect and respond to sensor telemetry every second, and respond to ground communication on demand. To survive an adversarial space environment, the CubeSat OS is implemented as a deterministic state machine, storing state in a fault tolerant global memory structure. We validate our system via an end to end test of the CubeSat with its ground station, and demonstrate its capability to tolerate and even actively mitigate potential faults resulting from space radiation.

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Vidal-Valladares, Matías G., i Marcos A. Díaz. "A Femto-Satellite Localization Method Based on TDOA and AOA Using Two CubeSats". Remote Sensing 14, nr 5 (24.02.2022): 1101. http://dx.doi.org/10.3390/rs14051101.

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This article presents a feasibility analysis to remotely estimate the geo-location of a femto-satellite only using two station-CubeSats and the communication link between the femto-satellite and each CubeSat. The presented approach combines the Time Difference Of Arrival (TDOA) and Angle Of Arrival (AOA) methods. We present the motivation, the envisioned solution together with the constraints for reaching it, and the best potential sensitivity of the location precision for different (1) deployment scenarios of the femto-satellite, (2) precisions in the location of the CubeSats, and (3) precisions in each CubeSat’s Attitude Determination and Control Systems (ADCS). We implemented a simulation tool to evaluate the average performance for different random scenarios in space. For the evaluated cases, we found that the Cramér-Rao Bound (CRB) for Gaussian noise over the small error region of the solution is highly dependent on the deployment direction, with differences in the location precision close to three orders of magnitude between the best and worst deployment directions. For the best deployment case, we also studied the best location estimation that might be achieved with the current Global Navigation Satellite System (GNSS) and ADCS commercially available for CubeSats. We found that the mean-square error (MSE) matrix of the proposed solution under the small error condition can attain the CRB for the simulated time, achieving a precision below 30 m when the femto-satellite is separated by around 800 m from the mother-CubeSat.

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Stesina, Fabrizio, Sabrina Corpino i Daniele Calvi. "A Test Platform to Assess the Impact of Miniaturized Propulsion Systems". Aerospace 7, nr 11 (16.11.2020): 163. http://dx.doi.org/10.3390/aerospace7110163.

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Miniaturized propulsion systems can enable many future CubeSats missions. The advancement of the Technology Readiness Level of this technology passes through the integration in a CubeSat platform and the assessment of the impact and the interactions of the propulsion systems on the actual CubeSat technology and vice versa. The request of power, the thermal environmental, and the electromagnetic emissions generated inside the platform require careful analyses. This paper presents the upgraded design and the validation of a CubeSat test platform (CTP) that can interface a wide range of new miniaturized propulsion systems and gather unprecedented information for these analyses, which can be fused with the commonly used ground support equipment. The CTP features are reported, and the main achievements of the tests are shown, demonstrating the effective capabilities of the platform and how it allows for the investigation of the mutual interactions at system level between propulsion systems and the CubeSat technology.

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Rozprawy doktorskie na temat "CubeSat"

Erlank, Alexander Olaf. "Development of CubeStar : a CubeSat-compatible star tracker". Thesis, Stellenbosch : Stellenbosch University, 2013. http://hdl.handle.net/10019.1/85746.

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Thesis (MEng)-- Stellenbosch University, 2013.
ENGLISH ABSTRACT: The next generation of CubeSats will require accurate attitude knowledge throughout orbit for advanced science payloads and high gain antennas. A star tracker can provide the required performance, but star trackers have traditionally been too large, expensive and power hungry to be included on a CubeSat. The aim of this project is to develop and demonstrate a CubeSat compatible star tracker. Subsystems from two other CubeSat components, CubeSense and CubeComputer, were combined with a sensitive, commercial image sensor and low-light lens to produce one of the smallest star trackers in existence. Algorithms for star detection, matching and attitude determination were investigated and implemented on the embedded system. The resultant star tracker, named CubeStar, can operate fully autonomously, outputting attitude estimates at a rate of 1 Hz. An engineering model was completed and demonstrated an accuracy of better than 0.01 degrees during night sky tests.
AFRIKAANSE OPSOMMING: Die volgende generasie van CubeSats sal akkurate orientasie kennis vereis gedurende 'n volle omwentelling van die aarde. 'n Sterkamera kan die vereiste prestasie verskaf, maar sterkameras is tradisioneel te groot, duur en krag intensief om ingesluit te word aanboord 'n CubeSat. Die doel van hierdie projek is om 'n CubeSat sterkamera te ontwikkel en te demonstreer. Substelsels van twee ander CubeSat komponente, CubeSense en CubeComputer, was gekombineer met 'n sensitiewe kommersiële beeldsensor en 'n lae-lig lens om een van die kleinste sterkameras op die mark te produseer. Algoritmes vir die ster opsporing, identi kasie en orientasie bepaling is ondersoek en geïmplementeer op die ingebedde stelsel. Die gevolglike sterkamera, genaamd CubeStar, kan ten volle outonoom orientasie afskattings lewer teen 'n tempo van 1 Hz. 'n Ingenieursmodel is voltooi en 'n akkuraatheid van beter as 0.01 grade is gedemonstreer.

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Slettebo, Christian. "CubeSub : A CUBESAT BASED SUBMERSIBLE TESTBED FOR SPACE TECHNOLOGY". Thesis, KTH, Flygdynamik, 2016. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-198521.

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This report is a Master’s Thesis in Aerospace Engineering, performed at the NASA Ames Research Center. It describes the development of the CubeSub, a submersible testbed compatible with the CubeSat form factor. The CubeSub will be used to mature technology and operational procedures to be used in space exploration, and possibly also as a tool for exploration of Earthly environments. CubeSats are carried as payloads, either containing technology to be tested or experiments and sensors for scientific use. The CubeSub is designed to be built up by modules, which can be assembled in different configurations to fulfill different needs. Each module is powered individually and intermodular communication is wireless, reducing the need for wiring. The inside of the hull is flooded with ambient water to simplify the interaction between payloads and surrounding environment. The overall torpedo-like shape is similar to that of a conventional AUV, slender and smooth. This is to make for a low drag, reduce the risk of snagging on surrounding objects and make it possible to deploy through an ice sheet via a narrow borehole. Rapid prototyping is utilized wherever possible. Full-scale prototypes have been constructed through 3D-printing and using COTS (Commercial Off-The-Shelf) components. Arduino boards are used for control and internal communication. Modules required for basic operation have been designed, manufactured and tested. Each module is described with regards to its function, design and manufacturability. By performing tests in a pool it was found that the basic concept is sound and that future improvements include better controllability, course stability and waterproofing of electrical components. Further development is needed to make the CubeSub usable for its intended purposes. The largest gains are expected to be found by developing the software and improving controllability.

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castello, brian. "CUBESAT MISSION PLANNING TOOLBOX". DigitalCommons@CalPoly, 2012. https://digitalcommons.calpoly.edu/theses/787.

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We are in an era of massive spending cuts in educational institutions, aerospace companies and governmental entities. Educational institutions are pursuing more training for less money, aerospace companies are reducing the cost of gaining ight heritage and the government is cutting budgets and their response times. Organizations are accomplishing this improved efficiency by moving away from large-scale satellite projects and developing pico and nanosatellites following the CubeSat specifications. One of the major challenges of developing satellites to the standard CubeSat mission requirements is meeting the exceedingly tight power, data and communication constraints. A MATLAB toolbox was created to assist the CubeSat community with understanding these restrictions, optimizing their systems, increasing mission success and decreasing the time building to these initial requirements. The Toolbox incorporated the lessons learned from the past nine years of CubeSats' successes and Analytical Graphics, Inc. (AGI)'s Satellite Tool Kit (STK). The CubeSat Mission Planning Toolbox (CMPT) provides graphical representations of the important requirements a systems engineer needs to plan their mission. This includes requirements for data storage, ground station facilities, orbital parameters, and power. CMPT also allows for a comparison of broadcast (BC) downlinking to Ground Station Initiated (GSI) downlinking for payload data using federated ground station networks. Ultimately, this tool saves time and money for the CubeSat systems engineer

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Tapparel, Pierre-André. "CDMS pour cubesat /". Sion, 2006. http://doc.rero.ch/search.py?recid=8376&ln=fr.

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Horký, Jan. "Řídicí jednotka pro CubeSat". Master's thesis, Vysoké učení technické v Brně. Fakulta elektrotechniky a komunikačních technologií, 2017. http://www.nusl.cz/ntk/nusl-318165.

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Cílem práce je návrh univerzální řídicí jednotky pro CubeSat založené na obvodu FPGA. Taková jednotka doposud nebyla komerčně dostupná a navržená jednotka má tak dobrý potenciál zaplnit příslušné místo na trhu komponent pro CubeSat. Celá jednotka je navržena z komerčně dostupných komponent. Návrh jednotky je proveden tak, aby umožnil její funkci ve vesmírném prostředí. Stav konfigurace FPGA je pravidelně kontrolován a v případě zjištěné chyby dochází automaticky k rekonfiguraci FPGA a návratu jednotky do výchozího stavu. Jednotka obsahuje sadu senzorů, které monitorují její stav a v případě potřeby je možné na základě jejich výstupů provést opatření z hlediska ochrany funkce jednotky. Dvě paměti MRAM umožňují uložení tovární a uživatelské konfigurace FPGA, mezi kterými dochází k automatickému přepnutí na základě korektnosti uživatelské konfigurace.

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Harris, Anthony D. "NPS CubeSat Launcher-lite sequence". Thesis, Monterey, Calif. : Naval Postgraduate School, 2009. http://edocs.nps.edu/npspubs/scholarly/theses/2009/Jun/09Jun%5FHarris.pdf.

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Thesis (M.S. in Space Systems Operations)--Naval Postgraduate School, June 2009.
Thesis Advisor(s): Newman, James H. "June 2009." Description based on title screen as viewed on July 10, 2009. Author(s) subject terms: NPSCuL, NPSCuL-Lite, P-POD, Sequencer, Launcher, Launch Vehicle, Microcontroller, Space, Satellite. Includes bibliographical references (p. 167-168). Also available in print.

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Hicks, Christina M. "NPS CubeSat Launcher program management". Thesis, Monterey, California : Naval Postgraduate School, 2009. http://edocs.nps.edu/npspubs/scholarly/theses/2009/Sep/09Sep%5FHicks.pdf.

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Thesis (M.S. in Space Systems Operations)--Naval Postgraduate School, September 2009.
Thesis Advisor(s): Newman, James H. "September 2009." Description based on title screen as viewed on November 10, 2009. Author(s) subject terms: NPSCuL, CubeSat, Launcher, P-POD, ABC, Aft Bulkhead Carrier, Centaur, ESPA, Secondary Payload, Program Management. Includes bibliographical references (p. 61-63). Also available in print.

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Frances, Matas Jordi. "Internal Wireless Bus for a CubeSat". Thesis, Norges teknisk-naturvitenskapelige universitet, Institutt for elektronikk og telekommunikasjon, 2013. http://urn.kb.se/resolve?urn=urn:nbn:no:ntnu:diva-23088.

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NTNU (Norwegian University of Science and Technology) hosts NUTS (NTNU Test Satellite), which is mainly envisioned as an educational satellite where most tasks are performed by students while supported by university staff. As a peculiarity this CubeSat, unlike many others, is not based on the PC104 Standard. It is, instead, developed around a backplane approach, similar to a motherboard on a desktop computer. This novel approach left us without the possibility to use readily available commercial modules for CubeSats and also with the responsibility to design an ad-hoc solution for power distribution and on-Board communication. CubeSat Space Protocol on an I2C-bus was decided as the solution for the main communication bus.Although for this given satellite the payload will be an IR Camera, the main idea is to develop a reusable platform for a variety of payloads. Thus the exploration of new and novel technologies to be used in such platforms is also a goal. Specifically studying the viability of using an intra-satellite RF link is a specific area that NUTS is keen on exploring. Therefore a communication bus on radio is being developed. There are some advantages to the use of a wireless intra-satellite bus including: lower costs (both economic and in weight) and the possibility to have several transmissions in parallel. The latter could be attained by the use of virtual channels(or similar solutions) that most vendors provide on their radio kits. A proper exploitation of such features would significantly increase throughput while not requiring additional hardware.The RF link would only be the physical layer, as it is intended to still use CSP on top of it. By keeping CSP an easier portability insured to those CubeSats that already rely on CSP.COTS radio modules are being used on the proof-of-concept implementation. This should also help for an easier deployment of this communications approach on future satellites, since components are readily available. Those satellites that are equipped with both wired and wireless busses for communication, such as NUTS, could use one as a fallback solution should the other fail. Since most of the communication stack would remain untouched the transitions between wired and wireless busses should be seamless. The implementation is kept as hardware independent as possible, thus deploying it on other satellites should be relatively effortless.

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Griffith, Robert C. "Mobile Cubesat Command and Control (MC3)". Thesis, Monterey, California. Naval Postgraduate School, 2011. http://hdl.handle.net/10945/5591.

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Approved for public release; distribution is unlimited.
The Mobile CubeSat Command and Control (MC3) program will become the ground segment of the Colony II satellite program. The MC3 ground station contains Commercial Off-the-Shelf (COTS) hardware with Government Off-the-Shelf (GOTS) software making it an affordable option for government agencies and universities participating in the Colony II program. Further, the MC3 program provides educational opportunities to students and training to space professionals in satellite communications. This thesis analyzes the MC3 program from the program manager's point of view providing a Concept of Operations (CONOPS) of the program as well as initial analysis of MC3 ground station locations. Also included in this thesis is a future cost analysis of the MC3 program as well as lessons learned from the NPS acquisition process.

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Ziegler, Caleb Kevin. "A jam-resistant CubeSat communications architecture". Thesis, Massachusetts Institute of Technology, 2017. http://hdl.handle.net/1721.1/112484.

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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 133-140).
This thesis proposes a communications system that utilizes the benefits of CubeSats to provide jam-resistant communications. The growth of CubeSats within educational communities has prompted their use in industry; both industry and academia have contributed towards making CubeSats much more capable. CubeSats can now perform many advanced missions, from technology demonstrations to Earth observation missions and science missions. Meanwhile, military satellite communications (MILSATCOM) continues to rely primarily on large, highly-capable satellites. CubeSats could augment MILSATCOM by providing many low-cost space terminals with short development times as a means to create a more robust communications suite. The CubeSat communications architecture proposed in this thesis aims to support mobile users in hostile environments who need to relay information to a command center. Jam-resistant communications are achieved by performing ground-based beam-forming (GBBF) on a radio-frequency (RF) uplink and relaying the information to a ground station via a laser communications (lasercom) downlink: each CubeSat acts as an element of a sparse antenna array. With the growth of free-space lasercom in the last decade, lasercom is now a reality on CubeSat-scale platforms. Lasercom systems have lower size, weight, and power (SWaP) compared to RF systems with similar data rates, making them a good fit for CubeSat platforms. GBBF is a special case of beamforming where each element of an antenna array relays its signal to a ground station for processing, minimizing complexity on the space terminal. Beam-forming provides anti-jamming capabilites due to the spacings between elements in the array, also known as spatial diversity. This spatial diversity allows spatial filtering to occur, which modifies the array's radiation pattern to mitigate interference, add gain to the main lobe, or add multiple beams. The system is designed with the goal of minimizing cost and development time, and two ways of accomplishing this are by supporting currently fielded handheld RF transmitters and by utilizing a lasercom downlink which is being developed as part of the Nanosatellite Optical Downlink Experiment (NODE) in MIT's Space, Telecommunications, Astronomy, and Radiation Lab (STARLab). This thesis builds on previous work done on the NODE project, specifically the waveform design for NODE. NODE is a 3U CubeSat demonstrating a lasercom down-link while in low Earth Orbit (LEO). NODE uses 200mW transmit power to obtain data rates from 8 Mbps to 80 Mbps. The Optical Communications Telescope Laboratory (OCTL) at the Jet Propulsion Laboratory (JPL) and an amateur telescope will be used as optical ground stations. In order to send information to the ground station, NODE uses a waveform that provides forward error correction (FEC) and interleaving to mitigate channel effects. This thesis develops the channel coding, interleaving, modulation, and framing approach employed in the NODE waveform to provide error-free communications. A Reed-Solomon code, selected because of its performance and the existence of open-source implementations, provides error-correction capabilities. NODE uses a one-second interleaver to combat the effects of channel fading when the laser beam passes through the atmosphere. The transmitter uses pulse position modulation (PPM), an intensity modulation scheme that uses the delay of a single pulse within a symbol time to transmit information, due to the advantages in using a duty-cycled waveform with an average-power limited optical amplifier. Since the delay of the pulse conveys information for PPM, the transmitter clock must be recovered in order to properly demodulate the received waveform, and NODE uses inter-symbol guard times to encode the transmitter clock onto the waveform. Python simulations are presented showing that the channel coding, interleaving, and modulation are sufficient to obtain error-free communications with a target channel bit error rate (BER) of 1 x 10-⁴. The modulator is implemented within a field programmable gate array (FPGA), and the design, validation, and testing of the modulator are described. The feasibility of performing GBBF on RF uplinks to CubeSats in LEO, where each CubeSat acts as an element of an adaptive array, is examined. The high Doppler and large spacing between CubeSats requires the use of a space-time-frequency adaptive processor (STFAP). The STFAP consists of Doppler and delay taps, complex weights, an adaptive processor, a polyphase filter bank, and a polyphase combiner. The STFAP becomes infeasible as the Doppler and delay spread between different CubeSats increases, and analysis is used to identify scenarios where the Doppler and delay spreads seen in LEO are acceptable. Systems Tool Kit (STK) simulations are performed to analyze the Doppler and delay environment in LEO. Two CubeSat formations and multiple orientations between a user and jammer are examined to determine cases where null-forming, a special case of beamforming, is effective. A constellation is necessary to provide global coverage and maximize the effectiveness of null-forming, and two possible constellations are discussed.
by Caleb Kevin Ziegler.
S.M.

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Książki na temat "CubeSat"

Italy) IAA Conference on University Satellite Missions and CubeSat Workshop (5th 2020 Rome. Fifth IAA Conference on University Satellite Missions and CubeSat Workshop 2020: Proceedings of the 5th Conference on Unbiversity Satellite Missions and CubeSat Workshop, held January 28-31, 2020, Rome, Italy. San Diego, Calif: Published for the American Astronautical Society by Univelt, 2020.

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Kwon, Young W. Direct manufacturing of CubeSat using 3-D digital printer and determination of its mechanical properties. Monterey, California: Naval Postgraduate School, 2010.

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Olson, Nathan. Cubes. Mankato, Minn: Capstone Press, 2008.

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illustrator, Mitter Kathy, red. Cubes. Minneapolis: Magic Wagon, 2012.

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1922-, Hemmings Ray, i Leapfrogs Limited, red. Cubes. Diss: Leapfrogs, 1986.

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Cubes: Roman. Paris: Stock, 2009.

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Cubos =: Cubes. North Mankato, MN: Capstone Press, 2013.

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Lewitt, Sol. 100 cubes. Ostfildern: Cantz, 1996.

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Lewitt, Shariann. 100 cubes. Ostfildern [Germany]: Cantz, 1996.

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America, Cuisenaire Company of, red. Snap cubes. White Plains, NY: Cuisenaire Co. of America, 1996.

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Części książek na temat "CubeSat"

Welle, Richard P. "Overview of CubeSat Technology". W Handbook of Small Satellites, 1–17. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-20707-6_3-1.

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Welle, Richard P. "Overview of CubeSat Technology". W Handbook of Small Satellites, 51–67. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-36308-6_3.

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Suhadis, N. M. "Statistical Overview of CubeSat Mission". W Lecture Notes in Mechanical Engineering, 563–73. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-4756-0_50.

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Brandon, Carl, i Peter Chapin. "A SPARK/Ada CubeSat Control Program". W Reliable Software Technologies – Ada-Europe 2013, 51–64. Berlin, Heidelberg: Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-38601-5_4.

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Welle, Richard, Siegfried Janson, Darren Rowen i Todd Rose. "CubeSat-Scale High-Speed Laser Downlinks". W Proceedings of the 13th Reinventing Space Conference, 7–17. Cham: Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-32817-1_2.

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Eastwood, Jonathan, i John Bellardo. "HeL1oNano: The first CubeSat to L1?" W Proceedings of the 13th Reinventing Space Conference, 49–58. Cham: Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-32817-1_6.

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Speretta, Stefano, Angelo Cervone, Prem Sundaramoorthy, Ron Noomen, Samiksha Mestry, Ana Cipriano, Francesco Topputo i in. "LUMIO: An Autonomous CubeSat for Lunar Exploration". W Space Operations: Inspiring Humankind's Future, 103–34. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-11536-4_6.

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Kelley, R. L., i D. R. Jarkey. "Cubesat Material Limits for Design for Demise". W Space Safety is No Accident, 479–82. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-15982-9_55.

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Honoré-Livermore, Evelyn, i Cecilia Haskins. "Model-Based Systems Engineering for CubeSat FMECA". W Recent Trends and Advances in Model Based Systems Engineering, 529–40. Cham: Springer International Publishing, 2022. http://dx.doi.org/10.1007/978-3-030-82083-1_45.

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Schoolcraft, Josh, Andrew Klesh i Thomas Werne. "MarCO: Interplanetary Mission Development on a CubeSat Scale". W Space Operations: Contributions from the Global Community, 221–31. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-51941-8_10.

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Streszczenia konferencji na temat "CubeSat"

Woo, Hyunwook, Octavio Rico, Simone Chesi i Marcello Romano. "CubeSat Three Axis Simulator(CubeTAS)". W AIAA Modeling and Simulation Technologies Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-6271.

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Khan, Muhammad Shadab, Rauno Gordon, Martin Simon, Kristjan Tonismae, Dzmitry Kananovich, Veljo Sinivee, Marko Karm i Kaarel Repän. "Development and flight results of TalTech University CubeSat mission". W Symposium on Space Educational Activities (SSAE). Universitat Politècnica de Catalunya, 2022. http://dx.doi.org/10.5821/conference-9788419184405.117.

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Student Satellite program at TalTech, Tallinn University of Technology, Tallinn, Estonia was initiated in 2014 with an aim to impart space technology knowledge to the Estonian students as well as assist towards development of new Space Technologies in Estonia. Two 1-Unit CubeSat named Koit and Hämarik that translates respectively as Dawn and Twilight in Estonian are part of the TalTech Satellite Program. The main scientific mission of the CubeSats was to demonstrate Earth observation and Optical Communication technology. Satellites had two types of cameras, an RGB Camera and an NIR Camera to carry out Earth Observation over Estonia. Testing High Speed Optical communication technology from LEO (Low Earth Orbit) was the second major scientific goal and for this purpose the CubeSats had LED (Light Emitting Diode). Koit CubeSat was successfully launched to space on-board Soyuz rocket on July 5, 2019 and Hämarik CubeSat was launched to Space on September 3, 2020 on-board Arianespace Vega Rocket. Koit CubeSat did not contact the Ground station for more than a year since its launch and it was assumed to be lost but on November 21, 2020 it made the first contact with the Ground Station. Hämarik CubeSat was first contacted on November 15, 2020. The team has been successful in updating software of Hämarik and further work is being done on the software with broader functions. Optical communication has not been tested yet because ground station for optical communication has not been developed yet but a good achievement in the path to optical communication was to see the satellites with small hobby telescope and one of the satellite team member was successful to detect the Hämarik CubeSat on 17 August 2021 which was at a distance of about 792 Kilometres. Satellite team is in contact with the Hämarik and has been successful to download a few thumbnails and is working to establish a quick data connection with it and determine its exact position so that the cameras can be focused towards the Earth in order to get the whole images captured by the CubeSat.

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Eschelmüller, V., A. Stren, M. Issa, J. Bauer, A. Goswami, E. Vitztum, K. Repän, W. Treberspurg i C. Scharlemann. "Development of a CubeSat CLIMBing to the Van-Allen belt". W Symposium on Space Educational Activities (SSAE). Universitat Politècnica de Catalunya, 2022. http://dx.doi.org/10.5821/conference-9788419184405.048.

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Based on its successful CubeSat mission PEGASUS, the University of Applied Sciences Wiener Neustadt (FHWN) is preparing its new CubeSat mission called CLIMB. CLIMB is a 3U CubeSat that will be launched to a low, circular orbit of about 500 km. Using a Field Emission Electric Propulsion (FEEP) system commercialized by the company ENPULSION, the satellite will be lifted to an elliptical orbit with its apogee around 1000 km – well inside the inner Van Allen belt. During its 1.5 yearlong ascent and its operation in the Van Allen belt, the satellite will continuously monitor the space radiation with a RadFET dosimeter payload and the impact on CLIMB’s subsystems. Comparisons with radiation testing on ground will allow the assessment of the capability of ground tests to predict effects of space radiation on CubeSat subsystems. The operation of the propulsion system will raise the satellite’s apogee on average 16 times a day. A comprehensive analysis has been conducted to assess its collision probability throughout its mission time. Using various tools, provided by ESA (CROC, MASTER and the DRAMA ARES python package), the collision probability for the entire mission duration (~3 years) was calculated to be 3.38 × 10-5, i.e. a magnitude smaller than the requested probability of 10-4. The second payload of CLIMB is an anisotropic magnetoresistance (AMR) magnetometer with a, for CubeSats high, sensitivity of about 10 nT RMS. The first results of measurements with this COTS based magnetometer are presented as well as experimental assessments of the satellite’s magnetic cleanliness. The benign thermal conditions on CubeSats operating close to Earth are complicated by the relatively high-power propulsion system onboard CLIMB. Detailed numerical analysis (ANSYS, ESATAN) and experimental verifications resulted in the identification of possible methods to deal with up to 18 W of dissipated electric power. The main heat sources are the thruster and the battery unit, during thruster operation

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"CubeSat Program". W 55th International Astronautical Congress of the International Astronautical Federation, the International Academy of Astronautics, and the International Institute of Space Law. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.iac-04-p.5.b.06.

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Cormier, Luis, Daniel Robson i Henry Cope. "FlatSat workshops teaching fundamental electronics skills for CubeSat building". W Symposium on Space Educational Activities (SSAE). Universitat Politècnica de Catalunya, 2022. http://dx.doi.org/10.5821/conference-9788419184405.095.

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The University of Nottingham (UoN) recently established its own CubeSat programme, with the team commencing design, construction and testing of the first CubeSats in late 2020. However, one major challenge encountered was a common lack of practical applied electronics skills amongst students. This was repeatedly noted by students as a major obstacle to project success in progress reviews for WormSail, our first CubeSat project. Notably, these sorts of skills are also an area of common concern for young workers and employers in the UK Space Sector. This skill gap existed despite the student team coming from a variety of STEM (Science, Technology, Engineering and Math) undergraduate backgrounds, including physics, computer science, and aerospace and mechanical engineering. With insufficient time to recruit students with electronic engineering backgrounds, it proved difficult to find "all-rounders" to join the team with the broad range of skills required for the project. One advantage that several students had however was their experience from informal hobbies involving Arduino and Raspberry Pi (RPi) based microcontroller electronics. These were found to endow highly transferrable skills, with these members providing significant contributions to the team through their skills and teaching. Team members found these so useful, that the “FlatSat” programme was set up to provide electronics teaching resources for new members of the CubeSat team. Sessions within the programme could be planned and delivered by the experienced team members, and hence be targeted to include applicable, referrable, and important skills and knowledge for building CubeSats. Through developing these resources, the team realised it may be beneficial to include this programme in taught modules offered in the Faculty of Engineering, to enhance practical skills for all students enrolled in these modules. This paper is intended to overview the work carried out in developing the FlatSat teaching workshop, and highlight the resources and their benefits to groups including other higher education space module conveners, developing CubeSat teams, School and further education teachers, STEM Outreach Coordinators, and general hobbyists. It is hoped that boosting confidence with such in-demand skills will be of great benefit to learners. We will also review case studies of the first large-scale workshop sessions and outline plans for future developments, particularly taking into consideration the feedback of demonstrators, students, and observers to the workshop.

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Ali, Anwar, Leonardo Reyneri, Juan Carlos de los Rios, Haider Ali i M. Rizwan Mughal. "Reconfigurable magnetorquer for the CubePMT module of CubeSat satellites". W 2012 15th International Multitopic Conference (INMIC). IEEE, 2012. http://dx.doi.org/10.1109/inmic.2012.6511478.

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Purio, Mark Angelo C., Timothy Ivan Leong, Yasir M. O. Abbas, Hoda Awny Elmegharbel, Koju Hiraki i Mengu Cho. "On-board image classification payload for a 3U CubeSat using machine learning for on-orbit cloud detection". W Symposium on Space Educational Activities (SSAE). Universitat Politècnica de Catalunya, 2022. http://dx.doi.org/10.5821/conference-9788419184405.112.

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CubeSats are giving the opportunity for educational institutes to participate in the space industry, develop new technologies and test out new ideas in outer space. CubeSat missions are developed to perform scientific research and demonstrate new space technologies with relatively cheap cost and limited resources. This category of satellites has many limitations such as the short development time, the power consumption and the limited time and capability of data downlink. Earth Observation from a Low Earth Orbit is one of the most appealing m applications of CubeSats developed by students or non-space faring countries. Investigating new technologies to improve image quality and studying ways to increase acquisition adequacy is very promising. This paper aims to introduce a mission hardware design and machine learning-based algorithm used within an Earth Observation (EO) CubeSat. The case study of this paper is Alainsat-1 project which is a 3U CubeSat developed with the support of IEEE Geo-science and Remote Sensing Society (GRSS) at the National Space Science and Technology Center, UAE. The satellite is planned to be launched by 2022. A low-resolution Commercial off-the-shelf (COTS) camera for EO is developed as a primary mission in this CubeSat. The compatible hardware design and software algorithm proposed is responsible for classifying the images captured by the camera into different categories based on cloud intensity detected in these images before downloading them to the ground station. A microcontroller-based architecture is developed for controlling the mission board; it is responsible for accessing the memory, reading the images, and running the cloud detection algorithm. The cloud detection algorithm is based on a U-net architecture while the algorithm is developed using a Tensor-flow library. This model is trained using a dataset of images taken from the Landsat 8 satellite project. Moreover, the SPARCS cloud assessment dataset is used to evaluate the developed model on a new set of images. The overall accuracy achieved by the model is around 85% in addition to the acceptable performance of the model observed on a set of low-resolution images. The plan is to make the design modular and optimize its performance to be used on-board CubeSats fulfilling the size constraint and overall power consumption limitation of an add-on module to a camera mission.

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"CubeSat Technical Aspects". W 55th International Astronautical Congress of the International Astronautical Federation, the International Academy of Astronautics, and the International Institute of Space Law. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.iac-04-p.5.b.07.

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Kinoshita, Nobuaki, Satoshi Okino, Kazumasa Sase, Shigeki Uchiyama, Sotaro Hashiguchi, Hisayuki Nakatsuji, Masahiro Yanagisawa i in. "Development of CubeSat". W 56th International Astronautical Congress of the International Astronautical Federation, the International Academy of Astronautics, and the International Institute of Space Law. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2005. http://dx.doi.org/10.2514/6.iac-05-b5.6.a.05.

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Przybyła, Rafał, Przemyslaw Kryczka i Edyta Dziemińska. "CubeSat: student satellite". W SPIE Proceedings, redaktor Ryszard S. Romaniuk. SPIE, 2006. http://dx.doi.org/10.1117/12.675033.

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Raporty organizacyjne na temat "CubeSat"

de Vries, Wim. Cubesat Drag Calculations. Office of Scientific and Technical Information (OSTI), sierpień 2010. http://dx.doi.org/10.2172/1124870.

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Shiroma, Wayne A., Larry K. Martin, Nicholas G. Fisher, Windell H. Jones, John G. Furumo, Jr Ah Heong, Umeda James R. i Monica M. Ho' oponopono: A Radar Calibration CubeSat. Fort Belvoir, VA: Defense Technical Information Center, październik 2011. http://dx.doi.org/10.21236/ada564129.

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Rossberg, Felix. Structural Design of a NPS CubeSat Launcher. Fort Belvoir, VA: Defense Technical Information Center, styczeń 2008. http://dx.doi.org/10.21236/ada490976.

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Akins, Alexander Brooks. Payload Communications Interface for CubeSat Platform: Design Review. Office of Scientific and Technical Information (OSTI), sierpień 2015. http://dx.doi.org/10.2172/1209454.

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Nathan Jerred, Troy Howe, Adarsh Rajguru i Dr. Steven Howe. DUAL-MODE PROPULSION SYSTEM ENABLING CUBESAT EXPLORATION OF THE SOLAR SYSTEM NASA Innovative Advanced Concepts (NIAC) Phase I Final Report. Office of Scientific and Technical Information (OSTI), czerwiec 2014. http://dx.doi.org/10.2172/1134415.

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Mastrogiannis, Evangelos. Theoretical and Experimental Validation of a CubeSat's L-Band Communication System. Portland State University Library, styczeń 2000. http://dx.doi.org/10.15760/etd.7438.

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Souza, P. Ultrasonic Time-of-Flight Measurements on Binary U-6Nb Cubes. Office of Scientific and Technical Information (OSTI), grudzień 2004. http://dx.doi.org/10.2172/15016861.

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Ledbetter, W. B., Matti Relis i Robert Denson. Feasibility of Producing Large-Sized, High-Strength Motor & Concrete Cubes. Fort Belvoir, VA: Defense Technical Information Center, styczeń 1986. http://dx.doi.org/10.21236/ada167993.

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Farber, Steven. Connecting People to Places: Spatiotemporal Analysis of Transit Supply Using Travel-Time Cubes. Portland State University Library, czerwiec 2016. http://dx.doi.org/10.15760/trec.143.

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Hoover, Donald R. Deriving and Applying Improved Upper Bounds for Multivariate Normal Probability Outside of N-Cubes. Fort Belvoir, VA: Defense Technical Information Center, lipiec 1988. http://dx.doi.org/10.21236/ada198193.

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