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Artykuły w czasopismach na temat „CubeSat”

Autor: Grafiati

Data publikacji: 4 czerwca 2021

Data aktualizacji: 25 lipca 2025

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1

De Leon, Michael B., Ulysses B. Ante, Madelene S. Velasco, et al. "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 pape

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Xu, Duo, Honghao Yue, Yong Zhao, et al. "Improved A* Algorithm for Path Planning Based on CubeSats In-Orbit Electromagnetic Transfer System." Aerospace 11, no. 5 (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

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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 (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 e

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Menchinelli, Alessandro, Francesca Ingiosi, Ludovico Pamphili, et al. "A Reliability Engineering Approach for Managing Risks in CubeSats." Aerospace 5, no. 4 (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 a

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5

Sibanda, Matthew, and Robert Ryk van Zyl. "Practical electromagnetic compatibility studies of a CubeSat." Journal of Engineering, Design and Technology 14, no. 4 (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

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Alanazi, Abdulaziz, and Jeremy Straub. "Engineering Methodology for Student-Driven CubeSats." Aerospace 6, no. 5 (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

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7

Lu, Sining, Panagiotis Ioannis Theoharis, Raad Raad, et al. "A Survey on CubeSat Missions and Their Antenna Designs." Electronics 11, no. 13 (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

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8

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 (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 spacecr

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9

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

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10

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,

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11

Meftah, Mustapha, Fabrice Boust, Philippe Keckhut, 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 (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 technolog

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12

Capovilla, Giorgio, Enrico Cestino, and Leonardo Reyneri. "Modular Multifunctional Composite Structure for CubeSat Applications: Embedded Battery Prototype Modal Analysis." Aerospace 10, no. 12 (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 str

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13

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 (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 o

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14

Bouzoukis, Konstantinos-Panagiotis, Georgios Moraitis, Vassilis Kostopoulos, and Vaios Lappas. "An Overview of CubeSat Missions and Applications." Aerospace 12, no. 6 (2025): 550. https://doi.org/10.3390/aerospace12060550.

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The proliferation of CubeSats in Earth orbit has accelerated dramatically in recent years, with projections indicating continued growth in the coming decades. This review examines the evolution of CubeSat applications, from basic technology demonstrations to complex mission capabilities, including Earth observation, telecommunications, astronomical research, biological experimentation, and deep-space exploration. A notable shift has occurred over the past fifteen years, with CubeSats transitioning from standalone platforms to integrated nodes within larger constellations, particularly for Eart

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15

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 (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 ante

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16

Ferrer-Perez, J. A., D. Gaviria-Arcila, C. Romo-Fuentes, et al. "Introduction to thermal control design process for CubeSats in Mexico." Journal of Physics: Conference Series 2804, no. 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 fu

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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 (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 minia

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18

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 (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) precisi

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Zanette, Luca, Leonardo Reyneri, and Giuseppe Bruni. "Swarm system for CubeSats." Aircraft Engineering and Aerospace Technology 90, no. 2 (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

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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 (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 m

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Stesina, Fabrizio. "Validation of a Test Platform to Qualify Miniaturized Electric Propulsion Systems." Aerospace 6, no. 9 (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 perspecti

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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 (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 Cube

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Zhao, Yong, Yuhao Zhang, Zeming Zhao, et al. "Simulation Analysis and Experimental Verification of the Transport Characteristics of a High-Volume CubeSat Storage Device." Aerospace 12, no. 6 (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. Simulatio

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Nakayama, Daisuke, Takashi Yamauchi, Hirokazu Masui, et al. "On-Orbit Experimental Result of a Non-Deployable 430-MHz-Band Antenna Using a 1U CubeSat Structure." Electronics 11, no. 7 (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 s

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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 (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 Horizonta

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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

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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 (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 n

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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 (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 in

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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 (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 interplaneta

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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 (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

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Yuen, Brosnan, and Mihai Sima. "Low Cost Radiation Hardened Software and Hardware Implementation for CubeSats." Arbutus Review 9, no. 1 (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 space

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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

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Abhishek, Sujith M.S., Kamalesh Pulluru, et al. "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 l

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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 (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 de

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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 (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 in

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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 (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

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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 (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 CubeSa

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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 (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

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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 (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 propulsio

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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 (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

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Cardillo, Emanuele, Renato Cananzi, and Paolo Vita. "Wideband Versatile Receiver for CubeSat Microwave Front-Ends." Sensors 22, no. 22 (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 pos

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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 it

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Bogomolov, A. V., V. V. Bogomolov, A. F. Iyudin, et al. "Observations of solar cosmic rays using cubesat nanosatellites." Izvestiâ Akademii nauk SSSR. Seriâ fizičeskaâ 88, no. 2 (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 (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) sim

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Ivliev, Nikolay, Vladimir Podlipnov, Maxim Petrov, et al. "3U CubeSat-Based Hyperspectral Remote Sensing by Offner Imaging Hyperspectrometer with Radially-Fastened Primary Elements." Sensors 24, no. 9 (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 cyli

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Hussain, Rifaqat, Khaled Aljaloud, Abida Shaheen Rao, et al. "Miniaturized Folded-Slot CubeSat MIMO Antenna Design with Pattern Diversity." Sensors 22, no. 20 (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

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Fahimi, Farbod. "Vision-Based CubeSat Closed-Loop Formation Control in Close Proximities." Nonlinear Engineering 8, no. 1 (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 controlle

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Wang, Zhaocheng, and Enrique R. Vivoni. "Mapping Flash Flood Hazards in Arid Regions Using CubeSats." Remote Sensing 14, no. 17 (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

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OKINO, Satoshi, Shigeki UCHIYAMA, Kazuma SASE, et al. "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 (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; t

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