Relevant bibliographies by topics / Deployable Solar Panel

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  1. Journal articles
  2. Dissertations / Theses
  3. Book chapters
  4. Conference papers

Academic literature on the topic 'Deployable Solar Panel'

Author: Grafiati
Published: 3 June 2025
Last updated: 31 July 2025

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Journal articles on the topic "Deployable Solar Panel"

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Ibrahim, Syahrim Azhan, and Eiki Yamaguchi. "Comparison of Solar Radiation Torque and Power Generation of Deployable Solar Panel Configurations on Nanosatellites." Aerospace 6, no. 5 (2019): 50. http://dx.doi.org/10.3390/aerospace6050050.

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Nanosatellites, like CubeSat, have begun completing advanced missions that require high power that can be obtained using deployable solar panels. However, a larger solar array area facing the Sun increases the solar radiation torque on the satellite. In this study, we investigated solar radiation torque characteristics resulting from the increased area of solar panels on board the CubeSats. Three common deployable solar panel configurations that are commercially available were introduced and their reference missions were established for the purpose of comparison. The software algorithms used t
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Ibrahim, Syahrim Azhan, and Eiki Yamaguchi. "Thermally induced dynamics of deployable solar panels of nanosatellite." Aircraft Engineering and Aerospace Technology 91, no. 7 (2019): 1039–50. http://dx.doi.org/10.1108/aeat-07-2018-0185.

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Purpose This study aims to predict the types of thermally induced dynamics (TID) that can occur on deployable solar panels of a small form factor satellite, CubeSat which flies in low Earth orbit (LEO). The TID effect on the CubeSat body is examined. Design/methodology/approach A 3U CubeSat with four short-edge deployable solar panels is considered. Time historic temperature of the solar panels throughout the orbit is obtained using a thermal analysis software. The results are used in numerical simulation to find the structural response of the solar panel. Subsequently, the effect of solar pan
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Bhattarai, Shankar, Hongrae Kim, and Hyun-Ung Oh. "CubeSat’s Deployable Solar Panel with Viscoelastic Multilayered Stiffener for Launch Vibration Attenuation." International Journal of Aerospace Engineering 2020 (August 11, 2020): 1–10. http://dx.doi.org/10.1155/2020/8820619.

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Ensuring the structural safety of a deployable solar panel under a severe launch vibration environment is one of the important factors for a successful CubeSat mission. A CubeSat’s deployable solar panel proposed in this study is effective to guarantee the structural safety of solar cells by attenuating launch loads owing to the superior damping characteristic achieved by a multilayered stiffener with viscoelastic acrylic tapes. The demonstration model of 3 U CubeSat’s deployable solar panel was fabricated and tested to validate the effectiveness of the proposed design. The basic dynamic chara
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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 (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
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Budiantoro, Poki Agung, and Ahmad Fauzi. "PRELIMINARY THERMAL CONTROL DESIGN ANALYSIS OF LAPAN SAR-MICROSATELLITE DEPLOYABLE SOLAR ARRAY PANEL USING ONE NODAL METHODE." Jurnal Teknologi Dirgantara 17, no. 2 (2019): 157. http://dx.doi.org/10.30536/j.jtd.2019.v17.a3155.

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LAPAN SAR-Microsatellite is the first LAPAN micro satellite being developed and planned to carry a Synthetic Aperture Radar (SAR) payload. Different from optical satellites that have been developed, LAPAN SAR-Microsatellite requires a lot more power. Solar array panels are needed to generate solar radiation into electrical energy which is used by all of subsystem satellite as energy to turn on and turn off all of components. More larger the area of solar array panel, more greater to the energy obtanied. Therefore, the needed of deployable solar array panel is a must caused by the dimension of
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Santoni, Fabio, Fabrizio Piergentili, Serena Donati, Massimo Perelli, Andrea Negri, and Michele Marino. "An innovative deployable solar panel system for Cubesats." Acta Astronautica 95 (February 2014): 210–17. http://dx.doi.org/10.1016/j.actaastro.2013.11.011.

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Kong, Yongfang, and Hai Huang. "Design and experiment of a passive damping device for the multi-panel solar array." Advances in Mechanical Engineering 9, no. 2 (2017): 168781401668796. http://dx.doi.org/10.1177/1687814016687965.

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With the space technology development, large flexible space deployable structures have been used widely. Studying on the vibration control for large flexible space deployable structures becomes very important. In this study, a novel passive vibration damping device is developed for the multi-panel sun-orientated deployable solar array. Its upper strut contains a viscous damper while the lower strut is rigid. The device is lockable and located near the solar array root hinge to increase the structural damping without reducing the fundamental frequency. This design will not influence the origina
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Triharjanto, M.Sc, Robertus Heru, and Poki Agung Budiantoro. "FINITE ELEMENT MODELING OF LAPAN-A5/CHIBASAT DEPLOYABLE SOLAR PANEL COMPOSITE PLATE." Jurnal Teknologi Dirgantara 16, no. 2 (2019): 169. http://dx.doi.org/10.30536/j.jtd.2018.v16.a3065.

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LAPAN-A5/ChibaSat, that will carry synthetic aperture radar payload, requires a lot more power generation capacity, compared to its predecessor. Therefore, its solar panel will be deployed in orbit to ensure maximum sun exposure. Since the deployable system requires solar panel plate that lightweight and strong, honeycomb composite material is selected. The selection of such material requires special treatment in the satellite structural stiffness calculation. The objective of the research is to find simple stiffness model of the plate, so that later it can be integrated with the total satelli
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Takatsuka, Masao. "Dynamic modeling of two-dimensional-deployable linked panels in space." International Journal of Space Structures 33, no. 1 (2017): 19–34. http://dx.doi.org/10.1177/0266351117746269.

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The objective of the present study is to derive a dominant equation of our previously proposed two-dimensional-deployable linked panel structure in space, which expresses the relationship between the deployment motion and input moment by an actuator. This article presents a derivation sequence of the dominant equation by the general dynamic modeling of square panels and demonstrates its numerical calculation examples. This numerical experimentation may be useful for designing an actuator considering deployment time in space, especially for realization of a future Solar Power Satellite which co
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Alam, Touhidul, Mohammad Tariqul Islam, Md Amanath Ullah, and Mengu Cho. "A Solar Panel-Integrated Modified Planner Inverted F Antenna for Low Earth Orbit Remote Sensing Nanosatellite Communication System." Sensors 18, no. 8 (2018): 2480. http://dx.doi.org/10.3390/s18082480.

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One of the most efficient methods to observe the impact of geographical, environmental, and geological changes is remote sensing. Nowadays, nanosatellites are being used to observe climate change using remote sensing technology. Communication between a remote sensing nanosatellite and Earth significantly depends upon antenna systems. Body-mounted solar panels are the main source of satellite operating power unless deployable solar panels are used. Lower ultra-high frequency (UHF) nanosatellite antenna design is a crucial challenge due to the physical size constraint and the need for solar pane
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Dissertations / Theses on the topic "Deployable Solar Panel"

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Peters, Eric David. "Dynamic instabilities imparted by CubeSat deployable solar panels." Thesis, Massachusetts Institute of Technology, 2014. http://hdl.handle.net/1721.1/93800.

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Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2014.<br>Cataloged from PDF version of thesis.<br>Includes bibliographical references (pages 85-87).<br>In this work, multibody dynamics simulation was used to investigate the effects of solar panel deployment on CubeSat attitude dynamics. Nominal and partial/asymmetric deployments were simulated for four different solar panel assemblies. Trend lines were obtained for the evolution of the angular velocities and accelerations of the CubeSat about its center of mass for the duration of the deployment
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Book chapters on the topic "Deployable Solar Panel"

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Johnston, J. D., and E. A. Thornton. "Thermal-Structural Performance of Rigid Panel Solar Arrays." In IUTAM-IASS Symposium on Deployable Structures: Theory and Applications. Springer Netherlands, 2000. http://dx.doi.org/10.1007/978-94-015-9514-8_18.

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Conference papers on the topic "Deployable Solar Panel"

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Mindarno, Hery Steven, Konosuke Nishinaga, Polimey Im, et al. "Design of 3U LEOPARD CubeSat with Deployable Solar Panels from Integration to Structural and Vibration Analysis." In 52nd IAF Student Conference, Held at the 75th International Astronautical Congress (IAC 2024). International Astronautical Federation (IAF), 2024. https://doi.org/10.52202/078379-0039.

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McGuire, Thomas, Michael Hirsch, Michael Parsons, Skye Leake, and Jeremy Straub. "A CubeSat deployable solar panel system." In SPIE Commercial + Scientific Sensing and Imaging, edited by Nibir K. Dhar and Achyut K. Dutta. SPIE, 2016. http://dx.doi.org/10.1117/12.2223566.

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Zirbel, Shannon A., Mary E. Wilson, Spencer P. Magleby, and Larry L. Howell. "An Origami-Inspired Self-Deployable Array." In ASME 2013 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/smasis2013-3296.

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The objective of this paper is to show the development of a compact, self-deploying array based on the tapered map fold. The tapered map fold was modified by applying an elastic membrane to one side of the array and adequately spacing the panels adjacent to valley folds. Through this approach, the array can be folded into a fully dense volume when stowed. The panels are dimensioned to account for the panel thickness when folded, which otherwise would prevent the model from reaching a fully dense form. The folding motion is achieved by creating a rigid-foldable model of the origami-inspired cre
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Yakovlev, Alexander, and Alexander Malyshenko. "Automatic derivation of kinematic equations of deployable solar panel arrays." In 2016 International Siberian Conference on Control and Communications (SIBCON). IEEE, 2016. http://dx.doi.org/10.1109/sibcon.2016.7491692.

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Buscicchio, Alessandro, Giammarco Alessandrino, Andrea Troise, Tommaso Sironi, and Alessia Gloder. "SolarCube: An Origami-Inspired Lightweight Deployable Solar Panel for Nanosatellites." In 2023 13th European Space Power Conference (ESPC). IEEE, 2023. http://dx.doi.org/10.1109/espc59009.2023.10298125.

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Septanto, Harry, and Oetomo Sudjana. "Simulation Approach to Determine Position of the Fixed Installed Deployable Solar Panel." In 2018 IEEE International Conference on Aerospace Electronics and Remote Sensing Technology (ICARES). IEEE, 2018. http://dx.doi.org/10.1109/icares.2018.8547098.

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Skinner, Mitchel, Andrew Geyser, Brandon Sargent, Spencer Magleby, and Larry Howell. "Compliant Stepped-Beam Analysis for Deployable Space Structures With Flexible Panels." In ASME 2024 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. American Society of Mechanical Engineers, 2024. http://dx.doi.org/10.1115/detc2024-142798.

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Abstract Deployable space structures that incorporate thin, flexible solar cells allow for innovative designs that are capable of high stowing efficiency. The purpose of this work is to present compliant stepped-beam analysis approaches that apply to deployable space structures with flexible panels connected with thin sheets and determine their deflection as a function of their material properties, geometry, and applied moments. Related methods are described. An analytical model and finite element analysis are compared and validated with a physical model. The end angle, coordinates, and radius
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Troise, Andrea, Alessandro Buscicchio, Vittorio Netti, and Maria Cinefra. "Finite Element Modeling on F.R.E.T. for Origami-Inspired CubeSat Applications." In ASME 2023 Aerospace Structures, Structural Dynamics, and Materials Conference. American Society of Mechanical Engineers, 2023. http://dx.doi.org/10.1115/ssdm2023-106876.

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Abstract Modelling of multi-layer rigid-flex printed circuit boards (PCB) for origami structures can be carried out with several different strategies, often resorting to models that either require a considerable amount of computational power, resulting excessively complex, or descending to oversimplifications that do not grasp the structural dynamics. Among these strategies, finite element modelling results the most convenient because it seizes the behaviour of the system with an eye on computational efficiency. This study shows a new finite element analysis approach to model the dynamics of F
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Budiantoro, Poki Agung, Ahmad Fauzi, Sri Ramayanti, et al. "Thermal Design and Analysis of Deployable Solar Panel Low Earth Orbit Equatorial Constellation Satellite." In 2022 IEEE International Conference on Aerospace Electronics and Remote Sensing Technology (ICARES). IEEE, 2022. http://dx.doi.org/10.1109/icares56907.2022.9993478.

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Troise, A. "Reduced-order modelling of the deployment of a modified flasher origami for aerospace applications." In Aeronautics and Astronautics. Materials Research Forum LLC, 2023. http://dx.doi.org/10.21741/9781644902813-120.

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Abstract. In this paper, we simulate the nonlinear deployment mechanics of a modified flasher origami structure designed to be a deployable solar panel. We compare reduced-order bar-and-hinge simulations, where panels are modelled as bar assemblies connected by joints and torsional springs, with results obtained from commercial finite element software. Through this comparison, we demonstrate the ability of the bar-and-hinge approach to capture key features of the origami behaviour at a fraction of the time needed to perform regular finite-element simulations. We also provide details on how to
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