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Journal articles on the topic 'Satellite solar panel deployment mechanism'

Author: Grafiati

Published: 3 June 2025

Last updated: 1 August 2025

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1

Solís-Santomé, Arturo, Guillermo Urriolagoitia-Sosa, Beatriz Romero-Ángeles, et al. "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, no. 1 (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 i

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Li, Ning, Ma Xiaolong, Zhang Chongfeng, Zou Huaiwu, Liu Jinglong, and Yang Wenmiao. "Modeling and analysis for the deployment dynamic behavior of the large flexible solar array." INTER-NOISE and NOISE-CON Congress and Conference Proceedings 265, no. 6 (2023): 1623–30. http://dx.doi.org/10.3397/in_2022_0229.

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The large flexible solar array for the satellite will deploy when it reaches the scheduled orbit by the space rocket, which is key for the normal running of the satellite. However, undesirable and unpredicted frequency vibration may be resulted from the flexibility of elements of the solar array. In this paper, the dynamic model of the solar panel was firstly developed based on the modal synthesis method. Moreover, the stretchable mechanism in the solar array was introduced by applying Euler-Bounerlli beam theory. Also, guide ropes, hinges and electric cables were considered in the proposed mo

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ODA, Yasufumi, Yasutaka NARUSAWA, Toshihiro IDEHARA, and Masanobu MIZOGUCHI. "131 Development of Solar Panel Deployment Mechanisms for a Small Satellite ChubuSat." Proceedings of Conference of Tokai Branch 2015.64 (2015): _131–1_—_131–2_. http://dx.doi.org/10.1299/jsmetokai.2015.64._131-1_.

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Chen, Chao, Guan Yang Liu, Yu Ru Zhang, et al. "Deployment Mechanism Design with Behavioral Modeling Based on Pro/Engineer Motion Skeleton." Applied Mechanics and Materials 163 (April 2012): 242–46. http://dx.doi.org/10.4028/www.scientific.net/amm.163.242.

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A novel method using motion skeleton and behavioral modeling in Pro/Engineer to design a motion mechanism is proposed in this paper. With this method, intuitive kinematical simulation system of a motion mechanism can be set up quickly and mechanism dimensions can be determined automatically. Deployment mechanism, as one kind of motion mechanisms, is often used to stretch out solar panels or antennas in spacecraft. This method is feasible and reliable to determine the dimensions of a six-bar-linkage deployment mechanism for stretching satellite antennas. Simulation results are obtained with kin

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Bhattarai, Shankar, Ji-Seong Go, and Hyun-Ung Oh. "Experimental CanSat Platform for Functional Verification of Burn Wire Triggering-Based Holding and Release Mechanisms." Aerospace 8, no. 7 (2021): 192. http://dx.doi.org/10.3390/aerospace8070192.

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In this study, we present the Diverse Holding and Release Mechanism Can Satellite (DHRM CanSat) platform developed by the Space Technology Synthesis Laboratory (STSL) at Chosun University, South Korea. This platform focuses on several types of holding and release mechanisms (HRMs) for application in deployable appendages of nanosatellites. The objectives of the DHRM CanSat mission are to demonstrate the design effectiveness and functionality of the three newly proposed HRMs based on the burn wire triggering method, i.e., the pogo pin-type HRM, separation nut-type HRM, and Velcro tape-type HRM,

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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 accom

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SEO, Jong-Hwi, Jang-Soo CHAE, Tae-Won PARK, Sang-Won HAN, Jang-Bom CHAI, and Hyun-Seok SEO. "Solar Panel Deployment Analysis of a Satellite System." JSME International Journal Series C 46, no. 2 (2003): 508–18. http://dx.doi.org/10.1299/jsmec.46.508.

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8

Fufa, Birhanu, Chen Zhao-Bo, and Ma Wensheng. "Modeling and Simulation of Satellite Solar Panel Deployment and Locking." Information Technology Journal 9, no. 3 (2010): 600–604. http://dx.doi.org/10.3923/itj.2010.600.604.

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9

Kamal, Shoaib, P. S. Ramapraba, Avinash Kumar, et al. "Optimization of Solar Panel Deployment Using Machine Learning." International Journal of Photoenergy 2022 (May 16, 2022): 1–7. http://dx.doi.org/10.1155/2022/7249109.

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In this work, we proposed a mechanism for topology reconfiguration or optimization of photovoltaic (PV) arrays using machine learning-assisted techniques. The study takes into concern several topologies that includes series parallel topology, parallel topology, bridge link topology, honeycomb topology, and total cross tied. The artificial neural network-based topology reconfiguration strategy allows for optimal working conditions for PV arrays. With this, machine learning-assisted topology reconfiguration or optimal solar panel deployment enables the proposed mechanism to achieve higher degree

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10

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 dir

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Burgess, S. C. "Simulation of the Initial Deployment Kinetics of a Spacecraft Solar Array." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 209, no. 2 (1995): 131–38. http://dx.doi.org/10.1243/pime_proc_1995_209_279_02.

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This paper presents a mathematical simulation of the initial deployment kinetics of a spacecraft solar array panel stack and its primary deployment mechanism. Two methods for achieving initial deployment are considered. The first deployment method involves the motorized deployment of a single hinge. The second deployment method involves the spring actuated deployment of two hinges. In the motorized deployment case, the solar array is predicted to slide against the spacecraft sidewall before separation. In the spring actuated deployment case, the solar array is predicted to separate from the sp

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12

Jeong, Ju Won, Kum Cheol Shin, Kyung Won Kim, Jae Hyuk Lim, and Jung Ju Lee. "SMA Damped Tape Spring Hinge for Quasi-Static Deployment of a Satellite Solar Array." Applied Mechanics and Materials 705 (December 2014): 96–100. http://dx.doi.org/10.4028/www.scientific.net/amm.705.96.

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A tape spring hinge is one of the most typical deployment devices and is frequently used in miniaturized satellite due to its simplicity, lightweight, low cost and high deployment reliability. But a tape spring hinge mechanism has limited performance due to the performance trade-off between deployed stiffness and latch-up shock.In this study, to improve a conventional tape spring hinge mechanism, SMA damped tape spring hinge is proposed so that a satellite solar array can be quasi-statically deployed. The test result shows the feasibility of the proposed concept.

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13

Zhang, Jie, Pengfei Wu, Qinghu Han, Xin Wei, and Yi Duan. "Dynamic Behavior of Satellite and Its Solar Arrays Subject to Large-Scale Antenna Deployment Shock." Aerospace 11, no. 5 (2024): 349. http://dx.doi.org/10.3390/aerospace11050349.

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Satellites should be equipped with more and more deployable, large, flexible appendages to improve their service efficiency and reduce launch costs. The spring-driven deployment method of flexible appendages has been widely applied and generates great instantaneous shock loads on satellites, maybe affecting the safety of other flexible appendages, but the current related investigations for satellites with multiple large flexible appendages are insufficient. In this study, the deployment test of the antenna itself was conducted, and the attitude changes in a satellite during antenna deployment

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14

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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Bhattarai, Shankar, Ji-Seong Go, Hongrae Kim, and Hyun-Ung Oh. "Experimental Validation of a Highly Damped Deployable Solar Panel Module with a Pogo Pin-Based Burn Wire Triggering Release Mechanism." International Journal of Aerospace Engineering 2020 (December 14, 2020): 1–14. http://dx.doi.org/10.1155/2020/8829515.

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In this present work, a highly damped deployable solar panel module was developed for application in the 3 U CubeSat. The solar panel proposed herein is effective in guaranteeing the structural safety of solar cells under a launch environment owing to the superior damping characteristics achieved using multilayered stiffeners with viscoelastic acrylic tapes. A holding and release action of the solar panel was achieved by a new version of spring-loaded pogo pin-based burn wire triggering mechanism. A demonstration model of high-damping solar panel assembly was fabricated and tested to validate

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16

ARAKI, Yuta, Miyuki SAITO, Tetsuya ISOMURA, Tatsuya YOSHINO, Masaki KANO, and Yasuyuki MIYAZAKI. "S192011 Development of the deployment mechanism of panel structure for Nano-Satellite." Proceedings of Mechanical Engineering Congress, Japan 2013 (2013): _S192011–1—_S192011–4. http://dx.doi.org/10.1299/jsmemecj.2013._s192011-1.

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Alam, Touhidul, Muntasir M. Sheikh, Rabah W. Aldhaheri, et al. "Lower Ultra-High Frequency Non-Deployable Omnidirectional Antenna for Nanosatellite Communication System." Nanomaterials 12, no. 18 (2022): 3143. http://dx.doi.org/10.3390/nano12183143.

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The concept of the nanosatellite comes into play in launching miniaturized versions of satellites or regarding payloads with minimizing cost and building time. The economic affordability of nanosatellites has been promoted with a view to launching various nanosatellite missions. The communication system is one of the most important aspects of a satellite. The antenna is a key element for establishing a communication link between the earth and the nanosatellite. The antenna and solar panel of the nanosatellite are two of the most vital components that profoundly impact antenna type and design.

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Wang, Yihang, Yongsheng Zhao, Bo Han, Jinming Dong, Meng Han, and Jiantao Yao. "Biomimetic Origami: Planar Single-Vertex Multi-Crease Mechanism Design and Optimization." Machines 13, no. 3 (2025): 240. https://doi.org/10.3390/machines13030240.

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Space exploration and satellite communication demand lightweight, large-scale, and highly deployable structures. Inspired by the folding mechanism of frilled lizards and origami mechanisms, this study explores a deployable structure based on the single-vertex multi-crease origami (SVMCO) concept. The design focuses on crease distribution optimization to enhance deployment efficiency. A mathematical model analyzes the relationship between sector angles of three types of facets and structural performances, providing guidelines for achieving optimal deployment. Drawing from the rib patterns of fr

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G. El-Sherbiny, M., A. Khattab, and M. K. Kassab. "Design of the Deployment Mechanism of Solar Array on a Small Satellite." American Journal of Mechanical Engineering 1, no. 3 (2013): 66–72. http://dx.doi.org/10.12691/ajme-1-3-2.

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20

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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21

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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El-Sherbiny, M., A. Khattab, and M. Kassab. "Drag Braking of the Deployment Mechanism of Solar Array on a Small Satellite." International Conference on Aerospace Sciences and Aviation Technology 15, AEROSPACE SCIENCES (2013): 1–16. http://dx.doi.org/10.21608/asat.2013.22260.

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23

Thesiya, Dignesh, A. R. Srinivas, and Piyush Shukla. "A Novel Lateral Deployment Mechanism for Segmented Mirror/Solar Panel of Space Telescope." Journal of Astronomical Instrumentation 04, no. 03n04 (2015): 1550006. http://dx.doi.org/10.1142/s2251171715500063.

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Space telescopes require large aperture primary mirrors to capture High Definition (HD) ground image while orbiting around the Earth. Fairing Volume of launch vehicles is limited and thus the size of monolithic mirror is limited to fairing size and solar panels are arranged within a petal formation in order to provide a greater power to volume ratio. This generates need for deployable mirrors for space use. This brings out a method for designing new deployment mechanism for segmented mirror. Details of mechanism folding strategy, design of components, FE simulations, realization and Lab model

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Zeng, Ting, Huaiming Wang, Lihui Chen, and Yun Li. "Research on the influence mechanism of assembly stress on reliability of space deployable mechanism." Journal of Physics: Conference Series 2029, no. 1 (2021): 012113. http://dx.doi.org/10.1088/1742-6596/2029/1/012113.

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Abstract The on-orbit performance of spaceborne SAR satellite mainly depends on the unwrapping precision of antenna panel, which is determined by its supporting pole system. The assembly stress of the pole system affects the antenna deployable precision in the assembly process of SAR antenna deployable mechanism. Aiming at this problem, this work presents a efficient method that the three-dimensional model of the deployment mechanism of SAR antenna is established, and the method of finite element simulation analysis is adopted. Prestress is applied to the pole system to simulate its assembly s

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XUAN Ming, 宣明, 张道威 ZHANG Dao-wei, 谷松 GU Song, 杨林 YANG Lin, and 程龙 CHENG Long. "Design of hold-down and release mechanism for solar panel of micro-satellite." Optics and Precision Engineering 25, no. 4 (2017): 979–86. http://dx.doi.org/10.3788/ope.20172504.0979.

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Thesiya, Dignesh, A. R. Srinivas, and Piyush Shukla. "Erratum: "A Novel Lateral Deployment Mechanism for Segmented Mirror/Solar Panel of Space Telescope"." Journal of Astronomical Instrumentation 05, no. 02 (2016): 1692001. http://dx.doi.org/10.1142/s225117171692001x.

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Gu, Wenyan, Jinsheng Zhang, Longye Pan, Yegao Qu, Jin-Hwan Choi, and Xiangqian Zhu. "Coupling Effect of Nonlinear Stiffness of Tape Spring Hinges and Flexible Deformation of Panels during Orbit Maneuvers." Aerospace 9, no. 1 (2022): 30. http://dx.doi.org/10.3390/aerospace9010030.

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Many solar panels for spacecrafts are deployed by Tape Spring Hinges (TSHs) which have changeable stiffness. The stiffness of TSH is small when panels are folded, and it becomes large quickly in its deployed status. Since the solar panel is a thin sheet, flexible deformation is easily generated by orbit maneuvers. The coupling effect between the nonlinear TSHs and the flexible panels generates obvious vibration which affects the operational stability of the satellite. To investigate this coupling effect, non-deformable, linear deformable and nonlinear deformable panels were modelled by rigid b

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Zafrane, Mohammed Amine, Abes Bachir, Zakaria Boudechiche, and Othmane Fekhikher. "Interactive design and advanced manufacturing of double solar panel deployment mechanism for CubeSat, part 1: electronics design." International Journal on Interactive Design and Manufacturing (IJIDeM) 14, no. 2 (2020): 503–18. http://dx.doi.org/10.1007/s12008-020-00642-3.

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Lee, So-Jeong, Dae-Hyun Hwang, and Jae-Hung Han. "Development of Pyroshock Simulator for Shock Propagation Test." Shock and Vibration 2018 (September 13, 2018): 1–13. http://dx.doi.org/10.1155/2018/9753793.

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Satellites are subjected to pyrotechnic shocks caused by actuating the pyrotechnic separation devices during various missions such as separation from the launch vehicle and deployment of the solar panel. Pyroshock rarely damages structural members, but it may cause damage to mounted electronic equipment, which can lead to mission failures. In order to protect electronic equipment from pyroshock, shock propagation characteristics need to be identified. This paper proposes a compact pyroshock simulator that can be used to identify the pyroshock propagation characteristics at various locations of

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Liu, Xianyi, Jiarui Zhang, Shuai Zhang, and Wei Li. "The design of a novel two-dimensional deployable mechanism for large-aperture planar antennas." Journal of Physics: Conference Series 2764, no. 1 (2024): 012007. http://dx.doi.org/10.1088/1742-6596/2764/1/012007.

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Abstract Large-aperture planar antennas are essential in applications like satellite communication and Earth observation. In order to accommodate them within the constrained storage space of rockets during launch, the development of high-folding-ratio mechanisms becomes imperative. However, most of the existing planar antennas rely on one-dimensional deployable mechanisms, limiting their width and impeding the development of planar antennas with larger apertures. The lack of two-dimensional deployable planar antennas is primarily due to their stringent requirements, including the need for flat

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Lin, Xiaoxia, Xinyue Xiao, Lin Sun, et al. "An Enhanced YOLOv8 Model with Symmetry-Aware Feature Extraction for High-Accuracy Solar Panel Defect Detection." Symmetry 17, no. 7 (2025): 1052. https://doi.org/10.3390/sym17071052.

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The growing popularity of solar panels is crucial for global decarbonization, but harsh environmental conditions can lead to defects such as cracks, fingerprints, and short circuits. Existing methods face the challenge of detecting multi-scale defects while maintaining real-time performance. This paper proposes a solar panel defect detection model, DCE-YOLO, based on YOLOv8. The model incorporates a C2f-DWR-DRB module for multi-scale feature extraction, where the parallel DRB branch models spatial symmetry through symmetric-rate dilated convolutions, improving robustness and consistency. The C

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Deepesh, Prakash Guragain, Kaji Budhathok Ram, and Ghimire Pramod. "Programmable timer triggered energy harvesting wireless sensor-node using long range radio access technology." International Journal of Electrical and Computer Engineering (IJECE) 12, no. 4 (2022): 3869–81. https://doi.org/10.11591/ijece.v12i4.pp3869-3881.

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Despite widespread deployment of wireless sensor networks (WSN) in remote and inapproachable locations, energy consumption/storage of WSN hindered its adoption. Similarly, the battery-powered sensor nodes are of no use once the battery is depleted. To overcome this limitation, energy harvesting is one of the key techniques. In this paper, an almost perpetual self-powered sensor node is proposed. This sensor node uses a solar panel to harvest energy while the entire energy management is accomplished by BQ25570. Similarly, a super-capacitor is used as an energy storage unit with long range radio

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Hossain, Mohammad Istiaque, Adnan Ali, Veronica Bermudez Benito, Benjamin Figgis, and Brahim Aïssa. "Anti-Soiling Coatings for Enhancement of PV Panel Performance in Desert Environment: A Critical Review and Market Overview." Materials 15, no. 20 (2022): 7139. http://dx.doi.org/10.3390/ma15207139.

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Areas with abundant sunlight, such as the Middle East and North Africa (MENA), are optimal for photovoltaic (PV) power generation. However, the average power loss of photovoltaic modules caused by dust accumulation is extreme and may reach 1%/day, necessitating frequent cleaning which adds to the cost of operations and maintenance. One of the solutions to the problem of PV soiling is to develop anti-soil coatings, where hydrophilic or hydrophobic coatings with spectral characteristics suitable for PV applications are added to the outer layer of PV glass. However, the effectiveness of such coat

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Salih, Rizgar Ahmed, Karzan Qadir Mohammed, Peshawa Osman Hama, Rawaz Othman Hassan, and Barham Kamal Noori. "Design and Implementation of Single Axis Solar Tracking System: Utilizing GPS, Astronomical Equations, and Satellite Dish Actuator for Optimal Efficiency." Journal of Engineering 31, no. 2 (2025): 95–109. https://doi.org/10.31026/j.eng.2025.02.06.

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Globally, the focus is on maximizing the energy yield and efficiency of PV systems as an essential renewable energy source. Different methods have been proposed to achieve this goal. Where the sun’s location in the sky is changed during the day, a tracking mechanism has been proposed as a promising technology to harness the maximum amount of solar radiation by PV system as compared to the fixed panels. In this study, the design and implementation of a polar single-axis tracking system is presented to improve the energy efficiency of PV system through angular variation during the day using the

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Delovski, Toni, Catherin Düvel, Fabian Greif, et al. "Eu:CROPIS AIV Program: Challenges and Solutions for a Spin-Stabilized Satellite Containing Biology." International Journal of Aerospace Engineering 2019 (November 11, 2019): 1–20. http://dx.doi.org/10.1155/2019/9190329.

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Eu:CROPIS is DLR’s first mission of the Compact Satellite Program. Its primary payload focuses on the research of closed-loop biological, regenerative life support systems, in a simulated gravitational environment of the Moon and Mars over months at a time. This is achieved by rotation of the satellite around its central body axis, using only magnetic torquers as actuators. A secondary payload (“PowerCells”) by the NASA Ames Research Center also utilizes the artificial gravity to conduct growth experiments on genetically modified organisms (GMOs). These payloads and the system design imposed c

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Saqib, Muhammad, Tarik Adnan Almohamad, and Raja Majid Mehmood. "A Low-Cost Information Monitoring System for Smart Farming Applications." Sensors 20, no. 8 (2020): 2367. http://dx.doi.org/10.3390/s20082367.

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A low-cost, low-power, and low data-rate solution is proposed to fulfill the requirements of information monitoring for actual large-scale agricultural farms. A small-scale farm can be easily managed. By contrast, a large farm will require automating equipment that contributes to crop production. Sensor based soil properties measurement plays an integral role in designing a fully automated agricultural farm, also provides more satisfactory results than any manual method. The existing information monitoring solutions are inefficient in terms of higher deployment cost and limited communication r

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Abdellatif, Akram, Ali H. Ali, Mohamed E. El-sayed, Nermine M. Elhusseiny, Youmna Mabrouk, and Youssef M. Fathy. "The Verification of Nanosatellites Solar Panels Automatic Deployment in Microgravity Conditions." Advances in Astronautics Science and Technology, August 12, 2021. http://dx.doi.org/10.1007/s42423-021-00083-4.

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AbstractThe solar panels installed on a CubeSat are considered the main energy source of a nanosatellites. The deployment mechanism of a solar panel must be analyzed and tested extensively. Any suggested solar panel design should present a low vibrating free spinning deployment mechanism. This paper examines various types of solar panels to reach a conclusion of the efficient design when deployed on a 1U or 2U unit. However, calculations, analysis, simulations do not always give an extensive picture of how the satellite shall behave during deployment. Thus, testing in a microgravity environmen

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Souradeep Hazra. "Design of a New Multi-Variant Solar Panel Deployment System (Mvspds)." Journal of Aerospace Sciences and Technologies, July 28, 2023, 267–72. http://dx.doi.org/10.61653/joast.v73i4.2021.106.

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Multi-Variant Solar Panel Deployment System (MVSPDS) is defined as the satellite deployment System which can change its orientation according to the power supply required for the satellite or power supply source available to the satellite. To deploy the solar panels completely, it is necessary to design the deployment mechanism which has high precision and reliability. So, this method of deployment will not only provide the said benefit but also it will allow a wide range of application. Consequently, the analysis on the dynamic characteristic of the deployment mechanism must be done at an ini

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Hossein, Ramezani Ali-Akbari. "Design of a Satellite Solar Panel Deployment Mechanism Using the Brushed DC Motor as Rotational Speed Damper." International Journal of Mechanical, Industrial and Aerospace Sciences 11.0, no. 4 (2018). https://doi.org/10.5281/zenodo.1316259.

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This paper presents an innovative method to control the rotational speed of a satellite solar panel during its deployment phase. A brushed DC motor has been utilized in the passive spring driven deployment mechanism to reduce the deployment speed. In order to use the DC motor as a damper, its connector terminals have been connected with an external resistance in a closed circuit. It means that, in this approach, there is no external power supply in the circuit. The working principle of this method is based on the back electromotive force (or back EMF) of the DC motor when an external torque (h

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"A Study on the Solar Panel Deployment of a Satellite." Journal of the Korean Society for Aeronautical & Space Sciences 31, no. 4 (2003): 53–59. http://dx.doi.org/10.5139/jksas.2003.31.4.053.

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Atar, Cihan, Metin Aktas, Nedim Sözbir, and Unal Camdali. "Thermal investigations of solar panel deployment angles for a 3U CubeSat orbiting at LEO." Journal of Thermal Science and Engineering Applications, August 2, 2024, 1–12. http://dx.doi.org/10.1115/1.4066139.

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Abstract Designing and manufacturing of CubeSats have a rapid growing interest lately as they can serve in a wide range of space missions. To ensure that they are safe, stable, and functional in harsh space environment, thermal studies are very important. New design approaches have been introducing to manufacture more efficient and long-lasting satellites, and deploying solar panels is one of them aiming to harness more solar energy. In the literature, however, the studies focusing on CubeSats with deployed solar panels at different angles are very limited. Due to the reason, we investigated t

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Zafrane, Mohammed Amine, Abdelghafour Azzouz Bouchahma, Bachir Abes, Bachir Zafrane, and Mokhtar Freh Bengabou. "E-design and manufacturing approach for Cubesat solar panel deployment mechanism." International Journal on Interactive Design and Manufacturing (IJIDeM), March 15, 2022. http://dx.doi.org/10.1007/s12008-022-00867-4.

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Fan, Rongquan, Ziqiang Ming, Weiting Xu, et al. "Optimization of photovoltaic panel deployment in centralized photovoltaic power plant under multiple factors." Frontiers in Energy Research 10 (January 23, 2023). http://dx.doi.org/10.3389/fenrg.2022.1087487.

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Solar energy is one of the main renewable energy sources and has rapidly developed in many countries. However, the photovoltaic (PV) output power will be different under various meteorological and geographical conditions. Therefore, this paper presents an optimization method for the deployment of PV panels in a centralized PV power plant considering multiple factors. Firstly, the whole planning area is divided into a certain amount of sub-areas according to a given area, and fuzzy C-means algorithm is used for terrain clustering according to the geographical characteristics of the sub-areas. S

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Jang, Kyung Bae, and Tae Ho Woo. "Analysis of Solar Radiation Shielding in Space for Climate Mitigations of the Earth." Energy Science & Engineering, February 27, 2025. https://doi.org/10.1002/ese3.2083.

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ABSTRACTSolar radiation modification (SRM) through space solar shielding is a proposed strategy to mitigate global warming. This approach involves reflecting sunlight back into space while allowing Earth's infrared radiation to escape, thereby controlling climate change. The effectiveness of space solar shielding is evaluated using a complex algorithm that considers various parameters of the shielding satellite, such as its size, orbit, and deployment mechanism. The thickness of the shield should be similar to the solar wavelength, around 400‐600 nm, to deflect sunlight with an expected mass d

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Gauld, Jethro, Philip W. Atkinson, João P. Silva, Andreas Senn, and Aldina M. A. Franco. "Characterisation of a new lightweight LoRaWAN GPS bio-logger and deployment on griffon vultures Gyps fulvus." Animal Biotelemetry 11, no. 1 (2023). http://dx.doi.org/10.1186/s40317-023-00329-y.

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Abstract1. Information provided by tracking studies using remote telemetry is providing ecologists with invaluable new insights into animal behaviour and movement strategies. Here we describe a new type of GNSS (Global Navigation Satellite System) tracking device currently under development and nearing commercialisation, which transmits data via LoRaWAN (long range wide area network) gateways. These tags have the potential to be a low weight and power consumption solution for tracking the movement of animals at high resolution. 2. We characterise the position accuracy and data transmission ran

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