Relevant bibliographies by topics / Cubesat development

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers

Academic literature on the topic 'Cubesat development'

Author: Grafiati
Published: 4 June 2021
Last updated: 6 February 2022

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Journal articles on the topic "Cubesat development"

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Menchinelli, Alessandro, Francesca Ingiosi, Ludovico Pamphili, Paolo Marzioli, Riccardo Patriarca, Francesco Costantino, and Fabrizio Piergentili. "A Reliability Engineering Approach for Managing Risks in CubeSats." Aerospace 5, no. 4 (November 15, 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, and Robert Ryk van Zyl. "Practical electromagnetic compatibility studies of a CubeSat." Journal of Engineering, Design and Technology 14, no. 4 (October 3, 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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SHIMAZU, Ryuya, Yusuke CHIBA, Hiroka KANEI, Hiroki WATARI, Ikuma NISHIKAWA, and Toshihiro KAMEDA. "D03 Development of CubeSat "YUI"." Proceedings of the Space Engineering Conference 2013.22 (2013): _D03–1_—_D03–5_. http://dx.doi.org/10.1299/jsmesec.2013.22._d03-1_.

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Carrara, Valdemir, Rafael Barbosa Januzi, Daniel Hideaki Makita, Luis Felipe de Paula Santos, and Lidia Shibuya Sato. "The ITASAT CubeSat Development and Design." Journal of Aerospace Technology and Management 9, no. 2 (April 24, 2017): 147–56. http://dx.doi.org/10.5028/jatm.v9i2.614.

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Lai, Peter C., David C. Sternberg, Robert J. Haw, Eric D. Gustafson, Phillipe C. Adell, and John D. Baker. "Lunar Flashlight CubeSat GNC system development." Acta Astronautica 173 (August 2020): 425–41. http://dx.doi.org/10.1016/j.actaastro.2020.01.022.

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Musiał, Alicja, Dominik Markowski, Jan Życzkowski, and Krzysztof A. Cyran. "Analysis of Methods for CubeSat Mission Design Based on in-orbit Results of KRAKsat Mission." International Journal of Education and Information Technologies 15 (September 21, 2021): 295–302. http://dx.doi.org/10.46300/9109.2021.15.31.

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The success rate of currently performed CubeSat missions shows that despite their popularity, small satellites are still not as reliable as larger platforms. This research was conducted to analyse in-orbit experience from the KRAKsat mission and discuss methods for mission design and engineering that can increase CubeSats reliability and prevent their failures. The main purpose was to define best practices and rules that should be followed during mission development and operations to ensure its success based on the overview of the lessons learned from KRAKsat and problems encountered during its mission. This paper summarizes the experiences obtained and provides methods that can be used while carrying out future robust CubeSat projects. It was written to prove that there are some parts of the small satellite missions that are often neglected in the university-led projects and, by ensuring proper testing and planning before the actual mission, its reliability can increase. The following analysis could be used as a guide during the development of the next CubeSat projects.
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Chau, Vu Minh, and Hien Bich Vo. "Structural Dynamics Analysis of 3-U CubeSat." Applied Mechanics and Materials 894 (September 2019): 164–70. http://dx.doi.org/10.4028/www.scientific.net/amm.894.164.

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The development of CubeSats has been advanced significantly during the past two decades for both scientific research and industrial purposes. During the manufacturing process, every CubeSat must satisfy various system requirements in which the structural analysis is one of the most vital necessity in order to assure a normal operation of the CubeSat during its working time in space. In the conceptual design phase, structural dynamics is a mandatory step to determine the natural frequencies of individual bodies, the deformation and stress induced at the corresponding vibration modes to prevent structural failure. In this work, IGOSat, a 3-Unit CubeSat, which was developed at the Paris Diderot University is exanimated in term of modal, harmonic response, and random vibration analysis at the time of ground testing as well as the launching phase using ANSYS software. These numerical simulations conducted according to the CubeSat Design Specification and the system requirements of QB50 project. The minimum natural frequency of the CubSat obtained to be 363.17 (Hz), which passed the required frequency of 90 (Hz). Moreover, the Harmonic and Random vibration analyses indicate that the peak response of normal stress, as well as deformation values obtained, are far lesser compared to the yield strength of the frame structure and subsystem materials. Hence, our numerical analysis found that the CubeSat remains intact during the launch environment.
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Filho, Edemar Morsch, Laio Oriel Seman, Cezar Antônio Rigo, Vicente de Paulo Nicolau, Raúl García Ovejero, and Valderi Reis Quietinho Leithardt. "Irradiation Flux Modelling for Thermal–Electrical Simulation of CubeSats: Orbit, Attitude and Radiation Integration." Energies 13, no. 24 (December 18, 2020): 6691. http://dx.doi.org/10.3390/en13246691.

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During satellite development, engineers need to simulate and understand the satellite’s behavior in orbit and minimize failures or inadequate satellite operation. In this sense, one crucial assessment is the irradiance field, which impacts, for example, the power generation through the photovoltaic cells, as well as rules the satellite’s thermal conditions. This good practice is also valid for CubeSat projects. This paper presents a numerical tool to explore typical irradiation scenarios for CubeSat missions by combining state-of-the-art models. Such a tool can provide the input estimation for software and hardware in the loop analysis for a given initial condition and predict it along with the satellite’s lifespan. Three main models will be considered to estimate the irradiation flux over a CubeSat, namely an orbit, an attitude, and a radiation source model, including solar, albedo, and infrared emitted by the Earth. A case study illustrating the tool’s abilities is presented for a typical CubeSats’ two-line element set (TLE) and five attitudes. Finally, a possible application of the tool as an input to a CubeSat task-scheduling is introduced. The results show that the complete model’s use has considerable differences from the simplified models sometimes used in the literature.
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Cho, Dong-Hyun, Won-Sub Choi, Min-Ki Kim, Jin-Hyung Kim, Eunsup Sim, and Hae-Dong Kim. "High-Resolution Image and Video CubeSat (HiREV): Development of Space Technology Test Platform Using a Low-Cost CubeSat Platform." International Journal of Aerospace Engineering 2019 (May 23, 2019): 1–17. http://dx.doi.org/10.1155/2019/8916416.

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In this paper, we present high-resolution image and video CubeSat (HiREV), the first constructed 6 U platform to reach the space technology test bed stage, developed by the Korea Aerospace Research Institute (KARI). The CubeSat system is a low-cost platform that has been widely applied to various space missions, from missions involving earth observation to deep space. Despite the emergence of the CubeSat technology worldwide, the CubeSat market in Korea is still in the beginning stages, and a standard testing platform is also in demand. For this reason, KARI is starting to develop a 6 U CubeSat platform, which includes a less than 3 U bus system and greater than 3 U payload space. HiREV has been developed with locally manufactured parts, creating a domestic commercial off-the-shelf infrastructure for CubeSat and 3 m resolution camera payload development. Core flight software has also been applied as an on-board flight software system. Presently, we have developed the main system, while HiREV is under space environmental testing.
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Pagano, Thomas S., Carlo Abesamis, Andres Andrade, Hartmut Aumann, Sarath Gunapala, Cate Heneghan, Robert Jarnot, et al. "CubeSat Infrared Atmospheric Sounder technology development status." Journal of Applied Remote Sensing 13, no. 03 (September 24, 2019): 1. http://dx.doi.org/10.1117/1.jrs.13.032512.

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Dissertations / Theses on the topic "Cubesat development"

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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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Cheney, Liam Jon. "Development of Safety Standards for CubeSat Propulsion Systems." DigitalCommons@CalPoly, 2014. https://digitalcommons.calpoly.edu/theses/1180.

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The CubeSat community has begun to develop and implement propulsion systems. This movement represents a new capability which may satisfy mission needs such as orbital and constellation maintenance, formation flight, de-orbit, and even interplanetary travel. With the freedom and capability granted by propulsion systems, CubeSat providers must accept new responsibilities in proportion to the potential hazards that propulsion systems may present. The Cal Poly CubeSat program publishes and maintains the CubeSat Design Specification (CDS). They wish to help the CubeSat community to safety and responsibly expand its capabilities to include propulsive designs. For this reason, the author embarked on the task of developing a draft of safety standards CubeSat propulsion systems. Wherever possible, the standards are based on existing documents. The author provides an overview of certain concepts in systems safety with respect to the classification of hazards, determination of required fault tolerances, and the use of inhibits to satisfy fault tolerance requirements. The author discusses hazards that could exist during ground operations and through launch with respect to hazardous materials and pressure systems. Most of the standards related to Range Safety are drawn from AFSPCMAN 91-710. Having reviewed a range of hypothetical propulsion system architectures with an engineer from Range Safety at Vandenberg Air Force Base, the author compiled a case study. The author discusses many aspects of orbital safety. The author discusses the risk of collision with the host vehicle and with third party satellites along with the trackability of CubeSats using propulsion systems. Some recommendations are given for working with the Joint Functional Component Command for Space (JFCC SPACE), thanks to the input of two engineers who work with the Joint Space Operations Center (JSpOC). Command Security is discussed as an important aspect of a mission which implements a propulsion system. The author also discusses End-of-Life procedures such as safing and de-orbit operations. The orbital safety standards are intended to promote “good citizenship.” The author steps through each proposed standard and offers justification. The author is confident that these standards will set the stage for a dialogue in the CubeSat community which will lead to the formulation of a reasonable and comprehensive set of standards. The author hopes that the discussions given throughout this document will help CubeSat developers to visualize the path to flight readiness so that they can get started on the right foot.
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Lumbwe, Lwabanji Tony. "Development of an onboard computer (OBC) for a CubeSat." Thesis, Cape Peninsula University of Technology, 2013. http://hdl.handle.net/20.500.11838/1172.

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Over the past decade, the satellite industry has witnessed the birth and evolution of the CubeSat standard, not only as a technology demonstrator tool but also as a human capacity development platform in universities. The use of commercial off the shelf (COTS) hardware components makes the CubeSat a cost effective and ideal solution to gain access to space in terms of budget and integration time for experimental science payloads. Satellite operations are autonomous and are essentially based on the interaction of interconnected electronic subsystems exchanging data according to the mission requirements and objectives. The onboard computer (OBC) subsystem is developed around a microcontroller and plays an essential role in this exchange process as it performs all the computing tasks and organises the collection of onboard housekeeping and payload data before downlink during an overpass above the ground station. The thesis here presented describes the process involved in the development, design and implementation of a prototype OBC for a CubeSat. An investigation covering previously developed CubeSat OBCs is conducted with emphasis on the characteristics and features of the microcontroller to be used in the design and implementation phases. A set of hardware requirements are defined and according to the current evolution on the microcontroller market, preference is given to the 32-bit core architecture over both its 8-bit and 16-bit counterparts. Following a well defined selection process, Atmel’s AT91SAM3U4E microcontroller which implements a 32-bit Cortex-M3 core is chosen and an OBC architecture is developed around it. Further, the proposed architecture is implemented as a prototype on a printed circuit board (PCB), presenting a set of peripherals necessary for the operation of the OBC. Finally, a series of tests successfully conducted on some of the peripherals are used to evaluate the proposed architecture.
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Zohar, Guy G. "AD-HOC REGIONAL COVERAGE CONSTELLATIONS OF CUBESATS USING SECONDARY LAUNCHES." DigitalCommons@CalPoly, 2013. https://digitalcommons.calpoly.edu/theses/927.

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As development of CubeSat based architectures increase, methods of deploying constellations of CubeSats are required to increase functionality of future systems. Given their low cost and quickly increasing launch opportunities, large numbers of CubeSats can easily be developed and deployed in orbit. However, as secondary payloads, CubeSats are severely limited in their options for deployment into appropriate constellation geometries. This thesis examines the current methods for deploying cubes and proposes new and efficient geometries using secondary launch opportunities. Due to the current deployment hardware architecture, only the use of different launch opportunities, deployment direction, and deployment timing for individual cubes in a single launch are explored. The deployed constellations are examined for equal separation of Cubes in a single plane and effectiveness of ground coverage of two regions. The regions examined are a large near-equatorial zone and a medium sized high latitude, high population density zone. Results indicate that simple deployment strategies can be utilized to provide significant CubeSat dispersion to create efficient constellation geometries. The same deployment strategies can be used to develop a multitude of differently dispersed constellations. Different launch opportunities can be utilized to tailor a constellation for a specific region or mission objective. Constellations can also be augmented using multiple launch opportunities to optimize a constellation towards a specific mission or region. The tools developed to obtain these results can also be used to perform specific analysis on any region in order to optimize future constellations for other applications.
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Royo, Serrano Daniel. "Development of a calibration procedure for gyroscopes in CubeSat missions." Thesis, Luleå tekniska universitet, Rymdteknik, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-83278.

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Persson, Marcus. "Software Development and Qualification Testing of a CubeSat X-ray Monitor." Thesis, Luleå tekniska universitet, Institutionen för system- och rymdteknik, 2019. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-76843.

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The CUBES (CUbesat x-ray Background Explorer using Scintillators) is a payload on the KTH student satellite MIST (MIniature STudent satellite) to evaluate Silicon Photo-multiplier technology and new scintillators such as GAGG (Gadolinium Aluminium Gallium Garnet, Gd3Al2Ga3O12) for future use in hard X-ray polarisation studies of Gamma-Ray Bursts. CUBES itself is designed to study the MIST in-orbit radiation environment by using a detector which is comprised of a silicon photomultiplier coupled to different scintillator materials. Three of these detectors will be mounted on the payload platform and then coupled to inputs of an Application Specific Integrated Circuit (ASIC) and connected to a Field-programmable Gate Array (FPGA) which will store and send data through the downlink on the MIST satellite to ground. This thesis covers the software development for the FPGA, together with two radiation tests of components and the preparation of these.
CUBES
MIST
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Botma, Pieter Johannes. "The design and development of an ADCS OBC for a CubeSat." Thesis, Stellenbosch : Stellenbosch University, 2011. http://hdl.handle.net/10019.1/18040.

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Thesis (MScEng)--Stellenbosch University, 2011.
ENGLISH ABSTRACT: The Electronic Systems Laboratory at Stellenbosch University is currently developing a fully 3-axis controlled Attitude Determination and Control Subsystem (ADCS) for CubeSats. This thesis describes the design and development of an Onboard Computer (OBC) suitable for ADCS application. A separate dedicated OBC for ADCS purposes allows the main CubeSat OBC to focus only on command and data handling, communication and payload management. This thesis describes, in detail the development process of the OBC. Multiple Microcontroller Unit (MCU) architectures were considered before selecting an ARM Cortex-M3 processor due to its performance, power efficiency and functionality. The hardware was designed to be as robust as possible, because radiation tolerant and redundant components could not be included, due to their high cost and the technical constraints of a CubeSat. The software was developed to improve recovery from lockouts or component failures and to enable the operational modes to be configured in real-time or uploaded from the ground station. Ground tests indicated that the OBC can handle radiation-related problems such as latchups and bit-flips. The peak power consumption is around 500 mW and the orbital average is substantially lower. The proposed OBC is therefore not only sufficient in its intended application as an ADCS OBC, but could also stand in as a backup for the main OBC in case of an emergency.
AFRIKAANSE OPSOMMING: Die Elektroniese Stelsels Laboratorium by die Universiteit van Stellenbosch is tans besig om ’n volkome 3-as gestabiliseerde oriëntasiebepaling en -beheerstelsel (Engels: ADCS) vir ’n CubeSat te ontwikkel. Hierdie tesis beskryf die ontwerp en ontwikkeling van ’n aanboordrekenaar (Engels: OBC) wat gebruik kan word in ’n ADCS. ’n Afsonderlike OBC wat aan die ADCS toegewy is, stel die hoof-OBC in staat om te fokus op beheer- en datahantering, kommunikasie en loonvragbestuur. Hierdie tesis beskryf breedvoerig die werkswyse waarvolgens die OBC ontwikkel is. Verskeie mikroverwerkers is as moontlike kandidate ondersoek voor daar op ’n ARM Cortex-M3-gebaseerde mikroverwerker besluit is. Hierdie mikroverwerker is gekies vanweë sy spoed, effektiewe kragverbruik en funksionaliteit. Die hardeware is ontwikkel om so robuust moontlik te wees, omdat stralingbestande en oortollige komponente weens kostebeperkings, asook tegniese beperkings van ’n CubeSat, nie ingesluit kon word nie. Die programmatuur is ontwikkel om van ’n uitsluiting en ’n komponentfout te kan herstel. Verder kan programme wat tydens vlug in werking is, verstel word en vanaf ’n grondstasie gelaai word. Grondtoetse het aangedui dat die OBC stralingverwante probleme, soos ’n vergrendeling (latchup) of bis-omkering (bit-flip), kan hanteer. Die maksimum kragverbruik is ongeveer 500 mW en die gemiddelde wentelbaankragverbruik is beduidend kleiner. Die voorgestelde OBC is dus voldoende as ADCS OBC asook hoof-OBC in geval van nood.
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Mey, Philip Hendrik. "Development of attitude controllers and actuators for a solar sail cubesat." Thesis, Stellenbosch : University of Stellenbosch, 2011. http://hdl.handle.net/10019.1/6862.

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Thesis (MScEng (Electrical and Electronic Engineering))--University of Stellenbosch, 2011.
ENGLISH ABSTRACT: CubeSats are small, lightweight satellites which are often used by academic institutions due to their application potential and low cost. Because of their size and weight, less powerful attitude controllers, such as solar sails, can be used. In 2010, the Japanese satellite, Ikaros, was launched to illustrate the usage of solar sails as a propulsion system. Similarly, by exploiting the solar radiation pressure, it is possible to use a solar sail, together with three magnetorquers, to achieve 3-axis attitude control of a 3-unit CubeSat. Simulations are required to demonstrate the attitude control of a sun-synchronous, low Earth orbit CubeSat using a solar sail. To allow the adjustment of the solar sail, and its resulting torque, a mechanical structure is required which can be used to position the sail within two orthogonal axes. Although the magnetorquers and solar sail are sufficient to achieve 3-axis attitude control, the addition of a reaction wheel can be implemented in an attempt to improve this control.
AFRIKAANSE OPSOMMING: CubeSats is klein, ligte satelliete wat dikwels deur universiteite gebruik word weens hul lae koste en groot toepassings potensiaal. As gevolg van hulle gewig en grootte, kan minder kragtige posisie beheerders, soos byvoorbeeld sonseile, gebruik word. Die Japannese satelliet, Ikaros, was in 2010 gelanseer om die gebruik van ’n sonseil as aandrywingstelsel te illustreer. Net so is dit moontlik om die bestraling van die son te gebruik, met behulp van ’n sonseil, en drie magneetstange om 3-as posisiebeheer op ’n 3-eenheid CubeSat te bekom. Simulasies word benodig om die posisie beheer van ’n sonsinkrone, lae-aard wentelbaan CubeSat met ’n sonseil te demonstreer. ’n Meganiese struktuur word benodig vir die posisionering van die sonseil in twee ortogonale asse sodat die sonseil, en dus die geassosieerde draaimoment, verskuif kan word. Alhoewel die magneetstange en sonseil voldoende is om 3-as posisiebeheer te bekom, kan ’n reaksiewiel bygevoeg word om hierdie beheer te probeer verbeter.
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Abel, John Trevor. "Development of a CubeSat Instrument for Microgravity Particle Damper Performance Analysis." DigitalCommons@CalPoly, 2011. https://digitalcommons.calpoly.edu/theses/537.

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Spacecraft pointing accuracy and structural longevity requirements often necessitate auxiliary vibration dissipation mechanisms. However, temperature sensitivity and material degradation limit the effectiveness of traditional damping techniques in space. Robust particle damping technology offers a potential solution, driving the need for microgravity characterization. A 1U cubesat satellite presents a low cost, low risk platform for the acquisition of data needed for this evaluation, but severely restricts available mass, volume, power and bandwidth resources. This paper details the development of an instrument subject to these constraints that is capable of capturing high resolution frequency response measurements of highly nonlinear particle damper dynamics.
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Loubser, Hanco Evert. "The development of Sun and Nadir sensors for a solar sail CubeSat." Thesis, Stellenbosch : University of Stellenbosch, 2011. http://hdl.handle.net/10019.1/6748.

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Thesis (MScEng (Electrical and Electronic Engineering))--University of Stellenbosch, 2011.
ENGLISH ABSTRACT: This thesis describes the development of attitude sensors required for the Attitude Determination and Control System (ADCS) for a Cubesat. The aim is to find the most suitable sensors for use on a small picosatellite by implementing miniaturised sensors with available commercial-off-the-shelf (COTS) technology. Specifically, the algorithms, hardware prototypes, software and filters required to create accurate sensors to determine the 3-axis orientation of a CubeSat are discussed.
AFRIKAANSE OPSOMMING: Hierdie tesis beskryf die ontwikkeling van oriëntasiesensors wat benodig word vir die oriëntasiebepaling en -beheerstelsel (Engels: ADCS) van ’n CubeSat. Die doelwit is om sensors te vind wat die geskikste is om in ’n klein picosatelliet te gebruik, deur miniatuursensors met kommersiële maklik verkrygbare tegnologie (Engels: COTS technology) te implementeer. Daar word in die bespreking veral aandag geskenk aan die algoritmes, hardewareprototipes, programmatuur en filters wat benodig word om akkurate sensors te skep wat op hul beurt 3-as oriëntasie van die CubeSat kan bepaal.
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Books on the topic "Cubesat development"

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Alberto, Ferrari, Russo Marco, and ebrary Inc, eds. Expert cube development with Microsoft SQL Server 2008 Analysis Services: Design and implement fast, scalable, and maintainable cubes. Birmingham, UK: Packt Publishing, 2009.

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Book chapters on the topic "Cubesat development"

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Schoolcraft, Josh, Andrew Klesh, and Thomas Werne. "MarCO: Interplanetary Mission Development on a CubeSat Scale." In 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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Park, Jae-Pil, Sang-Young Park, Young Bum Song, Guk Nam Kim, Kwangwon Lee, Hyungjik Jay Oh, Jin-Chul Yim, et al. "CANYVAL-X Mission Development Using CubeSats." In Space Operations: Contributions from the Global Community, 681–91. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-51941-8_30.

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Patil, R. T., and S. Sokhansanj. "Stress Relaxation Characteristics of Alfalfa Cubes." In Developments in Food Engineering, 84–86. Boston, MA: Springer US, 1994. http://dx.doi.org/10.1007/978-1-4615-2674-2_20.

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Manea, Florin, Mike Müller, and Dirk Nowotka. "The Avoidability of Cubes under Permutations." In Developments in Language Theory, 416–27. Berlin, Heidelberg: Springer Berlin Heidelberg, 2012. http://dx.doi.org/10.1007/978-3-642-31653-1_37.

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Mercaş, Robert, and Aleksi Saarela. "3-Abelian Cubes Are Avoidable on Binary Alphabets." In Developments in Language Theory, 374–83. Berlin, Heidelberg: Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-38771-5_33.

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Lietard, Florian, and Matthieu Rosenfeld. "Avoidability of Additive Cubes over Alphabets of Four Numbers." In Developments in Language Theory, 192–206. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-48516-0_15.

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Rahmat-Samii, Yahya, Vignesh Manohar, and Joshua M. Kovitz. "Novel antenna concepts and developments for CubeSats." In Developments in Antenna Analysis and Design: Volume 2, 361–401. Institution of Engineering and Technology, 2018. http://dx.doi.org/10.1049/sbew543g_ch11.

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Hepp, Aloysius F., Prashant N. Kumta, Oleg I. Velikokhatnyi, and Ryne P. Raffaelle. "Batteries for integrated power and CubeSats: Recent developments and future prospects." In Silicon Anode Systems for Lithium-Ion Batteries, 457–508. Elsevier, 2022. http://dx.doi.org/10.1016/b978-0-12-819660-1.00011-6.

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Zheng, Meiyun, and H. T. Nguyen. "An Efficient Parallel Implementation of the Marching-cubes Algorithm." In Massively Parallel Processing Applications and Development, 903–10. Elsevier, 1994. http://dx.doi.org/10.1016/b978-0-444-81784-6.50108-1.

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Berger, Stefan, and Michael Schrefl. "Federated Data Warehouses." In Complex Data Warehousing and Knowledge Discovery for Advanced Retrieval Development, 82–107. IGI Global, 2010. http://dx.doi.org/10.4018/978-1-60566-748-5.ch005.

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Abstract:
Federated data warehouses are a collection of autonomous and often heterogeneous data marts (DM). When attemping to integrate autonomous DMs, data designers commonly face numerous conflicts that must be repaired. This chapter analyzes and classifies the conflicts at the schema and instance level among dimensions and cubes in a systematic way, based on a formal data model. It shows the dependencies between dimension and cube integration and presents a methodological DM integration approach. A running example demonstrates how to repair the various heterogeneities. Moreover, the chapter introduces a federated DW reference architecture enabling tightly coupled integration of autonomous DMs.
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Conference papers on the topic "Cubesat development"

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Kinoshita, Nobuaki, Satoshi Okino, Kazumasa Sase, Shigeki Uchiyama, Sotaro Hashiguchi, Hisayuki Nakatsuji, Masahiro Yanagisawa, et al. "Development of CubeSat." In 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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Aslan, A. R., H. B. Yagci, M. E. Umit, A. Sofyali, M. E. Bas, M. S. Uludag, O. E. Ozen, et al. "Development of a LEO communication CubeSat." In 2013 6th International Conference on Recent Advances in Space Technologies (RAST). IEEE, 2013. http://dx.doi.org/10.1109/rast.2013.6581288.

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Ball, Christopher, Chi-Chih Chen, Andrew O'Brien, Graeme Smith, Christa McKelvey, Mark Andrews, J. Landon Garry, et al. "Development of the cubesat radiometer radio frequency interference technology validation (cuberrt) system." In 2017 IEEE International Geoscience and Remote Sensing Symposium (IGARSS). IEEE, 2017. http://dx.doi.org/10.1109/igarss.2017.8128362.

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Pottinger, Sabrina, David Krejci, and Carsten Scharlemann. "Development of a µPPT for CubeSat Applications." In 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-4532.

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Lan, Wenschel, Jonathan Brown, Armen Toorian, Roland Coelbo, Lori Brooks, Jordi Puig-Suari, and Robert Twiggs. "CubeSat Development in Education and into Industry." In Space 2006. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-7296.

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Samson, J. R. "Update on Dependable Multiprocessor CubeSat technology development." In 2012 IEEE Aerospace Conference. IEEE, 2012. http://dx.doi.org/10.1109/aero.2012.6187238.

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Polly, Colston, Peter Rockhold, Tae W. Lim, Tyler Dickenson, and Rachel Griffin. "Trade Studies for Cubesat Optical Communication Payload Development." In AIAA SPACE 2016. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2016. http://dx.doi.org/10.2514/6.2016-5562.

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Lim, Boon, Michael Shearn, Douglas Dawson, Chaitali Parashare, Andrew Romero-Wolf, Damon Russell, and Joel Steinkraus. "Development of the Radiometer Atmospheric CubeSat Experiment payload." In IGARSS 2013 - 2013 IEEE International Geoscience and Remote Sensing Symposium. IEEE, 2013. http://dx.doi.org/10.1109/igarss.2013.6721292.

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Schoolcraft, Joshua, Andrew T. Klesh, and Thomas Werne. "MarCO: Interplanetary Mission Development On a CubeSat Scale." In SpaceOps 2016 Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2016. http://dx.doi.org/10.2514/6.2016-2491.

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Kurochkin, V., A. Abrikosov, M. Balanov, S. Vorobey, A. Khmelev, and Y. Kurochkin. "Development of Cubesat For Quantum and Classical Communication." In Advanced Solid State Lasers. Washington, D.C.: OSA, 2019. http://dx.doi.org/10.1364/assl.2019.jtu3a.54.

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