Relevant bibliographies by topics / CubeSat

Contents

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

Academic literature on the topic 'CubeSat'

Author: Grafiati
Published: 4 June 2021
Last updated: 7 July 2025

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Journal articles on the topic "CubeSat"

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De Leon, Michael B., Ulysses B. Ante, Madelene S. Velasco, Arvin Oliver S. Ng, Joseph Alfred V. Garcia, Fred P. Liza, Rigoberto C. Advincula, and John Ryan C. Dizon. "3D-Printing for Cube Satellites (CubeSats): Philippines‘ Perspectives." Engineering Innovations 1 (March 25, 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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Xu, Duo, Honghao Yue, Yong Zhao, Fei Yang, Jun Wu, Xueting Pan, Tao Tang, and Yuhao Zhang. "Improved A* Algorithm for Path Planning Based on CubeSats In-Orbit Electromagnetic Transfer System." Aerospace 11, no. 5 (May 15, 2024): 394. http://dx.doi.org/10.3390/aerospace11050394.

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For future large-scale CubeSat applications in orbit, the deployer must accommodate a greater number of CubeSats and facilitate cluster releases. This paper introduces an improved A* algorithm tailored for CubeSat in-orbit transfer path planning. Unlike the traditional A* algorithm, this enhanced version incorporates a path coordination strategy to manage congestion caused by the simultaneous transfer of many CubeSats, ensuring they reach their designated release positions smoothly and thus significantly boosting the efficiency of CubeSat transfers. Additionally, the algorithm develops a cost model for attitude disturbances on the electromagnetic conveying platform and crafts an improved cost function. It strategically balances the reduction in attitude disturbances caused by CubeSat transfers with the efficiency of these transfers. The primary goal is to minimize platform disturbances while optimizing the number of steps CubeSats need to reach their intended positions. The effectiveness of this algorithm is demonstrated through detailed case studies, which confirm that during the CubeSat transfer process, the platform’s attitude remains stable, and the transfer efficiency is well-managed, achieving efficient path planning for the in-orbit transfer of numerous CubeSats.
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Şanlı, Alper, Tuncay Yunus Erkeç, Melih Beceren, and Mehmet Furkan Kemallı. "Architecture of Stratosphere Rocket for Cubesats." Volume 04 Issue 01 vm04, is01 (June 28, 2023): 14–22. http://dx.doi.org/10.23890/ijast.vm04is01.0102.

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Cubesat missions are evolving, and because of their high efficiency, they are becoming more common. Cubesats can go to space more easily because of their compact size. Launch vehicles provide great opportunity for us to reach space and high altitudes of the atmosphere. Today, cubesats are launched to high altitudes for experimental purposes with the help of launch vehicles. In this investigation, a novel launch vehicle was created to match the cubesat's specifications. A stable launch vehicle that can take a cubesat the size of 3U to the stratospheric layer has undergone its first design and examination. Flight simulations were carried out by researching the design stages considered in the launch vehicle. The first design of the launch vehicle suitable for the desired task was made and the altitude, stability and drag analyzes that this design could reach were carried out. The design stages and analysis results of the launch vehicle that will deliver the cubesat to the stratosphere layer are shared. In this study, a design exercise for a stratospheric rocket is proposed. Future research will examine the launch vehicle that will cross the space boundary, known as the Kármán line.
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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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Alanazi, Abdulaziz, and Jeremy Straub. "Engineering Methodology for Student-Driven CubeSats." Aerospace 6, no. 5 (May 13, 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, and Ladislau Matekovits. "A Survey on CubeSat Missions and Their Antenna Designs." Electronics 11, no. 13 (June 27, 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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O O, Afolabi, Adediji A. T, Ewetumo T, and Adedayo K. D. "A Survey of Locally Available Subsystems for Cubesat Projects in Nigerian Market." IOSR Journal of Applied Physics 16, no. 6 (December 2024): 22–26. https://doi.org/10.9790/4861-1606012226.

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There are quite a lot of cube sat subsystems that can be procured on the African continent to develop Cube Satellite (CubeSats). However these are not noticed by many relevant professionals that can design and integrate them to functional CubeSats in Nigeria.frican countries And other This is despite the ever increasing role this class of satellite is playing in educational, scientific research and commercial satellite weather, earth observation and communication services. The paper also identified basic physics principles and mathematical models for the prediction of the attitude of a spacecraft and the units that makes up the CubeSat. The thrust of this paper is to explore and bring to fore these vital subsystems, their uses and configuration for CubeSat project with a view of encouraging increased research activities in CubeSat development, with some information on their power requirements, typical cost, sources, their interrelationship and combination to perform the task of a weather monitoring CubeSat.
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Villela, Thyrso, Cesar A. Costa, Alessandra M. Brandão, Fernando T. Bueno, and Rodrigo Leonardi. "Towards the Thousandth CubeSat: A Statistical Overview." International Journal of Aerospace Engineering 2019 (January 10, 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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Sri, Ram Deepak Akella, and Srinivas Baswanth Pappula Sashendra. "Advancements in CubeSat development: Applications and structural analysis." i-manager's Journal on Structural Engineering 13, no. 2 (2024): 13. https://doi.org/10.26634/jste.13.2.21618.

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This paper explores the development, applications, and structural analysis of CubeSats, small standardized satellites that have revolutionized space missions through their affordability and versatility. Initiated by professors Jordi Puig-Suari and Bob Twiggs in 1999, CubeSats were designed for educational and research purposes, enabling the testing of space technologies in low Earth orbit (LEO). Initially dominated by academic institutions, CubeSat launches saw significant growth from commercial and amateur sectors by 2014. CubeSats have expanded from LEO operations to interplanetary missions, demonstrating their adaptability for remote sensing, communications, and scientific research. This literature review highlights CubeSat advancements, emphasizing their standardized 1U, 2U, and 3U configurations, each with distinct capabilities and challenges. Structural analysis using materials like aluminum alloy, titanium alloy, FR-4, and stainless-steel focuses on their performance under static and dynamic loads. Modal and structural analyses reveal that materials such as aluminum alloy and stainless-steel offer high performance, with significant implications for optimizing CubeSat designs. The findings underscore CubeSats' potential for enhancing Space science education, supporting technology development, and fostering space exploration in both developed and emerging nations.
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Dissertations / Theses on the topic "CubeSat"

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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.<br>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.<br>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.<br>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.<br>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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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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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.<br>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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Books on the topic "CubeSat"

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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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Italy) IAA Conference on University Satellite Missions and CubeSat Workshop (4th 2017 Rome. Fourth IAA Conference on University Satellite Missions and CubeSat Workshop 2017: Proceedings of the 4th International Academy of Astronautics Conference on University Satellite Missions and CubeSat Workshop, held December 4-7, 2017, Rome, Italy. Edited by Graziani Filippo editor, International Academy of Astronautics, and American Astronautical Society. San Diego, California: published for the American Astronautical Society by Univelt, Incorporated, 2018.

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

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1922-, Hemmings Ray, and Leapfrogs Limited, eds. Cubes. Diss: Leapfrogs, 1986.

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

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

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

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

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

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Book chapters on the topic "CubeSat"

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Elsayed, Mohamed Maher, Amir Ashraf, Ahmed Farag, and G. M. Abdo. "Thermal Analysis of an Educational Nano Satellite." In Springer Proceedings in Physics, 210–20. Singapore: Springer Nature Singapore, 2025. https://doi.org/10.1007/978-981-96-3276-3_15.

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Abstract CubeSats, being small satellites used for educational and scientific purposes, face significant thermal management challenges due to their compact size. This research paper focuses on conducting a thermal analysis of a 1U educational nanosatellite (CubeSat) utilizing Thermal Desktop and SINDA/FLUINT software. The study involves the development of a detailed 3D thermal model of the CubeSat using Thermal Desktop software, followed by thermal simulations using SINDA/FLUINT software. By evaluating the CubeSat's thermal performance under various operating conditions, the analysis aims to identify potential thermal issues that may arise. The results gained offer significant understanding of the CubeSat's thermal behavior and suggest ways to improve the design for increased dependability and performance. This research contributes to the understanding of CubeSat thermal management and facilitates the development of improved design strategies for effective thermal control. By addressing thermal challenges, CubeSats can achieve enhanced performance and ensure the success of educational and scientific missions. The results of the thermal investigation show that every CubeSat component is functioning within allowable temperature ranges, meeting an essential requirement for any space mission to be successful. By offering a framework for the creation of better design techniques for efficient thermal control, this study advances the subject of CubeSat thermal management.
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Welle, Richard P. "Overview of CubeSat Technology." In 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." In 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." In 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, and Peter Chapin. "A SPARK/Ada CubeSat Control Program." In 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, and Todd Rose. "CubeSat-Scale High-Speed Laser Downlinks." In 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, and John Bellardo. "HeL1oNano: The first CubeSat to L1?" In 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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Alqam, Muna, and Samir Al-Busaidi. "Controlling Robot Through Satellite: Telesurgery or Remote Surgery." In Springer Proceedings in Physics, 255–65. Singapore: Springer Nature Singapore, 2025. https://doi.org/10.1007/978-981-96-3276-3_19.

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Abstract Remote surgery is a promising medical technology that has the potential to revolutionize healthcare with the potential to provide life-saving care to patients in remote areas. However, one of the challenges facing this technology is the time delay associated with data transmission over conventional network infrastructures which makes it difficult to perform delicate procedures. CubeSats are a type of small satellite that can be used to overcome this challenge. CubeSats can be used to reduce the time delay by providing a low-cost, high-bandwidth communication link between the surgeon and the patient. In this report, we present the design and simulation using General Mission Analysis Tool (GMAT) software of a CubeSat constellation for 7 h remote surgery connecting two hospitals, Sultan Qaboos University Hospital (SQUH) in Sultanate of Oman and OSF children hospital in Illinois USA. We discuss the orbital design of the constellation to ensure that the satellites are always in view of both hospitals. The constellation must be designed to provide continuous coverage of the two hospitals, even as Earth rotates, as well as the challenges and solutions associated with this application.
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Speretta, Stefano, Angelo Cervone, Prem Sundaramoorthy, Ron Noomen, Samiksha Mestry, Ana Cipriano, Francesco Topputo, et al. "LUMIO: An Autonomous CubeSat for Lunar Exploration." In 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., and D. R. Jarkey. "Cubesat Material Limits for Design for Demise." In 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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Conference papers on the topic "CubeSat"

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deLoughery, Tyler J., Clayton D. Lauzon, Kyle H. Sims, John Weber, Wahab Almuhtadi, and Ross Cheriton. "CubeSat Astrophotonics: Lower cost, space-based optical astronomy using photonic integrated circuits." In Integrated Photonics Research, Silicon and Nanophotonics, IW3B.4. Washington, D.C.: Optica Publishing Group, 2024. http://dx.doi.org/10.1364/iprsn.2024.iw3b.4.

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CubeSats are low-cost, space-based platforms for sensing instrumentation, where limits on size, weight and power limitations favour using photonic integrated circuit. We explore the design and performance of a proof-of-concept astrophotonic CubeSat for optical astronomy.
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Rose, Todd S., Ariel Berman, Nicolette Werner, John Swigert, Eric McDonald, Sara Lampen, Stephanie Rodriguez, et al. "CubeSat optical crosslink." In Free-Space Laser Communications XXXVII, edited by Hamid Hemmati and Bryan S. Robinson, 8. SPIE, 2025. https://doi.org/10.1117/12.3046136.

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Skinner, Mark A. "CubeSat Confusion: Further Observations of a CubeSat-Based Pulsed LED Beacon." In 22nd IAA Symposium on Space Debris, Held at the 75th International Astronautical Congress (IAC 2024), 21–31. Paris, France: International Astronautical Federation (IAF), 2024. https://doi.org/10.52202/078360-0004.

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Woo, Hyunwook, Octavio Rico, Simone Chesi, and Marcello Romano. "CubeSat Three Axis Simulator(CubeTAS)." In 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, and Kaarel Repän. "Development and flight results of TalTech University CubeSat mission." In 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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Lombardo, M. "An overview of the ArgoMoon and LICIAcube flight dynamics operations." In Aeronautics and Astronautics. Materials Research Forum LLC, 2023. http://dx.doi.org/10.21741/9781644902813-138.

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Abstract CubeSats are becoming a reliable alternative for low-cost space applications in deep space, as mission companions or as standalone missions. The use of CubeSats in deep space requires to address many operational challenges, particularly those related to navigation. LICIACube and ArgoMoon are the first two 6U CubeSat missions to the outer space funded and managed by the Italian Space Agency, whose spacecrafts have been developed and operated by Argotec. The flight dynamics operations of both missions were performed by the flight dynamics team of the University of Bologna using NASA/JPL’s navigation software MONTE. This paper gives a brief presentation of the flight dynamics operations of ArgoMoon and LICIACube and presents the obtained results highlighting the challenges of cis-lunar and deep space CubeSat navigation as well as the achieved successes.
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Blazquez, E. "Small celestial body exploration with CubeSat Swarms." In Aeronautics and Astronautics. Materials Research Forum LLC, 2023. http://dx.doi.org/10.21741/9781644902813-129.

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Abstract. This work presents a large-scale simulation study investigating the deployment and operation of distributed swarms of CubeSats for interplanetary missions to small celestial bodies. Utilizing Taylor numerical integration and advanced collision detection techniques, we explore the potential of large CubeSat swarms in capturing gravity signals and reconstructing the internal mass distribution of a small celestial body while minimizing risks and Delta V budget. Our results offer insight into the applicability of this approach for future deep space exploration missions.
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Curatolo, A. "A distributed nanosatellite attitude testing laboratory for joint research activities." In Aerospace Science and Engineering. Materials Research Forum LLC, 2023. http://dx.doi.org/10.21741/9781644902677-30.

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Abstract. During the last decades, there has been an increase in the use of satellites of reduced dimensions. Among the others, microsatellites (mass from 11 to 200 kg) and nanosatellites (1 to 10 kg) have been the ones receiving increasing interest from Universities for educational activities [1], [2]. Their reduced cost, complexity and developing time compared to larger satellites make them particularly suitable for student projects. In this regard CubeSats (satellites of standardised dimensions, based on 1 unit, 10x10x10 cm) were developed at Caltech with the goal of having a low cost and fast to be developed satellite [3]. The CubeSat form factor has then been widely used also for scientific and commercial space missions [4]. Alongside the development of nanosatellites, there has been an increase in the need for better CubeSat testing for improving CubeSat reliability [5]. As reported in an extensive study on 855 CubeSats [4], at the year 2018 almost 25% of CubeSats missions failed in their early life stage (infant mortality). One of the subsystems more difficult to be tested is the Attitude Determination and Control System (ADCS). This subsystem includes sensors for attitude determination, actuators for attitude control and an onboard controller. Integrated subsystem testing is a challenging task since the device under test should freely rotate under low torque conditions and sensors/actuators should be stimulated. A common way to provide a free rotational environment is to use an air bearing table [6].
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Eschelmüller, V., A. Stren, M. Issa, J. Bauer, A. Goswami, E. Vitztum, K. Repän, W. Treberspurg, and C. Scharlemann. "Development of a CubeSat CLIMBing to the Van-Allen belt." In 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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Watson, Erkai, Nathanaël Durr, Jose-Luis Sandoval Murillo, Markus Büttner, and Pascal Matura. "Simulating Hypervelocity Impacts on Cfrp with a Discrete Element Approach." In 2022 16th Hypervelocity Impact Symposium. American Society of Mechanical Engineers, 2022. http://dx.doi.org/10.1115/hvis2022-57.

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Abstract Numerical simulations provide a powerful tool for investigating satellite breakups resulting from hypervelocity impact, and a discrete element simulation method has been shown to be well suited to model the fragmentation that materials undergo upon impact at high velocities. In this paper, we describe new developments to a discrete element simulation method to allow the modeling of orthotropic materials, specifically carbon fiber reinforced polymers which are commonly used in modern satellites. We model carbon fiber reinforced polymers by using different parameters for fiber and matrix materials in our discrete model. We calibrate our carbon fiber reinforced polymer model’s two free parameters with experimental hypervelocity impact data from literature. Finally, we demonstrate the numerical method’s applicability to simulate the satellite breakups with two simulations: a non-catastrophic sphere-CubeSat impact and a catastrophic CubeSat-CubeSat impact. We compare these scenarios, using aluminum and carbon fiber reinforced polymer CubeSats, to fragment size distributions predicted by the NASA standard satellite breakup model.
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Reports on the topic "CubeSat"

1

de Vries, Wim. Cubesat Drag Calculations. Office of Scientific and Technical Information (OSTI), August 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., and Monica M. Ho' oponopono: A Radar Calibration CubeSat. Fort Belvoir, VA: Defense Technical Information Center, October 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, January 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), August 2015. http://dx.doi.org/10.2172/1209454.

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Belian, Olivia, and Rachel Jones. CubeSat Interplanetary Exploration: A Deep Dive into Nuclear Propulsion and Astrodynamics for Small Satellites. Office of Scientific and Technical Information (OSTI), August 2024. http://dx.doi.org/10.2172/2426290.

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Nathan Jerred, Troy Howe, Adarsh Rajguru, and 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), June 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, January 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), December 2004. http://dx.doi.org/10.2172/15016861.

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Ledbetter, W. B., Matti Relis, and Robert Denson. Feasibility of Producing Large-Sized, High-Strength Motor & Concrete Cubes. Fort Belvoir, VA: Defense Technical Information Center, January 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, June 2016. http://dx.doi.org/10.15760/trec.143.

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