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Journal articles on the topic 'Cubesat development'

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

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1

Menchinelli, Alessandro, Francesca Ingiosi, Ludovico Pamphili, Paolo Marzioli, Riccardo Patriarca, Francesco Costantino, and Fabrizio Piergentili. "A Reliability Engineering Approach for Managing Risks in CubeSats." Aerospace 5, no. 4 (November 15, 2018): 121. http://dx.doi.org/10.3390/aerospace5040121.

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Besides large-scale space missions, the spread of CubeSats for a variety of applications is increasingly requiring the development of systematic approaches for risk management. Being these applications are based on components with low TRL (Technology Readiness Level) or with limited performance data, it is required to define approaches which ensure a systematic perspective. This paper aims to present a reliability engineering approach based on FMECA (Failure Mode, Effects, and Criticality Analysis) to manage CubeSat reliability data and prioritize criticalities early in the design phase. The approach firstly proposes an alpha-numeric coding system to support the identification and labeling of failure modes for typical CubeSats’ items. Subsequently, each FMECA coefficient (i.e., Severity, Occurrence, Detectability) has been linked to the CubeSat’s structural properties, reducing subjectivity by means of techno-centric proxy indicators. The approach has been validated in the design phases of a 6-Units university CubeSat for the observation of M-Dwarf stars and binary systems. The performed analysis supported the design process and allowed to identify the major criticalities of the CubeSat design, as demonstrated in the extended case study included in the paper. The formalized method could be applied to design procedures for nano-satellites, as well as being expanded for research and development in a variety of space missions.
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Sibanda, Matthew, and Robert Ryk van Zyl. "Practical electromagnetic compatibility studies of a CubeSat." Journal of Engineering, Design and Technology 14, no. 4 (October 3, 2016): 770–80. http://dx.doi.org/10.1108/jedt-04-2014-0025.

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Purpose Incorporating electromagnetic compatibility (EMC) in the design life of traditional satellites is entrenched in the satellite industry. However, EMC treatment of CubeSats has not been widely pursued, for various possible reasons. CubeSats are a young technology platform initially intended for students and researchers at universities to create awareness and excitement amongst them for space technology. This and other factors limited the need for stringent EMC planning. As CubeSats mature in complexity, the success of future missions will rely on incorporating proper EMC designs in their development. This paper aims to address the experimental investigation of known EMC culprits within a CubeSat’s context. Design/methodology/approach Electromagnetic interference suppression effectiveness of cable trays in CubeSats, as well as crosstalk in high-speed/frequency data links, is investigated, using the PC/104 connector stack. Some recommendations for improving the EMC and, therefore, enhancing satellite mission success are provided. Findings It was found that, if physically feasible in the CubeSat, cable trays are significant radiation suppressors. A further investigation into crosstalk between pins of the PC/104 connector stack showed that grounding a pin in between two signal pins leads to a significant reduction in the coupled signal. Originality/value This paper addresses EMC within the context of a CubeSat and outlines experiments done resulting in cost-effective methods of reducing interference by using already available material (such as unused signal pins available in the PC/104 connector).
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3

SHIMAZU, Ryuya, Yusuke CHIBA, Hiroka KANEI, Hiroki WATARI, Ikuma NISHIKAWA, and Toshihiro KAMEDA. "D03 Development of CubeSat "YUI"." Proceedings of the Space Engineering Conference 2013.22 (2013): _D03–1_—_D03–5_. http://dx.doi.org/10.1299/jsmesec.2013.22._d03-1_.

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4

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

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5

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

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6

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

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

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

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During satellite development, engineers need to simulate and understand the satellite’s behavior in orbit and minimize failures or inadequate satellite operation. In this sense, one crucial assessment is the irradiance field, which impacts, for example, the power generation through the photovoltaic cells, as well as rules the satellite’s thermal conditions. This good practice is also valid for CubeSat projects. This paper presents a numerical tool to explore typical irradiation scenarios for CubeSat missions by combining state-of-the-art models. Such a tool can provide the input estimation for software and hardware in the loop analysis for a given initial condition and predict it along with the satellite’s lifespan. Three main models will be considered to estimate the irradiation flux over a CubeSat, namely an orbit, an attitude, and a radiation source model, including solar, albedo, and infrared emitted by the Earth. A case study illustrating the tool’s abilities is presented for a typical CubeSats’ two-line element set (TLE) and five attitudes. Finally, a possible application of the tool as an input to a CubeSat task-scheduling is introduced. The results show that the complete model’s use has considerable differences from the simplified models sometimes used in the literature.
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9

Cho, Dong-Hyun, Won-Sub Choi, Min-Ki Kim, Jin-Hyung Kim, Eunsup Sim, and Hae-Dong Kim. "High-Resolution Image and Video CubeSat (HiREV): Development of Space Technology Test Platform Using a Low-Cost CubeSat Platform." International Journal of Aerospace Engineering 2019 (May 23, 2019): 1–17. http://dx.doi.org/10.1155/2019/8916416.

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

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11

Lee, Jeongho, Seongwhan Lee, JungKyu Lee, Hyojeong Lee, Jehyuck Shin, Seonyeong Jeong, YoungSeok Oh, and Ho Jin. "Development of Flight Software for SIGMA CubeSat." Journal of the Korean Society for Aeronautical & Space Sciences 44, no. 4 (April 1, 2016): 363–72. http://dx.doi.org/10.5139/jksas.2016.44.4.363.

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12

Han, Sanghyuck, Yeonju Choi, Dong-Hyun Cho, Won-Sub Choi, Hyeon Cheol Gong, Hae-Dong Kim, and Gi-Hyuk Choi. "Analysis of Cubesat Development Status in Korea." Journal of the Korean Society for Aeronautical & Space Sciences 45, no. 11 (November 30, 2017): 975–88. http://dx.doi.org/10.5139/jksas.2017.45.11.975.

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Ito, Tomonori, Satoshi Ota, Takuya Kamei, Shinya Sugai, Yusuke Takeuchi, Shin Satori, Kazuhisa Chiba, Masami Sasaki, and Ryuichi Mitsuhashi. "D02 Development of multi spectral camera for CubeSat." Proceedings of the Space Engineering Conference 2013.22 (2013): _D02–1_—_D02–4_. http://dx.doi.org/10.1299/jsmesec.2013.22._d02-1_.

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14

Céspedes, Jorge Enrique Salamanca, and Roberto Ferro Escobar. "Diseño e Implementacion de un Modulo de Gestion de Energia para un Pico-Satelite Tipo Cubesat." KnE Engineering 3, no. 1 (February 11, 2018): 913. http://dx.doi.org/10.18502/keg.v3i1.1512.

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This article briefly describes the development of Power Module for Experimental picosatellite CubeSat UD Colombia 1 following CubeSat standard requirements. Whether the Power Module project consists of four stages of development: study, design, implementation and testing. In the study phase to review the theoretical framework and preliminary designs made in the Universidad Distrital and other CubeSat developed in the world, also investigates existing components and technologies in the market. The design phase involves analysis of the system and using a computer program designed to generate the necessary hardware. The implementation consists in making the printed circuit board and the component assembly. And electrical type tests to certify the proper operation of the module. The development of the power module of the CubeSat standard requirements and mission picosatellite, and depends on the state and information available from other modules picosatellite. The ultimate goal is to obtain a power module that is functional and working conditions of the space environment in which the picosatellite fulfill its focused on telemedicine, with a payload that would become the telecommunications system mission. Keywords: Power Module, CubeSat UD Colombia 1, Standard CubeSat, DC-DC converters, Solar Panels, Batteries, Power Management.
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Walsh, Sarah, David Murphy, Maeve Doyle, Jack Reilly, Joseph Thompson, Rachel Dunwoody, Jessica Erkal, et al. "Development of the EIRSAT-1 CubeSat through Functional Verification of the Engineering Qualification Model." Aerospace 8, no. 9 (September 8, 2021): 254. http://dx.doi.org/10.3390/aerospace8090254.

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The Educational Irish Research Satellite (EIRSAT-1) is a 2U CubeSat developed at University College Dublin. The project aims to build, test, launch, and operate Ireland’s first satellite and to perform in-orbit demonstrations of three novel payloads developed in-house. To reduce risk within the mission, the project employs a prototype model philosophy in which two models of the spacecraft exist: an engineering qualification model (EQM) and a flight model (FM). This paper presents the verification approach of the functional tests implemented for the EIRSAT-1 project. The activities of the FlatSat and system level full functional tests of the EQM are presented and the results obtained during the test campaigns are discussed. Four test anomalies were encountered during the full functional test campaign resulting in two minor redesigns, and subsequent reassembly, of the CubeSat. The functional test campaigns highlighted the importance of FlatSat level testing of CubeSats to ensure compatibility of all subsystems prior to assembly and of thorough documentation to diagnose any unexpected behaviour of the hardware efficiently. The functional verification of the EQM proved that the system conformed to its design, verifying 57 mission requirements, and is a crucial step towards the development of the EIRSAT-1 FM.
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Nieto-Peroy, Cristóbal, and M. Reza Emami. "CubeSat Mission: From Design to Operation." Applied Sciences 9, no. 15 (August 1, 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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Ivansyah, Muhammad Dzaky, Edwar Edwar, Nachwan Mufti Adriansyah, Harfan Hian Ryanu, and Dhoni Putra Setiawan. "Development of a CubeSat Single Channel LoRa Receiver Module for Space-based IoT Application." Journal of Measurements, Electronics, Communications, and Systems 8, no. 1 (June 30, 2021): 8. http://dx.doi.org/10.25124/jmecs.v8i1.3950.

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CubeSat attracts many researchers due to its low production and deployment cost. One of the application is implemented in low data rate communication or machine to machine (M2M) with IoT devices in remote areas such as islands, forests, and mountains. In this study, a CubeSat receiver for IoT communication in remote areas has been developed and realized. A LoRa SX1276 chip is used for processing passband signals captured by the antenna. The device has a amplifier gain of 20.92 dB, 390 mW power consumption, and operating frequency of 923 MHz. The developed CubeSat is expected to provide a low bit rate of 5468.750 bps for SF 7 and 292.969 for SF 12 , the receiver serves as a concentrator for monitoring devices in rural areas.
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Monteiro, João P., Rui M. Rocha, Alexandre Silva, Rúben Afonso, and Nuno Ramos. "Integration and Verification Approach of ISTSat-1 CubeSat." Aerospace 6, no. 12 (December 1, 2019): 131. http://dx.doi.org/10.3390/aerospace6120131.

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Large-scale space projects rely on a thorough Assembly, Integration, and Verification (AIV) process to provide the upmost reliability to spacecraft. While this has not traditionally been the case with CubeSats, their increasing role in space science and technology has led to new verification approaches, including in educational CubeSats. This work describes the integration and verification approach for ISTSat-1, which is an educational CubeSat from the Instituto Superior Técnico in Portugal that partially discards the typical stage-gate approach to spacecraft development in favor of a more iterative approach, allowing for the system-level verification of unfinished prototypes. Early verification included software functional testing on a flatsat model, thermal vacuum and vibration testing on a battery model, ionizing radiation testing on the on-board computer, and non-ionizing radiation (EMC) testing on all subsystems. The testing of functional prototypes at an early development stage led to uncovering system-level errors that would typically require hardware redesign at a later project stage. The team considers the approach to be useful for educational projects that employ a small, co-located team with low non-recurring engineering costs.
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Filho, Antonio Cassiano Julio, Auro Tikami, Elaine de Souza Ferreira de Paula, Jhonathan Murcia Piñeros, George Favale Fernandes, Lázaro Aparecido Pires Camargo, Carlos Alberto Monteiro Barbosa dos Santos, Walter Abrahão dos Santos, and Kleber Pinheiro Naccarato. "CubeSat Development for Lightning Flashes Detection: RaioSat Project." Journal of Aerospace Technology and Management, no. 12 (November 21, 2020): 80–93. http://dx.doi.org/10.5028/jatm.cab.1161.

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Annually, severe weather phenomena are responsible for tens of thousands of deaths and tens of billions of dollars of damage around the world. In Brazil, unlike other hydrometeorological events, severe atmospheric events are random and, therefore, do not have a sociospatial pattern. Because of that, there is a significant motivation to improve the prediction techniques for this kind of events, using high resolution numerical models. A large amount of high-quality observational data is required, including lightning data in a very short-range. In addition, the detection of lightning flashes produced by storms is important for a wide variety of applications and in some areas of scientific research, which include the understanding of the human action on the climate and how the climate change can affect the behavior of storms in long range. One method to monitor the lightning flashes is the implementation of sensors in satellites to obtain data. In this sense, the objective of the RaioSat project is to develop national technology for detecting lightning flashes from the space, in order to complement the existing data from the ground detection network, BrasilDAT. The main objective of this article is to present a methodology for the development of the RaioSat mission including some parts of the preliminary design and operational modes. Additionally, the article describes the expected results and the continuity of the project and a preliminary analysis of a constellation for future projects.
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Kim, Jongbum, Youeyun Jung, Yeerang Lim, Hyochoong Bang, and Mikael Marin. "Development and Verification for Flight Model of CubeSat LINK." Journal of the Korean Society for Aeronautical & Space Sciences 45, no. 2 (February 1, 2017): 114–23. http://dx.doi.org/10.5139/jksas.2017.45.2.114.

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Gordon, R., A. Leibak, P. Org, E. Priidel, A. Rassõlkin, and T. Vaimann. "ADCS development for student CubeSat satellites – TalTech case study." Proceedings of the Estonian Academy of Sciences 70, no. 3 (2021): 268. http://dx.doi.org/10.3176/proc.2021.3.06.

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22

Isharuddin, Siti Sarah, Mohamed Okasha, and Sultan Ibrahim. "IIUM CubeSat Structural Subsystem Design." Advanced Materials Research 1115 (July 2015): 568–72. http://dx.doi.org/10.4028/www.scientific.net/amr.1115.568.

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This paper investigates the development process of a CubeSat model structure subsystem for the International Islamic University Malaysia (IIUM). Many universities around the world have participated in similar CubeSat satellite projects. CubeSat satellite enables to design and produce a fully functional satellite at low cost compared to other types of satellites. It gives the engineering students especially the aerospace one, a hands-on education, and learning about how to design their own satellite. This paper will discuss the procedures that can be used to design and test the CubeSat structure subsystem considering design goals and constraints. The analyses will consider the structure static and vibration tests utilizing ANSYS Workbench platform and SolidWorks software and the simulation results will be compared with the experimental test results on the physical model.
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Chen, Zhiyong. "Universal CubeSat Platform Design Technique." MATEC Web of Conferences 179 (2018): 01002. http://dx.doi.org/10.1051/matecconf/201817901002.

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This article summarizes cubesat technology, provides examples of their scientific impact, and describes the design and the manufacturing of a Cubesat platform. As for the design of the overall frame structure of the CubeSat, we have searched a lot of literature and consulted many predecessors' designs, and collected many satellite structure images. After analyzing the data, we aimed at all kinds of different structures’ advantages and disadvantages, finally we got a best design. It is a satellite of cubic shape (10 cm per side), weighing approximately 1kg, based on the creation of a central body made of different material using the 3D-Printing techniques. The 3D-Printing technique has several advantages including fast implementation, accuracy in manufacturing small parts and low cost. Moreover, concerning the construction of a small satellite, this technique is very useful thanks to the accuracy achievable in details, which are sometimes difficult and expensive to realize with the use of tools machine. The structure must be able to withstand the launch loads. For this reason, several simulations using an FEM simulation and an intensive vibration test campaign will be performed in the system development and test phase.
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Bhattarai, Shankar, Hongrae Kim, Sung-Hoon Jung, and Hyun-Ung Oh. "Development of Pogo Pin-Based Holding and Release Mechanism for Deployable Solar Panel of CubeSat." International Journal of Aerospace Engineering 2019 (May 5, 2019): 1–13. http://dx.doi.org/10.1155/2019/2580865.

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CubeSats are revolutionary to the space industry and are transforming space exploration which enables the next generation of scientists and engineers to complete all phases of space missions. Deployable solar panels have been widely used for the generation of enough power in CubeSats due to their limited volume area for solar cell integration. In general, the cable cutting release mechanism have been used in 1U-3U small satellites because of its simplicity and low cost. However, this mechanism has a low constraint force and is unable to apply constraints along the in-plane and out-of-plane directions. In this study, for the improvement of the conventional cable cutting mechanism, a spring-loaded pogo pin-based nichrome burn wire holding and release mechanism (HRM) was proposed and fabricated. The pogo pin constitutes an immensely attractive function for the holding and release mechanism of solar panels because it works as an electrical interface to provide power, a separation spring to initiate the reaction force to deploy the panels, and a status switch to determine deployments. In addition, the proposed mechanism guarantees the loading capability along the in-plane and out-of-plane directions of solar panels, the synchronous release of multiple panels, and a handling simplicity that differentiates it from the conventional mechanism. The design feasibility, structural safety, and reliability of the mechanism were verified through functionality tests and launch and on-orbit environmental tests. The proposed pogo pin-based holding and release mechanism would be equally applicable for other CubeSat deployable appendages.
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Romero, Alessandro Gerlinger, and Luiz Carlos Gadelha De Souza. "Stability Evaluation of the SDRE Technique based on Java in a CubeSat Attitude and Orbit Control Subsystem." WSEAS TRANSACTIONS ON SYSTEMS 20 (January 29, 2021): 1–8. http://dx.doi.org/10.37394/23202.2021.20.1.

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In 2013, the STRaND (University of Surrey and Surrey Satellite Technology Ltd) and the PhoneSat (NASA) programs attracted the attention of the aerospace community applying commercial off-the-shelf smartphones in CubeSats. Both programs deployed CubeSats using smartphones based on Google's Android, in which application development is mainly based on Java programming language. Some of these CubeSats had actuators, e.g., STRaND-1 had three reaction wheels mounted in an orthogonal configuration to provide three-axis control, whereas PhoneSat 2.0 beta had magnetorquers to de-tumble the spacecraft. Taking into account a CubeSat that runs Android operating system (based on a smartphone), it is natural to evaluate the attitude and orbit control subsystem (AOCS) based on Java. Elsewhere, we shown State-Dependent Riccati Equation (SDRE) is a feasible non-linear control technique that can be applied in such CubeSats using Java. Moreover, we shown, through simulation using a Monte Carlo perturbation model, SDRE provides better performance than the PID controller, a linear control technique. In this paper, we tackle the next fundamental problem: stability. We evaluate stability from two perspectives: (1) parametric uncertainty of the inertia tensor and (2) a Monte Carlo perturbation model based on a uniform attitude probability distribution. Through the combination of these two perspectives, we grasp the stability properties of SDRE in a broader sense. In order to handle the uncertainty appropriately, we combine SDRE with H∞. The Nanosatellite Constellation for Environmental Data Collection (CONASAT), a CubeSat from the Brazilian National Institute for Space Research (INPE), provided the nominal parameters for the simulations. The initial results of the simulations shown that the SDRE controller is stable to ± 20% uncertainty in the inertia tensor for attitudes uniformly distributed and angular velocity up to 0.15 radians/second.
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Malygin, I. V., A. S. Karamyshev, and S. S. Blinov. "The development of automatic expandable microwave antennas for CubeSat satellites." Ural Radio Engineering Journal 3, no. 1 (2019): 30–42. http://dx.doi.org/10.15826/urej.2019.3.1.002.

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Oberholzer, J. F., E. H. Uheida, and G. A. Oosthuizen. "Resource Efficient Process Chain Development of a Modular CubeSat Spaceframe." Procedia Manufacturing 35 (2019): 917–28. http://dx.doi.org/10.1016/j.promfg.2019.06.037.

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Konoue, Kazuya, Hirotaka Sawada, Koji Nakaya, Kyoichi Ui, Shingo Tsurumi, Osamu Mori, and Saburo Matunaga. "F-1528 Development of TITech CubeSat 2001 : an orbital satellite." Proceedings of the JSME annual meeting IV.01.1 (2001): 369–70. http://dx.doi.org/10.1299/jsmemecjo.iv.01.1.0_369.

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Mahesh Babu, T. S., Vivek George Koshy, and D. Bharath. "Thermal and Vibrational Analysis of Cubesat." Applied Mechanics and Materials 766-767 (June 2015): 1091–96. http://dx.doi.org/10.4028/www.scientific.net/amm.766-767.1091.

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There has been a recent increase in emphasis on small satellite because of their low cost, short development time’s relative simplicity, and cost efficiency. However, these satellites do have drawback. Their small size results in small surface areas which often translate into thermal and power constraint. A satellite basically any object that revolves around a planet in a circular or elliptical orbit path. nanosatellites are satellites that weigh less than 10Kg. These types of satellites are designed and developed to carry payloads that are much smaller and has a life span not more than 1 year generally. The below analysis is done on a Low Earth Orbiting Satellite.
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Ampatzoglou, Andreas, and Vassilis Kostopoulos. "Design, Analysis, Optimization, Manufacturing, and Testing of a 2U Cubesat." International Journal of Aerospace Engineering 2018 (June 12, 2018): 1–15. http://dx.doi.org/10.1155/2018/9724263.

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The design optimization, development, and verification by analysis and testing of the 1st Greek cubesat, developed by the University of Patras and Libre Space Foundation (UPSat (University of Patras Satellite)), is presented. The key innovative approach includes the replacement of the aluminum side faces with structural composite components, keeping the commonly used aluminum frame. A “hybrid” double-unit (2U) cubesat structure was optimized, built, and tested for all launch and thermal loads/specifications required for launch and mission operations as imposed from the EU-funded FP7-QB50 project. Results show that the new design of the structure using CFRP can offer similar levels of performance in terms of stiffness, while saving 30% of the mass, for the entire cubesat platform.
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Song, Sua, Hongrae Kim, and Young-Keun Chang. "Design and Implementation of 3U CubeSat Platform Architecture." International Journal of Aerospace Engineering 2018 (December 24, 2018): 1–17. http://dx.doi.org/10.1155/2018/2079219.

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This paper describes the main concept and development of a standard platform architecture of 3U Cube Satellite, whose design and performance were implemented and verified through the development of KAUSAT-5 3U CubeSat. The 3U standard platform is built in 1.5U size and developed as a modular concept to add and expand payloads and attitude control actuators to meet the user’s needs. In the case of the electrical power system, the solar panel, the battery, and the deployment mechanism are designed to be configured by the user. Mechanical system design maximizes the electrical capability to accommodate various payloads and to integrate and miniaturize EEE (Electrical, Electronic, and Electromechanical) parts and subsystem functions/performance into limited-size PCBs. The performance of KAUSAT-5 adopting standard platform was verified by mounting the VSCMG (Variable Speed Control Moment Gyro), which is one payload for technical demonstration, at the bottom of the platform and the infrared (IR) camera, which is the other payload for science mission, on the top. The 3U CubeSat equipped with the electronic optical camera is under development implementing the standard platform to reduce development cost and schedule by minimizing additional verification.
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32

Meftah, Mustapha, Thomas Boutéraon, Christophe Dufour, Alain Hauchecorne, Philippe Keckhut, Adrien Finance, Slimane Bekki, et al. "The UVSQ-SAT/INSPIRESat-5 CubeSat Mission: First In-Orbit Measurements of the Earth’s Outgoing Radiation." Remote Sensing 13, no. 8 (April 8, 2021): 1449. http://dx.doi.org/10.3390/rs13081449.

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UltraViolet & infrared Sensors at high Quantum efficiency onboard a small SATellite (UVSQ-SAT) is a small satellite at the CubeSat standard, whose development began as one of the missions in the International Satellite Program in Research and Education (INSPIRE) consortium in 2017. UVSQ-SAT is an educational, technological and scientific pathfinder CubeSat mission dedicated to the observation of the Earth and the Sun. It was imagined, designed, produced and tested by LATMOS in collaboration with its academic and industrial partners, and the French-speaking radioamateur community. About the size of a Rubik’s Cube and weighing about 2 kg, this satellite was put in orbit in January 2021 by the SpaceX Falcon 9 launch vehicle. After briefly introducing the UVSQ-SAT mission, this paper will present the importance of measuring the Earth’s radiation budget and its energy imbalance and the scientific objectives related to its various components. Finally, the first in-orbit observations will be shown (maps of the solar radiation reflected by the Earth and of the outgoing longwave radiation at the top of the atmosphere during February 2021). UVSQ-SAT is one of the few CubeSats worldwide with a scientific goal related to climate studies. It represents a research in remote sensing technologies for Climate observation and monitoring.
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33

Park, Tae-Yong, Bong-Geon Chae, and Hyun-Ung Oh. "Development of 6 U CubeSat’s Deployable Solar Panel with Burn Wire Triggering Holding and Release Mechanism." International Journal of Aerospace Engineering 2019 (April 30, 2019): 1–13. http://dx.doi.org/10.1155/2019/7346436.

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In the present work, a deployable solar panel based on a burn wire triggering holding and release mechanism was developed for use of 6 U CubeSat. The holding and release mechanism was designed based on a nichrome burn wire cutting method widely used for CubeSat applications. However, it provides a high loading capability, reliable wire cutting, multiplane constraints, and handling simplicity during the tightening process of wire. A demonstration model of a printed circuit board-based solar panel stiffened by a high-pressure fiberglass-laminated G10 material was fabricated and tested to validate the effectiveness of the design and functionality of the mechanism under various test conditions. The structural safety of the solar panel combined with the mechanism in a launch vibration environment was verified through sine and random vibration tests at qualification level.
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34

Perdomo, César A., Julián R. Camargo, and Albeiro Cortes Cabezas. "On Board Computer Module for Cubesat Compatible with QB50." Modern Applied Science 12, no. 12 (November 26, 2018): 206. http://dx.doi.org/10.5539/mas.v12n12p206.

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This paper presents the design and implementation at the hardware level of the OBC-OBDH subsystem (On-Board-Computer On-Board Data Handler) to meet the requirements of the CubeSat QB50 project, in addition, different tasks are performed at the software level to simplify the subsequent development (the implementation of the FreeRTOS real-time operating system has been carried out, and a simple example has been prepared that involves the use of all the necessary modules). The development of this module is justifiable at an academic level, since the QB50 project impacts on different aspects the academy (development of satellite systems), it must be taken into account that the QB50 challenge is presented to all the universities of the world and has a great impact on third world countries, providing the possibility of massive development and low launch costs.
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35

Kang, Soo-Jin, and Hyun-Ung Oh. "On-Orbit Thermal Design and Validation of 1 U Standardized CubeSat of STEP Cube Lab." International Journal of Aerospace Engineering 2016 (2016): 1–17. http://dx.doi.org/10.1155/2016/4213189.

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The Cube Laboratory for Space Technology Experimental Projects (STEP Cube Lab) is a cube satellite (CubeSat) classified as a pico-class satellite of 1 U (unit) size. Its main mission objective is to exploit core space technologies researched by domestic universities and verify the effectiveness of these technologies through on-orbit tests using the CubeSat. To guarantee a successful mission under extreme space thermal environments, proper thermal design is important. This paper describes the development process undertaken in the thermal design of the STEP Cube Lab, based on a passive approach, and its validation test. The system functionality and thermal design were verified through thermal vacuum and thermal balance tests under space simulated thermal vacuum environment condition. Finally, the orbital temperature of each component was predicted using a highly reliable correlated thermal mathematical model of the CubeSat obtained from the thermal balance test.
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36

Song, Sua, Soo-Yeon Lee, Hong-Rae Kim, and Young-Keun Chang. "KAUSAT-5 Development and Verification based on 3U Cubesat Standard Platform." Journal of the Korean Society for Aeronautical & Space Sciences 45, no. 8 (August 31, 2017): 686–96. http://dx.doi.org/10.5139/jksas.2017.45.8.686.

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37

Shravanth, Gelli Kusal Venkata Sai. "Design and Development of a Low Cost Ground System for CubeSat." International Journal for Research in Applied Science and Engineering Technology 9, no. 1 (January 31, 2021): 867–75. http://dx.doi.org/10.22214/ijraset.2021.32948.

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38

OHKAWA, Yusuke, Hiroyuki TSUKAMOTO, Masataka HIRAJO, Yohei HAMAMOTO, Akihito KARIYA, and Yasuyuki MIYAZAKI. "The overview of the development of micro satellite CubeSat in Nihon University." Proceedings of the JSME annual meeting 2002.1 (2002): 321–22. http://dx.doi.org/10.1299/jsmemecjo.2002.1.0_321.

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39

Chahat, Nacer, Richard E. Hodges, Jonathan Sauder, Mark Thomson, Eva Peral, and Yahya Rahmat-Samii. "CubeSat Deployable Ka-Band Mesh Reflector Antenna Development for Earth Science Missions." IEEE Transactions on Antennas and Propagation 64, no. 6 (June 2016): 2083–93. http://dx.doi.org/10.1109/tap.2016.2546306.

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NAKAYA, Jun, Taku TAKADA, Yoshihiro KAJIMURA, Kentarou KITAMURA, Shinya UETA, Hana TSUCHIYA, Namiki UEZONO, and Yui SASAOKA. "Development and Application of a CubeSat Ground Model for Space Technology Education." Journal of JSEE 67, no. 2 (2019): 2_101–2_106. http://dx.doi.org/10.4307/jsee.67.2_101.

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UEZONO, Namiki, Yui SASAOKA, Jun NAKAYA, Hana TSUCHIYA, Yoshihiro KAJIMURA, Kentarou KITAMURA, Shinya UETA, and Taku TAKADA. "Development and Application of a CubeSat Ground Model for Space Technology Education." Journal of JSEE 67, no. 2 (2019): 2_95–2_100. http://dx.doi.org/10.4307/jsee.67.2_95.

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42

O'Neill, Josh, Nadja Bressan, Grant McSorley, and Nicholas Krouglicof. "Development of a high-accuracy low-cost sun sensor for CubeSat application." Aeronautics and Aerospace Open Access Journal 4, no. 3 (September 29, 2020): 142–46. http://dx.doi.org/10.15406/aaoaj.2020.04.00115.

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43

Castillo, Joel A., Jorge Flores-Troncoso, Rigoberto Jáuregui, Jorge Simón, and José L. Alvarez-Flores. "Signal Conditioning Stage in S-Band Communication Subsystem for CubeSat Applications." Electronics 10, no. 14 (July 7, 2021): 1627. http://dx.doi.org/10.3390/electronics10141627.

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This work presents the design, performance evaluation, manufacture, and characterization of an RF front-end signal conditioning chain on a substrate that achieves the best performance at S-band frequencies and complies with the dimensions of the international standard for CubeSat-type nanosatellites. In this development, the signal conditioning chains were carried out on the high-frequency substrates RO4350B, CuClad 250, and RT/duroid 5880, considering scattering parameters in a small-signal regime. Concerning the power output, after the filtering and amplifying stages, the conditioning chain delivered 2 watts at 2.25 GHz. Moreover, up to 40 dB gain was achieved, and a good impedance matching at −20 dB for both input and output ports was observed. The numerical simulations and experimental results showed that an RO4350B substrate allows the smallest design dimensions, and these comply with the dimensions of the CubeSat standard. The manufactured RF front-end signal conditioning chain on RO4350B requires an area of 95 mm2, and it is ready to be used in a proof-of-concept space mission in a CubeSat.
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44

J. Schuch, Nelson, Otávio S. C. Durão, Marlos R. da Silva, Fátima Mattiello-Francisco, João B. dos S. Martins, Andrei P. Legg, André L. da Silva, and Eduardo E. Bürguer. "THE NANOSATC-BR, CUBESAT DEVELOPMENT PROGRAM – A JOINT CUBESAT PROGRAM DEVELOPED BY UFSM AND INPE/MCTIC – SPACE GEOPHYSICS MISSION PAYLOADS AND FIRST RESULTS." Brazilian Journal of Geophysics 37, no. 1 (March 23, 2019): 95. http://dx.doi.org/10.22564/rbgf.v37i1.1992.

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ABSTRACT. The INPE-UFSM’s NANOSATC-BR, CubeSats Development Program started in 2008. Currently, the Program counts with two CubeSats: the NANOSATC-BR1 (1U) launched in 2014 and still in operation & the NANOSATC-BR2 (2U), under development, which is expected to be launched in the last quarter of 2019. In this article, the scientific and technological results of the NANOSATC-BR1 and the finalization of NANOSATC-BR2 are presented. Considering the Capacity Building, the major target of the Program, the paper emphasizes the involvement of Universidade Federal de Santa Maria - UFSM undergraduate/graduate students in the conception, development and operation of NANOSATC-BR1, as well as the participation of the Instituto Nacional de Pesquisas Espaciais - INPE graduate students in the onboard data handling (OBDH) software subsystem development, verification and validation for the NANOSATC-BR2. In addition, the collaborations of other Space Science, Engineering and Computer Science institutions involved in Brazil and abroad are discussed. The Program has received financial support from the Brazilian Space Agency (AEB) and the Ministry of Science, Technology, Innovation and Communications (MCTIC). Keywords: cubesats, nanosatellites, capacity building. RESUMO. O programa NANOSATC-BR, Desenvolvimento de CubeSats, parceria INPE – UFSM, teve início em 2008. Atualmente, o Programa conta com dois CubeSats: o NANOSATC-BR1 (1U), lançado em 2014 e ainda em operação, e o NANOSATC-BR2 (2U), que está em desenvolvimento e tem expectativa de lançamento no último trimestre de 2019. Nesse artigo, a finalização do desenvolvimento do NANOSATC-BR2 e os resultados científicos e tecnológicos do NANOSATC-BR1 são apresentados. Considerando a Capacitação Profissional, o maior objetivo do Programa, o artigo dá ênfase ao envolvimento dos alunos de graduação na concepção, desenvolvimento e operação do NANOSATC-BR1, ao mesmo tempo em que enfatiza a participação dos alunos de pós-graduação do INPE no desenvolvimento, verificação e validação do Subsistema de Computador de Bordo para o NANOSATC-BR2. Além disso, colaborações de outras instituições de Ciência Espacial, Engenharia e Institutos de computação aplicada do Brasil e Exterior, são igualmente discutidas. O Programa recebeu suporte financeiro da Agência Espacial Brasileira (AEB) e do Ministério da Ciência, Tecnologia, Inovações e Comunicações (MCTIC). Palavras-chave: cubesats, nanosatélites, formação de recursos humanos.
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45

Bhattarai, Shankar, Ji-Seong Go, Hongrae Kim, and Hyun-Ung Oh. "Development of a Novel Deployable Solar Panel and Mechanism for 6U CubeSat of STEP Cube Lab-II." Aerospace 8, no. 3 (March 5, 2021): 64. http://dx.doi.org/10.3390/aerospace8030064.

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The structural safety of solar cells mounted on deployable solar panels in the launch vibration environment is a significant aspect of a successful CubeSat mission. This paper presents a novel highly damped deployable solar panel module that is effective in ensuring structural protection of solar cells under the launch environment by rapidly suppressing the vibrations transmitting through the solar panel by constrained layer damping achieved using printed circuit board (PCB)-based multilayered thin stiffeners with double-sided viscoelastic tapes. A high-damping solar panel demonstration model with a three-pogo pin-based burn wire release mechanism was fabricated and tested for application in the 6U CubeSat “STEP Cube Lab-II” developed by Chosun University, South Korea. The reliable release function and radiation hardness assurance of the mechanism in an in-orbit environment were confirmed by performing solar panel deployment tests and radiation tests, respectively. The design effectiveness and structural safety of the proposed solar panel module were validated by launch vibration and in-orbit environment tests at the qualification level.
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46

John, Aji, Justin Ong, Elli J. Theobald, Julian D. Olden, Amanda Tan, and Janneke HilleRisLambers. "Detecting Montane Flowering Phenology with CubeSat Imagery." Remote Sensing 12, no. 18 (September 7, 2020): 2894. http://dx.doi.org/10.3390/rs12182894.

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Shifts in wildflower phenology in response to climate change are well documented in the scientific literature. The majority of studies have revealed phenological shifts using in-situ observations, some aided by citizen science efforts (e.g., National Phenology Network). Such investigations have been instrumental in quantifying phenological shifts but are challenged by the fact that limited resources often make it difficult to gather observations over large spatial scales and long-time frames. However, recent advances in finer scale satellite imagery may provide new opportunities to detect changes in phenology. These approaches have documented plot level changes in vegetation characteristics and leafing phenology, but it remains unclear whether they can also detect flowering in natural environments. Here, we test whether fine-resolution imagery (<10 m) can detect flowering and whether combining multiple sources of imagery improves the detection process. Examining alpine wildflowers at Mt. Rainier National Park (MORA), we found that high-resolution Random Forest (RF) classification from 3-m resolution PlanetScope (from Planet Labs) imagery was able to delineate the flowering season captured by ground-based phenological surveys with an accuracy of 70% (Cohen’s kappa = 0.25). We then combined PlanetScope data with coarser resolution but higher quality imagery from Sentinel and Landsat satellites (10-m Sentinel and 30-m Landsat), resulting in higher accuracy predictions (accuracy = 77%, Cohen’s kappa = 0.39). The model was also able to identify the timing of peak flowering in a particularly warm year (2015), despite being calibrated on normal climate years. Our results suggest PlanetScope imagery holds utility in global change ecology where temporal frequency is important. Additionally, we suggest that combining imagery may provide a new approach to cross-calibrate sensors to account for radiometric irregularity inherent in fine resolution PlanetScope imagery. The development of this approach for wildflower phenology predictions provides new possibilities to monitor climate change effects on flowering communities at broader spatiotemporal scales. In protected and tourist areas where the flowering season draws large numbers of visitors, such as Mt. Rainier National Park, the modeling framework presented here could be a useful tool to manage and prioritize park resources.
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NAKAYA, Jun, Hana TSUCHIYA, Tomoya SAKAMOTO, Tatsuki KATO, Yoshihiro KAJIMURA, Kentarou KITAMURA, Shinya UETA, and Taku TAKADA. "Development and Application of a 2U CubeSat Ground Model for Space Technology Education." Journal of JSEE 68, no. 2 (2020): 2_60–2_65. http://dx.doi.org/10.4307/jsee.68.2_60.

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48

SAKAMOTO, Tomoya, Tatsuki KATO, Jun NAKAYA, Hana TSUCHIYA, Makoto WAKABAYASHI, Masahiro TOKUMITSU, Shinya UETA, and Taku TAKADA. "Development and Application of a 2U CubeSat Ground Model for Space Technology Education." Journal of JSEE 68, no. 2 (2020): 2_66–2_71. http://dx.doi.org/10.4307/jsee.68.2_66.

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49

Tapsawat, Wittawat, Teerawat Sangpet, and Suwat Kuntanapreeda. "Development of a hardware-in-loop attitude control simulator for a CubeSat satellite." IOP Conference Series: Materials Science and Engineering 297 (January 2018): 012010. http://dx.doi.org/10.1088/1757-899x/297/1/012010.

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50

Post, Mark A., Junquan Li, and Regina Lee. "A Low-Cost Photodiode Sun Sensor for CubeSat and Planetary Microrover." International Journal of Aerospace Engineering 2013 (2013): 1–9. http://dx.doi.org/10.1155/2013/549080.

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This paper presents the development of low-cost methodologies to determine the attitude of a small, CubeSat-class satellite and a microrover relative to the sun's direction. The use of commercial hardware and simple embedded designs has become an effective path for university programs to put experimental payloads in space for minimal cost, and the development of sensors for attitude and heading determination is often a critical part. The development of two compact and efficient but simple coarse sun sensor methodologies is presented in this research. A direct measurement of the solar angle uses a photodiode array sensor and slit mask. Another estimation of the solar angle uses current measurements from orthogonal arrays of solar cells. The two methodologies are tested and compared on ground hardware. Testing results show that coarse sun sensing is efficient even with minimal processing and complexity of design for satellite attitude determination systems and rover navigation systems.
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