Artykuły w czasopismach: „CubeSat”

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

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

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

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

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

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

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

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

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

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

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

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

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Meftah, Mustapha, Fabrice Boust, Philippe Keckhut, Alain Sarkissian, Thomas Boutéraon, Slimane Bekki, Luc Damé i in. "INSPIRE-SAT 7, a Second CubeSat to Measure the Earth’s Energy Budget and to Probe the Ionosphere". Remote Sensing 14, nr 1 (1.01.2022): 186. http://dx.doi.org/10.3390/rs14010186.

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INSPIRE-SAT 7 is a French 2-Unit CubeSat (11.5 × 11.5 × 22.7 cm) primarily designed for Earth and Sun observation. INSPIRE-SAT 7 is one of the missions of the International Satellite Program in Research and Education (INSPIRE). Twice the size of a 4 × 4 Rubik’s Cube and weighing about 3 kg, INSPIRE-SAT 7 will be deployed in Low Earth Orbit (LEO) in 2023 to join its sister satellite, UVSQ-SAT. INSPIRE-SAT 7 represents one of the in-orbit demonstrators needed to test how two Earth observation CubeSats in orbit can be utilized to set up a satellite constellation. This new scientific and technological pathfinder CubeSat mission (INSPIRE-SAT 7) uses a multitude of miniaturized sensors on all sides of the CubeSat to measure the Earth’s energy budget components at the top-of-the-atmosphere for climate change studies. INSPIRE-SAT 7 contains also a High-Frequency (HF) payload that will receive HF signals from a ground-based HF transmitter to probe the ionosphere for space weather studies. Finally, this CubeSat is equipped with several technological demonstrators (total solar irradiance sensors, UV sensors to measure solar spectral irradiance, a new Light Fidelity (Li-Fi) wireless communication system, a new versatile telecommunication system suitable for CubeSat). After introducing the objectives of the INSPIRE-SAT 7 mission, we present the satellite definition and the mission concept of operations. We also briefly show the observations made by the UVSQ-SAT CubeSat, and assess how two CubeSats in orbit could improve the information content of their Earth’s energy budget measurements. We conclude by reporting on the potential of future missions enabled by CubeSat constellations.

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Benson, Ilia, Adam Kaplan, James Flynn i Sharlene Katz. "Fault-Tolerant and Deterministic Flight-Software System For a High Performance CubeSat". International Journal of Grid and High Performance Computing 9, nr 1 (styczeń 2017): 92–104. http://dx.doi.org/10.4018/ijghpc.2017010108.

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

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

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

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

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

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Zanette, Luca, Leonardo Reyneri i Giuseppe Bruni. "Swarm system for CubeSats". Aircraft Engineering and Aerospace Technology 90, nr 2 (5.03.2018): 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 i Sang-Young Park. "Novel Structure and Thermal Design and Analysis for CubeSats in Formation Flying". Aerospace 8, nr 6 (26.05.2021): 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, nr 9 (4.09.2019): 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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Nayyar, Shivang, Sandeep Kumar i Vikas Suhag. "Earthquake Signature Detection Using Cubesat Technology". Journal of Advance Research in Electrical & Electronics Engineering (ISSN: 2208-2395) 1, nr 2 (28.02.2014): 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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Nakayama, Daisuke, Takashi Yamauchi, Hirokazu Masui, Sangkyun Kim, Kazuhiro Toyoda, Tharindu Lakmal Dayarathna Malmadayalage i Mengu Cho. "On-Orbit Experimental Result of a Non-Deployable 430-MHz-Band Antenna Using a 1U CubeSat Structure". Electronics 11, nr 7 (6.04.2022): 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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Chau, Vu Minh, i Hien Bich Vo. "Structural Dynamics Analysis of 3-U CubeSat". Applied Mechanics and Materials 894 (wrzesień 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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Nganpet Nzeugaing, Gutembert, i Elmarie Biermann. "Image compression system for a 3U CubeSat". Journal of Engineering, Design and Technology 14, nr 3 (4.07.2016): 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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Yuen, Brosnan, i Mihai Sima. "Low Cost Radiation Hardened Software and Hardware Implementation for CubeSats". Arbutus Review 9, nr 1 (25.09.2018): 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 i 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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Filho, Edemar Morsch, Laio Oriel Seman, Cezar Antônio Rigo, Vicente de Paulo Nicolau, Raúl García Ovejero i Valderi Reis Quietinho Leithardt. "Irradiation Flux Modelling for Thermal–Electrical Simulation of CubeSats: Orbit, Attitude and Radiation Integration". Energies 13, nr 24 (18.12.2020): 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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Cardillo, Emanuele, Renato Cananzi i Paolo Vita. "Wideband Versatile Receiver for CubeSat Microwave Front-Ends". Sensors 22, nr 22 (21.11.2022): 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 i 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 (21.09.2021): 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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OKINO, Satoshi, Shigeki UCHIYAMA, Kazuma SASE, Yuka IWAI, Kanako DAIGO, Nobuaki KINOSHITA, Sotaro HASHIGUCHI i 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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Hussain, Rifaqat, Khaled Aljaloud, Abida Shaheen Rao, Abdullah M. AlGarni, Ali H. Alqahtani, Abdul Aziz, Yosef T. Aladadi, Saad I. Alhuwaimel i Niamat Hussain. "Miniaturized Folded-Slot CubeSat MIMO Antenna Design with Pattern Diversity". Sensors 22, nr 20 (16.10.2022): 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, nr 1 (28.01.2019): 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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Poghosyan, Armen, i Alessandro Golkar. "CubeSat evolution: Analyzing CubeSat capabilities for conducting science missions". Progress in Aerospace Sciences 88 (styczeń 2017): 59–83. http://dx.doi.org/10.1016/j.paerosci.2016.11.002.

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Wang, Zhaocheng, i Enrique R. Vivoni. "Mapping Flash Flood Hazards in Arid Regions Using CubeSats". Remote Sensing 14, nr 17 (26.08.2022): 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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Yang, Weicai, Qing Chang, Allison Kealy, Yong Xu i Tianyi Lan. "A Novel Location-Awareness Method Using CubeSats for Locating the Spot Beam Emitters of Geostationary Communications Satellites". Mathematical Problems in Engineering 2018 (2018): 1–9. http://dx.doi.org/10.1155/2018/8035093.

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As more spacecraft are launched into the Geostationary Earth Orbit (GEO) belt, the possibility of fatal collisions or unnecessary interference between spacecraft increases. In this paper, a new location-awareness method that uses CubeSats is proposed to assist with radiofrequency (RF) domain verification by means of awareness and identification of the positions of the spot beam emitters of communications satellites in geostationary orbit. By flying a CubeSat (or a constellation of CubeSats) through the coverage area of a spot beam, the spot beam emitter’s position is identified and the spot beam’s pattern knowledge is characterized. The geometry, the equations of motion of the spacecraft, the measurement process, and the filtering equations in a location system are addressed with respect to the location methods investigated in this study. A realistic scenario in which a CubeSat receives signals from GEO communications satellites is simulated using the Systems Tool Kit (STK). The results of the simulation and the analysis presented in this study provide a thorough verification of the performance of the location-awareness method.

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Solís-Santomé, Arturo, Guillermo Urriolagoitia-Sosa, Beatriz Romero-Ángeles, Christopher Rene Torres-San Miguel, Jorge J. Hernández-Gómez, Isaac Medina-Sánchez, Carlos Couder-Castañeda, Jesús Irán Grageda-Arellano i Guillermo Urriolagoitia-Calderón. "Conceptual design and finite element method validation of a new type of self-locking hinge for deployable CubeSat solar panels". Advances in Mechanical Engineering 11, nr 1 (styczeń 2019): 168781401882311. http://dx.doi.org/10.1177/1687814018823116.

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Deployable mechanisms in CubeSat satellites have many problems with the system that provides the anchor position. The main defect of the traditional deployment mechanisms for solar panels in CubeSats is the lack of position system to block the back-driving of the panel when it reaches the final phase of the deployment. This generates spurious oscillations in the panel, affecting the photovoltaic process as well as generating fatigue in the mechanical elements of the mechanism (hinge or pin). In this work, the design, analysis and manufacture of a deployment mechanism for CubeSat solar panels is shown. A finite element method analysis was carried out in a hinge with an integrated blocking system as well as a double torsion spring, which can be used on CubeSats. The outcome shows the layout of the described anchor hinge and the used double-torsion spring, which provides a positive direction torque transfer. Likewise, the performed numerical analyses on the designed system, reduce the weight and optimise the geometry of the mechanism, showing its feasibility as well as the potential applications and further research in the area.

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Cook, Riley, Lukas Swan i Kevin Plucknett. "Impact of Test Conditions While Screening Lithium-Ion Batteries for Capacity Degradation in Low Earth Orbit CubeSat Space Applications". Batteries 7, nr 1 (15.03.2021): 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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Khramov, D. A. "Miniaturized satellites of Cubesat standard". Kosmìčna nauka ì tehnologìâ 15, nr 3 (30.05.2009): 20–31. http://dx.doi.org/10.15407/knit2009.03.020.

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YONEZU, Keiko, Hiroyuki SASAKI, Tsuyoshi NAGAO, Junichi NAKAO, Yuji NISHIHARA, Nobushiro MASAKI i Seiji KUROKI. "SokaUniversity CubeSat Project". Proceedings of the JSME annual meeting 2003.5 (2003): 353–54. http://dx.doi.org/10.1299/jsmemecjo.2003.5.0_353.

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PAHONIE, Radu Călin, Ciprian LARCO i Ștefan-Mircea MUSTAȚĂ. "ASPECTS ON A CUBESAT PROJECT". SCIENTIFIC RESEARCH AND EDUCATION IN THE AIR FORCE 20 (18.06.2018): 219–24. http://dx.doi.org/10.19062/2247-3173.2018.20.29.

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Gopal, Banala Krishna. "Atmospheric Data Collecting Cubesat using Raspberry PI". International Journal for Research in Applied Science and Engineering Technology 9, nr VI (30.06.2021): 3880–88. http://dx.doi.org/10.22214/ijraset.2021.35848.

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As advances in technology make payloads and instruments for space missions smaller, lighter, and more power efficient, a distinct segment market is emerging for low-cost missions on very small spacecrafts such as - micro, nano, and picosatellites. Due to the fact that even after many technological advances the usage of miniature satellites the remote sensing of atmospheric is still not a widely explored aspect, to overcome this we idealized a system to build a CUBESAT which can be built with minimal efforts. We proposed this system with an objective to build a CUBESAT to detect different weather aspects of our earth at the troposphere layer which is the lowest layer of earth. We implemented our project using the Raspberry Pi due to its versatility in multi-processing and connectivity. Here the Raspberry-Pi is going to be configured with transceiver modules in the CUBESAT’s sender-end to gather atmospheric data associated with temperature, gasses present, humidity and pressure using CUBESAT sensors and after the reception of data at ground station by Arduino configured as receiver, data is going to be stored in an accessible website for viewing and further computations.

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Lappas, Vaios, Nasir Adeli, Lourens Visagie, Juan Fernandez, Theodoros Theodorou, Willem Steyn i Matthew Perren. "CubeSail: A low cost CubeSat based solar sail demonstration mission". Advances in Space Research 48, nr 11 (grudzień 2011): 1890–901. http://dx.doi.org/10.1016/j.asr.2011.05.033.

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Madni, Mohamed Atef Ali, Saeid Iranmanesh i Raad Raad. "DTN and Non-DTN Routing Protocols for Inter-CubeSat Communications: A comprehensive survey". Electronics 9, nr 3 (14.03.2020): 482. http://dx.doi.org/10.3390/electronics9030482.

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CubeSats, which are limited by size and mass, have limited functionality. These miniaturised satellites suffer from a low power budget, short radio range, low transmission speeds, and limited data storage capacity. Regardless of these limitations, CubeSats have been deployed to carry out many research missions, such as gravity mapping and the tracking of forest fires. One method of increasing their functionality and reducing their limitations is to form CubeSat networks, or swarms, where many CubeSats work together to carry out a mission. Nevertheless, the network might have intermittent connectivity and, accordingly, data communication becomes challenging in such a disjointed network where there is no contemporaneous path between source and destination due to satellites’ mobility pattern and given the limitations of range. In this survey, various inter-satellite routing protocols that are Delay Tolerant (DTN) and Non Delay Tolerant (Non-DTN) are considered. DTN routing protocols are considered for the scenarios where the network is disjointed with no contemporaneous path between a source and a destination. We qualitatively compare all of the above routing protocols to highlight the positive and negative points under different network constraints. We conclude that the performance of routing protocols used in aerospace communications is highly dependent on the evolving topology of the network over time. Additionally, the Non-DTN routing protocols will work efficiently if the network is dense enough to establish reliable links between CubeSats. Emphasis is also given to network capacity in terms of how buffer, energy, bandwidth, and contact duration influence the performance of DTN routing protocols, where, for example, flooding-based DTN protocols can provide superior performance in terms of maximizing delivery ratio and minimizing a delivery delay. However, such protocols are not suitable for CubeSat networks, as they harvest the limited resources of these tiny satellites and they are contrasted with forwarding-based DTN routing protocols, which are resource-friendly and produce minimum overheads on the cost of degraded delivery probability. From the literature, we found that quota-based DTN routing protocols can provide the necessary balance between delivery delay and overhead costs in many CubeSat missions.

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Chanoui, Mohammed Alae, Issam Bouganssa, Mohammed Sbihi, Zine Elabidine Alaoui Ismaili i Adil Salbi. "Design and Simulation of a Median Filter for a CubeSat Image Processing Application Using an FPGA Architecture". ITM Web of Conferences 46 (2022): 04002. http://dx.doi.org/10.1051/itmconf/20224604002.

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CubeSats are small satellites that can perform space missions with the advantage of low cost and short development time. Earth observation is a well-known satellite use case that has found its place in the CubeSat community. To improve the quality and the number of images that can be received from the satellite, image processing techniques can be performed. Satellite images can be disturbed, and the median filter is a pre-processing technique usually used to remove impulse noise. The aim is to develop an architecture for CubeSat onboard image processing, starting with the design of a median filter. This paper presents the design and the simulation process of a 3x3 median filter based on the Spartan 6 FPGA architecture using software components. Simulation results are generated using a test bench algorithm and a visual comparison of both the input and output images is performed.

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Lokman, Abdul Halim, Ping Jack Soh, Saidatul Norlyana Azemi, Herwansyah Lago, Symon K. Podilchak, Suramate Chalermwisutkul, Mohd Faizal Jamlos, Azremi Abdullah Al-Hadi, Prayoot Akkaraekthalin i Steven Gao. "A Review of Antennas for Picosatellite Applications". International Journal of Antennas and Propagation 2017 (2017): 1–17. http://dx.doi.org/10.1155/2017/4940656.

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Cube Satellite (CubeSat) technology is an attractive emerging alternative to conventional satellites in radio astronomy, earth observation, weather forecasting, space research, and communications. Its size, however, poses a more challenging restriction on the circuitry and components as they are expected to be closely spaced and very power efficient. One of the main components that will require careful design for CubeSats is their antennas, as they are needed to be lightweight, small in size, and compact or deployable for larger antennas. This paper presents a review of antennas suitable for picosatellite applications. An overview of the applications of picosatellites will first be explained, prior to a discussion on their antenna requirements. Material and antenna topologies which have been used will be subsequently discussed prior to the presentation of several deployable configurations. Finally, a perspective and future research work on CubeSat antennas will be discussed in the conclusion.

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Areda, Eyoas Ergetu, Jose Rodrigo Cordova-Alarcon, Hirokazu Masui i Mengu Cho. "Development of Innovative CubeSat Platform for Mass Production". Applied Sciences 12, nr 18 (9.09.2022): 9087. http://dx.doi.org/10.3390/app12189087.

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With the recent increase in CubeSats’ ability to undertake complex and advanced missions, they are being considered for missions such as constellations, which demand high development efficiency. From a satellite interface perspective, productivity can be maximized by implementing a flexible modular structural platform that promotes easy reconfigurability during the integration and testing phase. Thus, the structural design of a CubeSat plays a crucial role in facilitating the satellite integration process. In most cases, the mechanical interface implemented between the primary load-supporting structure and internal satellite subassemblies affects the speed and efficiency of satellite integration by adding or reducing complexity. Most CubeSat structural designs use stacking techniques to mount PCBs onto the primary structure using stacking rods/screws. As a result, the internal subsystems are interconnected. This conventional interface method is observed to increase the number of structural parts, while increasing complexity during integration. In this study, flexible 3U and 1U CubeSat platforms are developed, based on the slot concept. This innovative mounting design provides a simple method of mounting PCBs into the slots. The concept is evaluated and verified for its feasibility for mass production applications. Count and complexity analysis is carried to evaluate the proposed design against the conventional type of structural interface methods. The assessment reveals that this new concept demonstrates a significant improvement in the efficiency of the mass production process.

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Nieto-Peroy, Cristóbal, i M. Reza Emami. "CubeSat Mission: From Design to Operation". Applied Sciences 9, nr 15 (1.08.2019): 3110. http://dx.doi.org/10.3390/app9153110.

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The current success rate of CubeSat missions, particularly for first-time developers, may discourage non-profit organizations to start new projects. CubeSat development teams may not be able to dedicate the resources that are necessary to maintain Quality Assurance as it is performed for the reliable conventional satellite projects. This paper discusses the structured life-cycle of a CubeSat project, using as a reference the authors’ recent experience of developing and operating a 2U CubeSat, called qbee50-LTU-OC, as part of the QB50 mission. This paper also provides a critique of some of the current poor practices and methodologies while carrying out CubeSat projects.

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Carrasco-Casado, Alberto, Koichi Shiratama, Dimitar Kolev, Phuc V. Trinh, Femi Ishola, Tetsuharu Fuse i Morio Toyoshima. "Development and Space-Qualification of a Miniaturized CubeSat’s 2-W EDFA for Space Laser Communications". Electronics 11, nr 15 (8.08.2022): 2468. http://dx.doi.org/10.3390/electronics11152468.

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The Japanese National Institute of Information and Communications Technology (NICT) is currently developing a high-performance laser-communication terminal for CubeSats aimed at providing a high-datarate communication solution for LEO satellites requiring transmission of large volumes of data from orbit. A key aspect of the communication system is a high-power optical amplifier capable of providing enough gain to the transmitted signals to be able to close the link on its counterpart’s receiver with the smallest impact in terms of energy and power on the CubeSat’s platform. This manuscript describes the development of a miniaturized 2-W space-grade 2-stage erbium-doped fiber amplifier (EDFA) compatible with the CubeSat form factor, showing the best power-to-size ratio for a space-qualified EDFA to the best of the authors’ knowledge. Performance results under realistic conditions as well as full space qualification and test are presented, proving that this module can support short-duration LEO-ground downlinks as well as long-duration intersatellite links.

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Cho, Dong-Hyun, Won-Sub Choi, Min-Ki Kim, Jin-Hyung Kim, Eunsup Sim i Hae-Dong Kim. "High-Resolution Image and Video CubeSat (HiREV): Development of Space Technology Test Platform Using a Low-Cost CubeSat Platform". International Journal of Aerospace Engineering 2019 (23.05.2019): 1–17. http://dx.doi.org/10.1155/2019/8916416.

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In this paper, we present high-resolution image and video CubeSat (HiREV), the first constructed 6 U platform to reach the space technology test bed stage, developed by the Korea Aerospace Research Institute (KARI). The CubeSat system is a low-cost platform that has been widely applied to various space missions, from missions involving earth observation to deep space. Despite the emergence of the CubeSat technology worldwide, the CubeSat market in Korea is still in the beginning stages, and a standard testing platform is also in demand. For this reason, KARI is starting to develop a 6 U CubeSat platform, which includes a less than 3 U bus system and greater than 3 U payload space. HiREV has been developed with locally manufactured parts, creating a domestic commercial off-the-shelf infrastructure for CubeSat and 3 m resolution camera payload development. Core flight software has also been applied as an on-board flight software system. Presently, we have developed the main system, while HiREV is under space environmental testing.

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Song, Young-Joo, Ho Jin i Ian Garick-Bethell. "Lunar CubeSat Impact Trajectory Characteristics as a Function of Its Release Conditions". Mathematical Problems in Engineering 2015 (2015): 1–16. http://dx.doi.org/10.1155/2015/681901.

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As a part of early system design activities, trajectory characteristics for a lunar CubeSat impactor mission as a function of its release conditions are analyzed. The goal of this mission is to take measurements of surface magnetic fields to study lunar magnetic anomalies. To deploy the CubeSat impactor, a mother-ship is assumed to have a circular polar orbit with inclination of 90 degrees at a 100 km altitude at the Moon. Both the in- and out-of-plane direction deploy angles as well as delta-Vmagnitudes are considered for the CubeSat release conditions. All necessary parameters required at the early design phase are analyzed, including CubeSat flight time to reach the lunar surface, impact velocity, cross ranges distance, and associated impact angles, which are all directly affected by the CubeSat release conditions. Also, relative motions between these two satellites are analyzed for communication and navigation purposes. Although the current analysis is only focused on a lunar impactor mission, the methods described in this work can easily be modified and applied to any future planetary impactor missions with CubeSat-based payloads.

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Hakima, Houman, i M. Reza Emami. "Deorbiter CubeSat mission design". Advances in Space Research 67, nr 7 (kwiecień 2021): 2151–71. http://dx.doi.org/10.1016/j.asr.2021.01.005.

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M, Muhaidheen, Muralidharan S i Vanaja N. "Multiport Converter for CubeSat". International Journal of Electrical and Electronics Research 10, nr 2 (30.06.2022): 290–96. http://dx.doi.org/10.37391/ijeer.100239.

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Maximizing solar energy harvesting and miniaturizing DC-to-DC converters will be a difficult task for the CubeSat that operates in low earth orbit (LEO), where size and weight are limited. To maximize solar energy collection, the electrical power system (EPS) architectures use numerous separate DC–DC converters, which will be problem for miniaturization of whole model because several inductors will be used in each converter. The key purpose of this article is to demonstrate a topology of multiport converter that requires only one inductor and a small number of components, reducing the overall system size. The proposed system will have half-bridge modules with series connection, connected parallelly with PV panels will power the battery system through a DC-DC boost converter. On considering the 1U CubeSat standards a prototype is used to verify the performance of the proposed converter in numerous case scenarios.

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Tsitas, S. R., i J. Kingston. "6U CubeSat commercial applications". Aeronautical Journal 116, nr 1176 (luty 2012): 189–98. http://dx.doi.org/10.1017/s0001924000006692.

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AbstractRecent work by Tsitas and Kingston(1)has demonstrated that an 8kg 6U CubeSat can be designed to perform Earth observation missions equivalent to those of 50-150kg microsatellites. Their design is reviewed and its commercial potential is compared to the 156kg RapidEye spacecraft. Three other commercial applications of this design are described. These are: a standard spacecraft for space scientists and astronomers; the spacecraft component of anNnation 5 spectral band disaster monitoring constellation and a night imaging satellite. Nanosatellites should now be considered for commercial missions previously thought to require microsatellites.

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Hakima, Houman, i M. Reza Emami. "Deorbiter CubeSat System Engineering". Journal of the Astronautical Sciences 67, nr 4 (16.07.2020): 1600–1635. http://dx.doi.org/10.1007/s40295-020-00220-5.

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Gorev, Vasily, Anatoly Pelemeshko, Alexander Zadorozhny i Aleksey Sidorchuk. "Thermal deformation of 3U CubeSat in low Earth orbit". MATEC Web of Conferences 158 (2018): 01013. http://dx.doi.org/10.1051/matecconf/201815801013.

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The impact of uneven heating on a satellite structure in low Earth orbit has been considered using the example of 3U CubeSat. The calculations showed that the thermal deformation of CubeSat structure in orbit caused a deviation between normals to opposite small satellite sides of about 0.03°. Such a deviation is commensurate with the required satellite pointing accuracy approximately 0.1° necessary for satellite laser communication. It means that to solve similar problems in the CubeSat designing that require such or better CubeSat pointing accuracy, it is necessary to take into account the expected satellite structure thermal deformation.

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Munoz-Martin, Joan Francesc, Lara Fernandez, Adrian Perez, Joan Adrià Ruiz-de-Azua, Hyuk Park, Adriano Camps, Bernardo Carnicero Domínguez i Massimiliano Pastena. "In-Orbit Validation of the FMPL-2 Instrument—The GNSS-R and L-Band Microwave Radiometer Payload of the FSSCat Mission". Remote Sensing 13, nr 1 (31.12.2020): 121. http://dx.doi.org/10.3390/rs13010121.

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The Flexible Microwave Payload-2 is the GNSS-R and L-band Microwave Radiometer Payload on board 3Cat-5/A, one of the two 6-unit CubeSats of the FSSCat mission, which were successfully launched on 3 September 2020 on Vega flight VV16. The instrument occupies nearly a single unit of the CubeSat, and its goal is to provide sea-ice extension and thickness over the poles, and soil moisture maps at low-moderate resolution over land, which will be downscaled using data from Cosine Hyperscout-2 on board 3Cat-5/B. The spacecrafts are in a 97.5° inclination Sun-synchronous orbit, and both the reflectometer and the radiometer have been successfully executed and validated over both the North and the South poles. This manuscript presents the results and validation of the first data sets collected by the instrument during the first two months of the mission. The results of the validation are showing a radiometric accuracy better than 2 K, and a sensitivity lower than the Kelvin. For the reflectometer, the results are showing that the sea-ice transition can be estimated even at short integration times (40 ms). The presented results shows the potential for Earth Observation missions based on CubeSats, which temporal and spatial resolution can be further increased by means of CubeSat constellations.

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Athirah, Nur, Mohd Afendi, Ku Hafizan, N. A. M. Amin i M. S. Abdul Majid. "Stress and Thermal Analysis of CubeSat Structure". Applied Mechanics and Materials 554 (czerwiec 2014): 426–30. http://dx.doi.org/10.4028/www.scientific.net/amm.554.426.

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This paper presents the stress and thermal analysis on the CubeSat structure to study the survivability of the CubeSat during the launching process or operating condition at the orbit is presented. Various design of mechanical structures were analyzed to determine the best design for different mission requirements. Analysis on the temperature of the batteries will be conducted as it is one of the most critical components that must operate in the required temperature to avoid failure of the CubeSat. ANSYS 13.0 was used to simulate both the structural and thermal analysis. Static structural was used to study the impact of G-force on the CubeSat during the launching process and Icepak was used to study the internal temperature. All of the result will be compiled in the table and comparisons were made among different designs to determine the advantages and disadvantages of each design. Results from simulation such as: safety factor, weight, internal available space and battery discharge rate were analyzed. From the findings, there is no best design in the CubeSat structure but only the most suitable design for the mission purposes. Battery discharge rate will play an important role to determine the requirement of heater in CubeSat.

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