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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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Meftah, Mustapha, Fabrice Boust, Philippe Keckhut, Alain Sarkissian, Thomas Boutéraon, Slimane Bekki, Luc Damé, et al. "INSPIRE-SAT 7, a Second CubeSat to Measure the Earth’s Energy Budget and to Probe the Ionosphere." Remote Sensing 14, no. 1 (January 1, 2022): 186. http://dx.doi.org/10.3390/rs14010186.
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INSPIRE-SAT 7 is a French 2-Unit CubeSat (11.5 × 11.5 × 22.7 cm) primarily designed for Earth and Sun observation. INSPIRE-SAT 7 is one of the missions of the International Satellite Program in Research and Education (INSPIRE). Twice the size of a 4 × 4 Rubik’s Cube and weighing about 3 kg, INSPIRE-SAT 7 will be deployed in Low Earth Orbit (LEO) in 2023 to join its sister satellite, UVSQ-SAT. INSPIRE-SAT 7 represents one of the in-orbit demonstrators needed to test how two Earth observation CubeSats in orbit can be utilized to set up a satellite constellation. This new scientific and technological pathfinder CubeSat mission (INSPIRE-SAT 7) uses a multitude of miniaturized sensors on all sides of the CubeSat to measure the Earth’s energy budget components at the top-of-the-atmosphere for climate change studies. INSPIRE-SAT 7 contains also a High-Frequency (HF) payload that will receive HF signals from a ground-based HF transmitter to probe the ionosphere for space weather studies. Finally, this CubeSat is equipped with several technological demonstrators (total solar irradiance sensors, UV sensors to measure solar spectral irradiance, a new Light Fidelity (Li-Fi) wireless communication system, a new versatile telecommunication system suitable for CubeSat). After introducing the objectives of the INSPIRE-SAT 7 mission, we present the satellite definition and the mission concept of operations. We also briefly show the observations made by the UVSQ-SAT CubeSat, and assess how two CubeSats in orbit could improve the information content of their Earth’s energy budget measurements. We conclude by reporting on the potential of future missions enabled by CubeSat constellations.
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Capovilla, Giorgio, Enrico Cestino, and Leonardo Reyneri. "Modular Multifunctional Composite Structure for CubeSat Applications: Embedded Battery Prototype Modal Analysis." Aerospace 10, no. 12 (November 30, 2023): 1009. http://dx.doi.org/10.3390/aerospace10121009.
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Current CubeSats usually exhibit a low structural mass efficiency and a low internal volume for their payloads. The present work aims to propose an advanced structural architecture for CubeSats that addresses the issues of low structural mass efficiency and payload volume. The starting concept is the smart tiles architecture for satellites developed for the ARAMIS (an Italian acronym for a highly modular architecture for satellite infrastructures) CubeSat project. By introducing multifunctional structures and lightweight, composite materials in the design of smart tiles, the volumetric and structural mass efficiency of the entire CubeSat are enhanced. The advantages of the chosen approach are preliminarily analyzed in terms of the volumetric efficiency and amplitude of the payload design space. A 1U battery tile design is then selected to investigate the multifunctional structures design aspects in the project of space structures. A battery tile prototype is designed, produced, and tested. The CubeSat volumetric increment and the payload volume gain with respect to the traditional architecture is shown to reach a maximum of 37%. The CubeSat structural mass ratio can be reduced to 16.7%.
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Benson, Ilia, Adam Kaplan, James Flynn, and Sharlene Katz. "Fault-Tolerant and Deterministic Flight-Software System For a High Performance CubeSat." International Journal of Grid and High Performance Computing 9, no. 1 (January 2017): 92–104. http://dx.doi.org/10.4018/ijghpc.2017010108.
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We describe the design and implementation of a complete flight-software operating system (OS) for a high-performance CubeSat carrying a third-party payload. This CubeSat's mission is to carry out research experiments on this payload while in low earth orbit. These experiments may be specified and prepared on the ground while the CubeSat is already in flight, and later uploaded via communication link. Experimental results collected by the CubeSat may likewise be downloaded to the ground. The CubeSat must collect and respond to sensor telemetry every second, and respond to ground communication on demand. To survive an adversarial space environment, the CubeSat OS is implemented as a deterministic state machine, storing state in a fault tolerant global memory structure. We validate our system via an end to end test of the CubeSat with its ground station, and demonstrate its capability to tolerate and even actively mitigate potential faults resulting from space radiation.
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Benhmimou, Boutaina, Fouad Omari, Nancy Gupta, Khalid El Khadiri, Rachid Ahl Laamara, and Mohamed El Bakkali. "Air-Gap Reduction and Antenna Positioning of an X-Band Bow Tie Slot Antenna on 2U CubeSats." Journal of Applied Engineering and Technological Science (JAETS) 6, no. 1 (December 15, 2024): 86–102. https://doi.org/10.37385/jaets.v6i1.6158.
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In this research work, a small size and wide-band Bow Tie slot antenna (BTSA) is proposed and optimized for use on an unlimited lifetime small-sized CubeSats at X-band. Interestingly, this paper introduces a graceful mechanism of integrating Bow Tie slot antennas on the bodies of small CubeSat configurations, which minimizes the antenna throwing from the satellite body and the whole CubeSat volume. The proposed approaches propose and analyze in detail how a small metallic part of a 2U CubeSat body improves the antenna performances around an operating frequency of 8.4 GHz. It maximizes the antenna gain simultaneously with the beamwidth angles at 8.4 GHz by suppressing the resulting back-lobes, which are re-directed outside the CubeSat box. These impacts are achieved by shifting a very small air-gap distance of only 1 mm between the back face of the BTSA dielectric and the CubeSat top face. The developed BTSA is lightweight and exhibits a unidirectional radiation pattern with a wide beamwidth angle of about 160° and a high gain of about 11.0 dBi at 8.4 GHz. The overall results with occupied size and volume are satisfactory for unlimited lifetime CubeSat missions at X-band such as UM5-Ribat and UM5-EOSAT of University Mohammed V in Rabat.
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Ferrer-Perez, J. A., D. Gaviria-Arcila, C. Romo-Fuentes, R. G. Chávez-Moreno, J. A. Ramírez-Aguilar, M. López-Parra, B. Bermudez-Reyes, et al. "Introduction to thermal control design process for CubeSats in Mexico." Journal of Physics: Conference Series 2804, no. 1 (July 1, 2024): 012011. http://dx.doi.org/10.1088/1742-6596/2804/1/012011.
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Abstract CubeSats are a popular type of spacecraft categorized as nanosatellites. In 1999, Professors first developed these devices at California Polytechnic State University and Stanford University to offer an affordable and accessible experience to students. Data information updated up to May 31st, 2023, shows that 2286 Nanosats have been launched, where 2105 were CubeSats. Moreover, 82 countries have nanosats, whereas Latin America has 44 CubeSat. The fact that Mexico just 5 launched 5 CubeSats is a consequence of the complicated space sector ecosystem in the nation that combines lack of funding and, more importantly, the absence of ¨know-how¨ design space missions from scratch. This manuscript reviews the system engineering methodology used to develop space missions, according to NASA discussing a particular methodology for CubeSat Missions. Next, a CubeSat data trend is shown, followed by a general description of its subsystems. Afterward, the design process activities of the Thermal Control Subsystem (TCS) based on the “NASA Systems Engineering Processes and Requirements” and “Thermal analysis handbook is described. The TCS is often underestimated and confused to implement. For this reason, a design methodology for the TCS accepted to Mexico context is proposed. Finally, the conclusions are presented.
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Stesina, Fabrizio, Sabrina Corpino, and Daniele Calvi. "A Test Platform to Assess the Impact of Miniaturized Propulsion Systems." Aerospace 7, no. 11 (November 16, 2020): 163. http://dx.doi.org/10.3390/aerospace7110163.
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Miniaturized propulsion systems can enable many future CubeSats missions. The advancement of the Technology Readiness Level of this technology passes through the integration in a CubeSat platform and the assessment of the impact and the interactions of the propulsion systems on the actual CubeSat technology and vice versa. The request of power, the thermal environmental, and the electromagnetic emissions generated inside the platform require careful analyses. This paper presents the upgraded design and the validation of a CubeSat test platform (CTP) that can interface a wide range of new miniaturized propulsion systems and gather unprecedented information for these analyses, which can be fused with the commonly used ground support equipment. The CTP features are reported, and the main achievements of the tests are shown, demonstrating the effective capabilities of the platform and how it allows for the investigation of the mutual interactions at system level between propulsion systems and the CubeSat technology.
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Vidal-Valladares, Matías G., and Marcos A. Díaz. "A Femto-Satellite Localization Method Based on TDOA and AOA Using Two CubeSats." Remote Sensing 14, no. 5 (February 24, 2022): 1101. http://dx.doi.org/10.3390/rs14051101.
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This article presents a feasibility analysis to remotely estimate the geo-location of a femto-satellite only using two station-CubeSats and the communication link between the femto-satellite and each CubeSat. The presented approach combines the Time Difference Of Arrival (TDOA) and Angle Of Arrival (AOA) methods. We present the motivation, the envisioned solution together with the constraints for reaching it, and the best potential sensitivity of the location precision for different (1) deployment scenarios of the femto-satellite, (2) precisions in the location of the CubeSats, and (3) precisions in each CubeSat’s Attitude Determination and Control Systems (ADCS). We implemented a simulation tool to evaluate the average performance for different random scenarios in space. For the evaluated cases, we found that the Cramér-Rao Bound (CRB) for Gaussian noise over the small error region of the solution is highly dependent on the deployment direction, with differences in the location precision close to three orders of magnitude between the best and worst deployment directions. For the best deployment case, we also studied the best location estimation that might be achieved with the current Global Navigation Satellite System (GNSS) and ADCS commercially available for CubeSats. We found that the mean-square error (MSE) matrix of the proposed solution under the small error condition can attain the CRB for the simulated time, achieving a precision below 30 m when the femto-satellite is separated by around 800 m from the mother-CubeSat.
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Zanette, Luca, Leonardo Reyneri, and Giuseppe Bruni. "Swarm system for CubeSats." Aircraft Engineering and Aerospace Technology 90, no. 2 (March 5, 2018): 379–89. http://dx.doi.org/10.1108/aeat-07-2016-0119.
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Purpose This paper aims to present an innovative system able to establish an inter-satellite communication crosslink and to determine the mutual physical positioning for CubeSats belonging to a swarm. Design/methodology/approach Through a system involving a smart antenna array managed by a beamforming control strategy, every CubeSat of the swarm can measure the direction of arrival (DOA) and the distance (range) to estimate the physical position of the received signal. Moreover, during the transmission phase, the smart antenna shapes the beam to establish a reliable and directive communication link with the other spacecraft and/or with the ground station. Furthermore, the authors introduce a deployable structure fully developed at Politecnico di Torino that is able to increase the external surface of CubeSats: this surface allows to gain the interspace between elements of the smart antenna. Findings As a consequence, the communication crosslink, the directivity and the detection performance of the DOA system in terms of directivity and accuracy are improved. Practical implications Moreover, the deployable structure offers a greater usable surface, so a larger number of solar panels can be used. This guarantees up to 25 W of average power supply for the on-board systems and for transmission on a one-unit (1U) CubeSat (10 × 10 × 10 cm). Originality/value This paper describes the physical implementation of the antenna array system on a 1U CubeSat by using the deployable structure developed. Depending on actuators and ability that every CubeSat disposes, various interaction levels between elements can be achieved, thus making the CubeSat constellation an efficient and valid solution for space missions.
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Park, Yeon-Kyu, Geuk-Nam Kim, and Sang-Young Park. "Novel Structure and Thermal Design and Analysis for CubeSats in Formation Flying." Aerospace 8, no. 6 (May 26, 2021): 150. http://dx.doi.org/10.3390/aerospace8060150.
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The CANYVAL-C (CubeSat Astronomy by NASA and Yonsei using a virtual telescope alignment for coronagraph) is a space science demonstration mission that involves taking several images of the solar corona with two CubeSats—1U CubeSat (Timon) and 2U CubeSat (Pumbaa)—in formation flying. In this study, we developed and evaluated structural and thermal designs of the CubeSats Timon and Pumbaa through finite element analyses, considering the nonlinearity effects of the nylon wire of the deployable solar panels installed in Pumbaa. On-orbit thermal analyses were performed with an accurate analytical model for a visible camera on Timon and a micro propulsion system on Pumbaa, which has a narrow operating temperature range. Finally, the analytical models were correlated for enhancing the reliability of the numerical analysis. The test results indicated that the CubeSats are structurally safe with respect to the launch environment and can activate each component under the space thermal environment. The natural frequency of the nylon wire for the deployable solar panels was found to increase significantly as the wire was tightened strongly. The conditions of the thermal vacuum and cycling testing were implemented in the thermal analytical model, which reduced the differences between the analysis and testing.
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Stesina, Fabrizio. "Validation of a Test Platform to Qualify Miniaturized Electric Propulsion Systems." Aerospace 6, no. 9 (September 4, 2019): 99. http://dx.doi.org/10.3390/aerospace6090099.
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Miniaturized electric propulsion systems are one of the main technologies that could increase interest in CubeSats for future space missions. However, the integration of miniaturized propulsion systems in modern CubeSat platforms presents some issues due to the mutual interactions in terms of power consumption, chemical contamination and generated thermal and electro-magnetic environments. The present paper deals with the validation of a flexible test platform to assess the interaction of propulsion systems with CubeSat-technologies from mechanical, electrical, magnetic, and chemical perspectives. The test platform is a 6U CubeSat hosting an electric propulsion system and able to manage a variety of electric propulsion systems. The platform can regulate and distribute electric power (up to 60 W), exchange data according to several protocols (e.g., CAN bus, UART, I2C, SPI), and provide different mechanical layouts in 4U box completely dedicated to the propulsion system. Moreover, the data gathered by the onboard sensors are combined with the data from external devices and tools providing unprecedented information about the mutual behavior of a CubeSat platform and an electric propulsion system.
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Bradburn, John, Mustafa Aksoy, Lennox Apudo, Varvara Vukolov, Henry Ashley, and Dylan VanAllen. "ACCURACy: A Novel Calibration Framework for CubeSat Radiometer Constellations." Remote Sensing 17, no. 3 (January 30, 2025): 486. https://doi.org/10.3390/rs17030486.
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As a result of progress in space technology, more scientific missions are benefiting from using CubeSats equipped with radiometers. CubeSat constellations are especially effective in overcoming obstacles in cost, weight, and power. However, these benefits have certain significant downsides, including the difficulty in calibration due to the increased sensitivity of instruments to ambient conditions. Such limitations prevent conventional calibration methods from being reliably applied to CubeSat radiometers. A novel, constellation-level calibration framework called “Adaptive Calibration of CubeSat Radiometer Constellations (ACCURACy)” is being developed to address this issue. ACCURACy, in its current version, uses telemetry data obtained from thermistors in each CubeSat to cluster constellation members into time-adaptive groups of radiometers in similar states. Each radiometer is assigned membership to a cluster and this status is updated as in-orbit measurements shift in the clustering model. This paper introduces the ACCURACy framework, discusses its theoretical background, and presents a MATLAB prototype with performance and uncertainty analyses using synthetic radiometer data in comparison with traditional radiometer calibration methods.
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Zhao, Yong, Yuhao Zhang, Zeming Zhao, Chenyuan Li, Lili Zhang, Xiaoze Yang, Honghao Yue, et al. "Simulation Analysis and Experimental Verification of the Transport Characteristics of a High-Volume CubeSat Storage Device." Aerospace 12, no. 6 (May 25, 2025): 466. https://doi.org/10.3390/aerospace12060466.
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To enhance the efficiency and extent of space resource development and utilization, this paper proposes a device designed for large-scale storage and transport of multi-species CubeSats, characterized by its high storage density and efficient transport capabilities. This paper comprehensively describes the structural composition and operational principles of this storage and transport system. Using dynamic simulation analysis, this paper studies the deployment mechanism of CubeSats within the push device and identifies the movement rules of the CubeSats during the deployment process. Simulation results show that under microgravity conditions, the average linear displacement speed of CubeSats reaches 32.8 mm/s during the pushing process. A prototype of the storage device was developed and tested for scenarios where the CubeSat’s initial position is aligned or misaligned relative to the transport pallet. The test results demonstrate that when the CubeSat’s initial attitude is misaligned, its pose can be autonomously adjusted to an ideal state upon entering the capture slide, with a maximum deviation of less than one degree. The designed push device and transport pallet exhibit robust anti-interference and tolerance capabilities. The transport process after pushing was tested, and the CubeSat pushed into the transport pallet was able to be stably transported to the designated location. In this process, the movement of the transport pallet was not interfered with by the storage device. The pushing device can complete the pushing task well.
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Nakayama, Daisuke, Takashi Yamauchi, Hirokazu Masui, Sangkyun Kim, Kazuhiro Toyoda, Tharindu Lakmal Dayarathna Malmadayalage, and Mengu Cho. "On-Orbit Experimental Result of a Non-Deployable 430-MHz-Band Antenna Using a 1U CubeSat Structure." Electronics 11, no. 7 (April 6, 2022): 1163. http://dx.doi.org/10.3390/electronics11071163.
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1U CubeSats often use the 430-MHz band for communication due to their size and power limitations, and half-wavelength dipole antennas are employed. A 430-MHz-band dipole antenna requires a deployable structure for a 1U CubeSat. However, a 1U CubeSat has a small volume margin for redundant systems, so the antenna deployment system can be a single point of failure. In this paper, the 1U CubeSat structure itself was used as an antenna. As a sub-mission of the BIRDS-4 project, three 1U CubeSats (GuaraniSat-1, Maya-2, and Tsuru) demonstrated this antenna structure. The results of the ground tests showed a maximum gain of −5.7 dBi with the flight model. These satellites were deployed from the International Space Station on 14 March 2021. Radio signals were alternately transmitted from the dipole antenna and the structure antenna onboard Tsuru for on-orbit demonstration on 15 December 2021, and the received signal strength on the ground was compared using RTL-SDR, SDR# and several codes. The ground station was able to receive both dipole and structure CW signals. The received power strength indicates that a gain of −8.1 dBi is being demonstrated with the structure antenna.
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González-Rodríguez, Desiree, Pedro Orgeira-Crespo, Chantal Cappelletti, and Fernando Aguado-Agelet. "Methodology for CubeSat Debris Collision Avoidance Based on Its Active ADCS System." Applied Sciences 13, no. 22 (November 16, 2023): 12388. http://dx.doi.org/10.3390/app132212388.
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This research assesses the feasibility of a collision avoidance methodology for CubeSats lacking propulsion. The approach involves altering the satellite’s orientation to modify its cross-sectional area and, subsequently, the drag force. Examining altitudes within low Earth orbit (LEO) across 2U, 3U, and 6U CubeSat formats, maneuvers are considered two days before the Time to Closest Approach (TCA). Evaluation against the Conjunction Data Messages (CDMs) threshold miss distances reveals a minimum 7% and maximum 106% deviation in Vertical Distance Difference (VDD), and 68% to 1045% in Horizontal Distance Difference (HDD) concerning the notification threshold. These findings strongly endorse the practicality of the proposed collision avoidance methodology, utilizing CubeSat Attitude Determination and Control Systems (ADCS). Ongoing research focuses on assessing ADCS maneuver execution rates and implementation times, advancing our understanding and applicability of this innovative CubeSat collision avoidance approach.
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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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Melaku, Shimeles Demissie, and Hae-Dong Kim. "Optimization of Multi-Mission CubeSat Constellations with a Multi-Objective Genetic Algorithm." Remote Sensing 15, no. 6 (March 13, 2023): 1572. http://dx.doi.org/10.3390/rs15061572.
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The increasing demand for low-cost space-borne Earth observation missions has led to small satellite constellation systems development. CubeSat platforms can provide a cost-effective multiple-mission space system using state-of-the-art technology. This paper presents a new approach to CubeSat constellation design for multiple missions using a multi-objective genetic algorithm (MOGA). The CubeSat constellation system is proposed to perform multi-missions that should satisfy global Earth observation and regional disaster monitoring missions. A computational approach using a class of MOGA named non-dominated sorting genetic algorithm II is implemented to optimize the proposed system. Pareto optimal solutions are found that can minimize the number of satellites and the average revisit time (ART) for both regional and global coverage while maximizing the percentage coverage. As a result, the study validates the feasibility of implementing the CubeSat constellation design with an acceptable level of performance in terms of ART and percentage coverage. Moreover, the study demonstrates CubeSat’s ability to perform a multi-missions.
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Nayyar, Shivang, Sandeep Kumar, and Vikas Suhag. "Earthquake Signature Detection Using Cubesat Technology." Journal of Advance Research in Electrical & Electronics Engineering (ISSN: 2208-2395) 1, no. 2 (February 28, 2014): 03–07. http://dx.doi.org/10.53555/nneee.v1i2.256.
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Cubesats play a vital role in development of new micro components being used in various micro/nano satellites. Cubesats have an effective small design and have the ability to get modified easily. Quakesat, a satellite being deployed by Space Systems Development Laboratory (SSDL) is used to study, detect, record, and downlink extremely low frequency (ELF) magnetic signals, which are used to predict earthquake activity. Quakesat is a live example of cubesat technology, uses non space application components and provides a low cost alternative to launch space missions and support nano satellite infrastructure in future.
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Vishal S K, Hariharan S, and Vishnuprakash B. "Interplanetary CubeSat Networks: Challenges and Future Prospects in Deep Space Communication." Acceleron Aerospace Journal 4, no. 5 (May 30, 2025): 1123–31. https://doi.org/10.61359/11.2106-2526.
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The rapid development of miniaturized space technology has enabled CubeSats to extend their reach beyond low Earth orbit and be used for interplanetary missions. These small, low-cost spacecrafts hold new promises for distributed science observations, communication relay, and autonomous exploration. Establishing dependable communication networks for CubeSats in deep space is a significant challenge due to severe latency, limited power budgets, low bandwidth, and the lack of specialized interplanetary infrastructure. This review addresses the fundamental communication challenges of interplanetary CubeSats, including signal loss over large distances, Doppler shift, and frequency stability. It also speaks of current and future solutions such as Delay/Disruption Tolerant Networking (DTN), optical communications systems, and cooperative CubeSat swarm development. Through current mission analysis and projected architecture, this paper highlights the technological advances needed to enable scalable and fault-tolerant interplanetary CubeSat networks. The review is completed with a summary of future research directions and the urgent necessity of autonomous, adaptive communication systems to facilitate the next generation of deep space exploration.
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Capovilla, Giorgio, Enrico Cestino, Leonardo Reyneri, and Federico Valpiani. "Modular Multifunctional Composite Structure for CubeSat Applications: Embedded Battery Prototype Thermal Analysis." Batteries 11, no. 5 (April 23, 2025): 172. https://doi.org/10.3390/batteries11050172.
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The present work aims to develop the current CubeSats architecture. Starting from the framework of project ARAMIS (an Italian acronym for a highly modular architecture for satellite infrastructures), a new concept of smart tiles has been developed, employing multifunctional structures and lightweight, composite materials. This enables increased CubeSat mass efficiency and payload volume. An embedded battery tile has been designed, built, and tested from a vibration point of view. In the present work, the LiPo batteries selected for the prototype have been tested with the HPPC testing procedure, to extract their equivalent Randles circuit parameters. Thus, the thermal power dissipation from the batteries can be estimated. With these data, Thermal Desktop simulations of a representative ARAMIS CubeSat are performed, considering LEO orbit and hot/cold cases. Firstly, a parametric analysis was conducted to evaluate the thermal behaviors of various design alternatives. A suitable configuration for the CubeSat was then found, enabling the validation of the embedded battery tile from a thermal point of view. The final configuration includes heaters for the LiPo batteries, a commercial CubeSat skeleton made in aluminum alloy, and a top coating for smart tiles with proper solar absorptivity.
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Yuen, Brosnan, and Mihai Sima. "Low Cost Radiation Hardened Software and Hardware Implementation for CubeSats." Arbutus Review 9, no. 1 (September 25, 2018): 46–62. http://dx.doi.org/10.18357/tar91201818386.
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CubeSats are small satellites used for scientific experiments because they cost less than full sized satellites. Each CubeSat uses an on-board computer. The on-board computer performs sensor measurements, data processing, and CubeSat control. The challenges of designing an on-board computer are costs, radiation, thermal stresses, and vibrations. An on-board computer was designed and implemented to solve these challenges. The on-board computer used special components to mitigate radiation effects. Software was also used to provide redundancies in cases of faults. This paper may aid future spacecraft design as it improves the reliability of spacecraft, while keeping costs low.
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Tribak, Ferdaous, Othmane Bendaou, and Fayçal Ben Nejma. "Impact of orbit inclination on heat transfer in a 1U LEO CubeSat." MATEC Web of Conferences 371 (2022): 02001. http://dx.doi.org/10.1051/matecconf/202237102001.
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Temperature prediction is crucial to build dependable CubeSats and operate them at peak efficiency. Therefore, all parameters that could impact the thermal performance of the satellite must be taken into account in the thermal analysis. This work covers the thermal simulation of a 1U CubeSat. The objective is to simulate, using the commercial software COMSOL Multiphysics, the impact of an important parameter on the satellite’s temperature distribution: beta angle. It defines the position of the CubeSat relatively to the solar vector. To investigate the effect of this parameter on the satellite, a set of simulations was performed for different beta angles.
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Abhishek, Sujith M.S., Kamalesh Pulluru, Jeevan D, Dr. Sindhu Sree M, Dr. Pavithra G, and Dr. T.C.Manjunath. "Mars Exploration Perseverance Rover." international journal of engineering technology and management sciences 7, no. 3 (2023): 436–39. http://dx.doi.org/10.46647/ijetms.2023.v07i03.56.
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In this paper, the development of chronologies for the mass exploration rover is presented in a nutshell. Over the last twenty years, a “New Space” revolution has quietly unfolded in the domain of space exploration. Previously, only select countries, space agencies, and large industries were able to design, launch, and operate satellites and spacecraft. However, this has changed with the introduction of the “CubeSat” standard in 1999, which has allowed universities and research institutes to join in the space race. In 2013, the commercial Earth Observation sector took off, with two companies launching 100+ CubeSat constellations for optical imaging and weather prediction, featuring very low revisit times. Today, a similar transformation is taking place in the fields of telecommunications and astronomical scientific missions. This chapter reviews the evolution of the space sector up until the arrival of the CubeSats, followed by a discussion of the CubeSat’s intrinsic limitations, which are crucial in understanding the development and current status of the CubeSat sector. The strategies of NASA and ESA are also presented. Finally, the chapter concludes with a summary of the technology roadmap required to enable the next generation of CubeSat-based missions, including satellite constellations or federations, formation flying, and synthetic apertures. The work done & presented in this paper is the result of the mini-project work that has been done by the first sem engineering students of the college and as such there is little novelty in it and the references are being taken from various sources from the internet, the paper is being written by the students to test their writing skills in the starting of their engineering career and also to test the presentation skills during their mini-project presentation. The work done & presented in this paper is the report of the assignment / alternate assessment tool as a part and parcel of the academic assignment of the first year subject on nanotechnology & IoT.
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Saeidi, Tale, and Saeid Karamzadeh. "Enhancing CubeSat Communication Through Beam-Steering Antennas: A Review of Technologies and Challenges." Electronics 14, no. 4 (February 14, 2025): 754. https://doi.org/10.3390/electronics14040754.
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With their compact design and versatility, CubeSats have emerged as critical platforms for advancing space exploration and communication technologies. However, achieving reliable and efficient communication in the dynamic and constrained environment of low Earth orbit (LEO) remains a significant challenge. Beam-steering antenna systems offer a promising solution to address these limitations, enabling adaptive communication links with improved gain and coverage. This review article provides a comprehensive analysis of the state-of-the-art in CubeSat communication, concentrating on the latest developments in beam-steering antennas. By synthesizing the findings from recent studies, the key challenges are highlighted, including power constraints, miniaturization, and integration with CubeSat platforms. Furthermore, this paper investigates cutting-edge techniques, such as phased array systems, metasurface-based designs, and reconfigurable antennas, which pave the way for enhanced performance. This study can serve as a resource for researchers and engineers, offering insights into current trends and future opportunities for advancing CubeSat communications through innovative antenna systems.
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Nganpet Nzeugaing, Gutembert, and Elmarie Biermann. "Image compression system for a 3U CubeSat." Journal of Engineering, Design and Technology 14, no. 3 (July 4, 2016): 446–60. http://dx.doi.org/10.1108/jedt-12-2013-0086.
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Purpose Research and application on the design, implementation and testing of an image compression system for a 3U CubeSat. Design/methodology/approach This paper is an intensive study on image compression technique, proposed design and approach on appropriate hardware for image compression on-board the CubeSats. Findings The paper reveals a method on improving image compression ration while maintaining the image quality unchanged. It also discusses about an appropriate hardware (world smallest super computer) for image compression on-board the CubeSats. Originality/value The study provides insight into image compression algorithm.
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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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Giordano, A. "Enabling Interplanetary Exploration for CubeSats with a Fully Chemical Propulsion System." Journal of the British Interplanetary Society 76, no. 4 (June 14, 2023): 134–44. http://dx.doi.org/10.59332/jbis-076-04-0134.
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Interplanetary CubeSat missions are currently becoming more popular, with a significant number of recently planned missions. The context of this paper is a Mars mission, starting from a parking orbit around Earth: the adoption of a chemical propulsion system for the Earth-Mars transfer phase is investigated, considering the recent technological developments for CubeSats. A trade-off of propulsion system type and propellant results in the choice of a mono-propellant system adopting the HAN-based propellant AF-M315E (ASCENT). The main challenge for the propulsion system is to fit inside a CubeSat standardised volume, which can range up to 24 U, for which the implementation of a suitable COTS micro-pump is considered. Finally, the complete architecture and design of the propulsion system is presented. This work demonstrates the feasibility of adopting full chemical propulsion for an interplanetary CubeSat mission, with consequent advantages in terms of transfer time and required power, at the cost of relatively small mass and volume left for the other subsystems. Even better results can be expected for interplanetary missions requiring slightly lower ΔV budgets, such as Near Earth Objects exploration or asteroid fly-by missions. Keywords: CubeSat, Chemical Propulsion, Green Mono-propellant, Interplanetary Mission, Mars Exploration
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Nurgizat, Yerkebulan, Abu-Alim Ayazbay, Dimitri Galayko, Gani Balbayev, and Kuanysh Alipbayev. "Low-Cost Orientation Determination System for CubeSat Based Solely on Solar and Magnetic Sensors." Sensors 23, no. 14 (July 14, 2023): 6388. http://dx.doi.org/10.3390/s23146388.
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CubeSats require accurate determination of their orientation relative to the Sun, Earth, and other celestial bodies to operate successfully and collect scientific data. This paper presents an orientation system based on solar and magnetic sensors that offers a cost-effective and reliable solution for CubeSat navigation. Solar sensors analyze the illumination on each face to measure the satellite’s orientation relative to the Sun, while magnetic sensors determine the Earth’s magnetic field vector in the satellite’s reference frame. By combining the measured data with the known ephemeris of the satellite, the satellite–Sun vector and the magnetic field orientation can be reconstructed. The orientation is expressed using quaternions, representing the rotation from the internal reference system of the satellite to the selected reference system. The proposed system demonstrates the ability to accurately determine the orientation of a CubeSat using only two sensors, making it suitable for installations where more complex and expensive instruments are impractical. Additionally, the paper presents a mathematical model of a low-cost CubeSat orientation system and a hardware implementation of the sensor. The technology, using solar and magnetic sensors, provides a reliable and affordable solution for CubeSat navigation, supporting the increasing sophistication of miniature payloads and enabling accurate satellite positioning in space missions.
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Chiewchanchang, P., P. Parittothok, R. Manorattana, and J. Wongwiwat. "The study of convergent-divergent nozzle geometry for CubeSat chemical propulsion system." IOP Conference Series: Earth and Environmental Science 1500, no. 1 (May 1, 2025): 012012. https://doi.org/10.1088/1755-1315/1500/1/012012.
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Abstract The satellite was designed to simulate an orbit around a planet, serving as a vital tool for space exploration. To reduce resource consumption and development time, nanosatellites, or CubeSats, were developed. Despite their advantages, CubeSats face significant space constraints, often limiting them to payload purposes. However, for certain missions, orbital or directional control becomes essential. To address this, CubeSats incorporate a propulsion system, with the nozzle serving as a critical component. The nozzle converts the high temperature and pressure generated by the propulsion reactor into velocity, enabling precise satellite movement and control. To evaluate the performance of the nozzle, experimental setups and CFD (Computational Fluid Dynamics) simulations were employed. Experimentation involved hydrogen peroxide (H2O2) reacting with a silver catalyst under atmospheric pressure. Results demonstrated that increasing the H2O2 flow rate resulted in higher temperatures and pressures. However, a limitation was observed in the silver catalyst, which degraded after initial use, impacting performance. CFD simulations investigated the effects of varying the convergent and divergent half-angles of the nozzle. Findings revealed that the divergent half-angle significantly influenced thrust performance, with an optimal angle of 35 degrees producing maximum thrust due to reduced boundary layer effects. Beyond this angle, thrust efficiency declined. Meanwhile, variations in the convergent half-angle showed minimal impact on thrust generation, highlighting the divergent half-angle’s critical role in optimizing propulsion. These results emphasize the importance of nozzle geometry in CubeSat propulsion systems. By optimizing the divergent half-angle, CubeSats can achieve higher thrust efficiency, enhancing their operational capabilities. The study provides valuable insights for improving the design and performance of CubeSat propulsion systems, enabling more effective satellite manoeuvrability and expanding CubeSat applications in space exploration.
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López-Balcázar, C. A., Jorge Hernández, F. Ramírez-López, and G. G. García-Balcázar. "Verilog-based logical design of CubeSat ACS based in fuzzy inference systems focused on trapezoidal membership functions." Journal of Physics: Conference Series 2946, no. 1 (January 1, 2025): 012004. https://doi.org/10.1088/1742-6596/2946/1/012004.
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Abstract Nowadays, fuzzy inference systems are popular tools to implement control systems with relative development ease and speed. In particular, within CubeSat development, it is crucial to implement systems subject to severe design restrictions imposed by the CubeSat Standard, like size, weight and power consumption, among others. For attitude control in CubeSats, one option is to implement fuzzy inference systems of the Sugeno type. However, control algorithms based in fuzzy logic principles are, as many others, established in a sequential order, following specific steps, and not requiring further repetitive tasks. In this sense, they are more suitable to be implemented in logic circuitry than in microcontrollers or microprocessors. Thus, in this work we present the logical design of an attitude control subsystem for CubeSats which is developed in Verilog® hardware description language, which is then validated through simulation. As this is an ongoing research, the presented system only implements triangular/trapezoidal membership functions.
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Cardillo, Emanuele, Renato Cananzi, and Paolo Vita. "Wideband Versatile Receiver for CubeSat Microwave Front-Ends." Sensors 22, no. 22 (November 21, 2022): 9004. http://dx.doi.org/10.3390/s22229004.
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One of the main features of CubeSats is represented by their extreme versatility, e.g., maintaining the same overall structure for different purposes. This requires high technological flexibility achievable in a cost-effective way while maintaining compact sizes. In this contribution, a microwave receiver specifically designed for CubeSat applications is proposed. Due to the wide input operating bandwidth, i.e., 2 GHz–18 GHz, it can be exploited for different purposes, e.g., satellite communication, radars, and electronic warfare systems. This is beneficial for CubeSat systems, whereby the possibility to share the same front-end circuit for different purposes is a key feature in reducing the overall size and weight. The downconverter was designed to minimize the spurious contributions at low frequency by taking advantage, at the same time, of commercial off-the-shelf components due to their cost-effectiveness. The idea behind this work is to add flexibility to the CubeSat communication systems in order to be reusable in different contexts. This feature enables new applications but also provides the largest bandwidth if required from the ground system. An accurate experimental characterization was performed to validate the downconverter performance with the aim of allowing easy system integration for the new frontier of CubeSat technologies. This paves the way for the most effective implementation of the Internet of Things (IoT), machine-to-machine (M2M) communications, and smart-everything services.
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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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Bogomolov, A. V., V. V. Bogomolov, A. F. Iyudin, V. E. Eremeev, Yu K. Zaiko, V. V. Kalegaev, I. N. Myagkova, et al. "Observations of solar cosmic rays using cubesat nanosatellites." Izvestiâ Akademii nauk SSSR. Seriâ fizičeskaâ 88, no. 2 (October 14, 2024): 314–18. http://dx.doi.org/10.31857/s0367676524020266.
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We discussed the possibilities of using cubesat nanosatellites for studying solar cosmic rays. SCR electron fluxes in the polar caps at an altitude of ~550 km were detected. The measurements were carried out with DeCoR scintillation detectors operated at several cubesats of Moscow State University during the solar cosmic ray event on September 6–21, 2022.
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Nabanita Brahmachari, Mohamed Abdullah K, and Vishnuprakash B. "Aerodynamic Panel Shape Optimization for CubeSats to Reduce Chaotic Motion in Lower Earth Orbit." Acceleron Aerospace Journal 4, no. 2 (February 28, 2025): 911–20. https://doi.org/10.61359/11.2106-2509.
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CubeSats are increasingly employed in various low-Earth orbit (LEO) missions. However, their stability is often compromised by chaotic motion induced by aerodynamic disturbances and the deployment of appendages, such as solar panels or fins. Addressing these challenges is critical to ensuring mission reliability and extending operational lifetimes. This study explores the aerodynamic performance and stability implications of deployable fin geometries for CubeSats, where two configurations of square-shaped and elliptical fins are chosen for analysis. Using computational fluid dynamics (CFD) simulations under identical boundary conditions, velocity fields, flow structures, and turbulence intensity around the CubeSat have been examined. The results reveal that elliptical fins produce smoother flow patterns with reduced velocity gradients, minimizing turbulence and enhancing stability. In contrast, square fins exhibit higher turbulence intensity, which could promote chaotic motion. By establishing the aerodynamic advantages of elliptical fin designs, this work not only provides actionable insights for stabilizing CubeSats in LEO but also offers a framework for optimizing fin geometries to mitigate chaotic behavior. These findings lay the foundation for future advancements in CubeSat design, enabling improved aerodynamic performance and stability in dynamic orbital environments.
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Ivliev, Nikolay, Vladimir Podlipnov, Maxim Petrov, Ivan Tkachenko, Maksim Ivanushkin, Sergey Fomchenkov, Maksim Markushin, et al. "3U CubeSat-Based Hyperspectral Remote Sensing by Offner Imaging Hyperspectrometer with Radially-Fastened Primary Elements." Sensors 24, no. 9 (April 30, 2024): 2885. http://dx.doi.org/10.3390/s24092885.
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This paper presents findings from a spaceborne Earth observation experiment utilizing a novel, ultra-compact hyperspectral imaging camera aboard a 3U CubeSat. Leveraging the Offner optical scheme, the camera’s hyperspectrometer captures hyperspectral images of terrestrial regions with a 200 m spatial resolution and 12 nanometer spectral resolution across a 400 to 1000 nanometer wavelength range, covering 150 channels in the visible and near-infrared spectrums. The hyperspectrometer is specifically designed for deployment on a 3U CubeSat nanosatellite platform, featuring a robust all-metal cylindrical body of the hyperspectrometer, and a coaxial arrangement of the optical elements ensures optimal compactness and vibration stability. The performance of the imaging hyperspectrometer was rigorously evaluated through numerical simulations prior to construction. Analysis of hyperspectral data acquired over a year-long orbital operation demonstrates the 3U CubeSat’s ability to produce various vegetation indices, including the normalized difference vegetation index (NDVI). A comparative study with the European Space Agency’s Sentinel-2 L2A data shows a strong agreement at critical points, confirming the 3U CubeSat’s suitability for hyperspectral imaging in the visible and near-infrared spectrums. Notably, the ISOI 3U CubeSat can generate unique index images beyond the reach of Sentinel-2 L2A, underscoring its potential for advancing remote sensing applications.
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Hussain, Rifaqat, Khaled Aljaloud, Abida Shaheen Rao, Abdullah M. AlGarni, Ali H. Alqahtani, Abdul Aziz, Yosef T. Aladadi, Saad I. Alhuwaimel, and Niamat Hussain. "Miniaturized Folded-Slot CubeSat MIMO Antenna Design with Pattern Diversity." Sensors 22, no. 20 (October 16, 2022): 7855. http://dx.doi.org/10.3390/s22207855.
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In this paper, a folded slot-based multiple-input–multiple-output (MIMO) antenna design for Cube Satellite (CubeSat) applications is presented for the ultra-high frequency (UHF) band. A unique combination of a reactively loaded meandered slot with a folded structure is presented to achieve the antenna’s miniaturization. The proposed antenna is able to operate over a wide frequency band from 430~510 MHz. Moreover, pattern diversity is achieved by the antenna’s element placement, resulting in good MIMO diversity performance. The four elements are placed on one Unit (1U) for CubeSat dimensions of 100 mm × 100 mm × 100 mm. The miniaturized antenna design with pattern diversity over a wide operating band is well suited for small satellite applications, particularly CubeSats in the UHF band.
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Fahimi, Farbod. "Vision-Based CubeSat Closed-Loop Formation Control in Close Proximities." Nonlinear Engineering 8, no. 1 (January 28, 2019): 609–18. http://dx.doi.org/10.1515/nleng-2017-0147.
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Abstract A vision based formation and attitude controller has been derived and simulated for the formation keeping of two 3U CubeSats. Four markers are installed on the leader CubeSat. Two cameras are installed on the follower CubeSat. An efficient vision based pose estimation method is used to estimate the pose of the follower with respect to the leader. A Higher-Order Sliding Mode (HOSM) exact differentiator with finite-time convergence is derived to estimate the rate of the follower’s pose parameters. The follower’s pose and its time rate are fedback to HOSM formation and attitude controllers to correct any gradual drift in formation and pose of the follower. The simulations show the effectiveness of the approach, and its feasibility on existing hardware.
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Wang, Zhaocheng, and Enrique R. Vivoni. "Mapping Flash Flood Hazards in Arid Regions Using CubeSats." Remote Sensing 14, no. 17 (August 26, 2022): 4218. http://dx.doi.org/10.3390/rs14174218.
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Flash flooding affects a growing number of people and causes billions of dollars in losses each year with the impact often falling disproportionally on underdeveloped regions. To inform post-flood mitigation efforts, it is crucial to determine flash flooding extents, especially for extreme events. Unfortunately, flood hazard mapping has often been limited by a lack of observations with both high spatial and temporal resolution. The CubeSat constellation operated by Planet Labs can fill this key gap in Earth observations by providing 3 m near-daily multispectral imagery at the global scale. In this study, we demonstrate the imaging capabilities of CubeSats for mapping flash flood hazards in arid regions. We selected a severe storm on 13–14 August 2021 that swept through the town of Gila Bend, Arizona, causing severe flood damages, two deaths, and the Declaration of a State of Emergency. We found the spatial extent of flooding can be mapped from CubeSat imagery through comparisons of the near-infrared surface reflectance prior to and after the flash flood event (ΔNIR). The unprecedented spatiotemporal resolution of CubeSat imagery allowed the detection of ponded (ΔNIR ≤ −0.05) and flood-affected (ΔNIR ≥ +0.02) areas that compared remarkably well with the 100-year flood event extent obtained by an independent hydraulic modeling study. Our findings demonstrate that CubeSat imagery provides valuable spatial details on flood hazards and can support post-flood activities such as damage assessments and emergency relief.
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OKINO, Satoshi, Shigeki UCHIYAMA, Kazuma SASE, Yuka IWAI, Kanako DAIGO, Nobuaki KINOSHITA, Sotaro HASHIGUCHI, and Yasuyuki MIYAZAKI. "Nihon University CubeSat Project." Proceedings of the JSME annual meeting 2004.5 (2004): 475–76. http://dx.doi.org/10.1299/jsmemecjo.2004.5.0_475.
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Cook, Riley, Lukas Swan, and Kevin Plucknett. "Impact of Test Conditions While Screening Lithium-Ion Batteries for Capacity Degradation in Low Earth Orbit CubeSat Space Applications." Batteries 7, no. 1 (March 15, 2021): 20. http://dx.doi.org/10.3390/batteries7010020.
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A wide variety of commercial cylindrical lithium-ion batteries are available for use in nanosatellites (CubeSats) that cycle in low Earth orbit (LEO). This space application differs greatly from the conditions used to create the manufacturer datasheets that CubeSat teams rely on to screen cell types and estimate performance lifetimes. To address this, we experimentally test three LIB cell types using a representative LEO CubeSat power profile in three progressively complex test representations of LEO. The first is “standardized” condition (101 kPa-abs, 20 °C), which uses only a power cycler; the second adds a thermal chamber for “low temperature” condition (101 kPa-abs, 10 °C); and the third adds a vacuum chamber for “LEO” condition (0.2 kPa-abs, 10 °C). Results indicate that general “standardized” and “low temperature” conditions do not yield representative results to what would occur in LEO. Coincidentally, the “LEO” condition gives similar capacity degradation results as manufacturer datasheets. This was an unexpected finding, but suggests that CubeSat teams use full experimental thermal-vacuum testing or default to the manufacturer datasheet performance estimates during the lithium-ion cell screening and selection process. The use of a partial representation of the LEO condition is not recommended.
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Yan, Mingzheng, Xiaodong Song, Jixin Shi, Bo Zhao, and Haosen Zhang. "Fast non-singular terminal sliding mode control of the cubesat attitude for on-orbit assembly process." Journal of Physics: Conference Series 2820, no. 1 (August 1, 2024): 012036. http://dx.doi.org/10.1088/1742-6596/2820/1/012036.
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Abstract The construction of space assemblies using on-orbit assembly technology is beneficial for supporting various complex space missions, and has broad application prospects and high practical significance. This paper designs a novel terminal sliding mode attitude controller to address the time-varying mass parameters and suppress internal and external disturbances during the on-orbit assembly process of CubeSat. Specifically, the CubeSat attitude dynamics model with a telescopic mechanism is established based on the vector mechanics method. Subsequently, given the expressions for fast, non-singular terminal sliding surfaces and adaptive power-reaching laws, the controller’s stability is demonstrated. Then, the variation pattern of the model parameters is determined through dynamic simulations, and finally, extensive simulations verify the attitude control effect of the two CubeSats in the on-orbit assembly process. The simulation results demonstrate that the proposed method is robust to time-varying and jumping CubeSat mass parameters and presents a significant suppression effect on random interference caused by the shaking of the telescopic mechanism and the impact torque at the moment of the docking lock. The proposed method has faster attitude convergence and smoother control torque than traditional sliding mode control methods.