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Journal articles on the topic 'Deployable Solar Panel'

Author: Grafiati

Published: 3 June 2025

Last updated: 19 July 2025

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1

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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2

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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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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7

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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8

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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9

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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10

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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11

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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12

Kuang, Jinlu, Paul A. Meehan, A. Y. T. Leung, and Soonhie Tan. "Nonlinear dynamics of a satellite with deployable solar panel arrays." International Journal of Non-Linear Mechanics 39, no. 7 (2004): 1161–79. http://dx.doi.org/10.1016/j.ijnonlinmec.2003.07.001.

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13

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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Kim, Min-Ki, Won-Sub Choi, Jin-Hyung Kim, Ji-Seok Kim, Cheol-Ho Lim, and Sung-Ho Lee. "Deployment Tests and Lessons Learned of Deployable Solar Panel for Nanosatellite." Journal of the Korean Society for Aeronautical & Space Sciences 51, no. 4 (2023): 281–89. http://dx.doi.org/10.5139/jksas.2023.51.4.281.

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15

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 validat

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16

Wei, Jin, Wei Liu, Jia Liu, and Tao Yu. "Dynamic Modeling and Analysis of Spacecraft with Multiple Large Flexible Structures." Actuators 12, no. 7 (2023): 286. http://dx.doi.org/10.3390/act12070286.

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An analytical dynamic model is presented for a spacecraft with multiple large flexible structures. Based on the partial differential equations (PDEs) of the motion of the solar panel and deployable arm, the governing equations of the main-body and deployable antenna and the boundary conditions at each end point are used to obtain the frequency and mode shapes of the system. Then, the ordinary differential equations (ODEs) of the system can be obtained from the orthogonality relations and mode shape. The influence of the deployable antenna on the frequencies and mode shapes of the spacecraft is

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17

Kazantsev, Z. A., A. M. Eroshenko, L. A. Babkina, and A. V. Lopatin. "Analysis of design of spacecraft solar arrays." Spacecrafts & Technologies 5, no. 3 (2021): 121–36. http://dx.doi.org/10.26732/j.st.2021.3.01.

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Solar arrays supply electrical power to spacecraft equipment and also provide charging of electrochemical batteries used in the shadow sections of the orbit. Photovoltaic converters of light energy of solar radiation form the basis of the solar battery. Their principle of operation is based on the phenomenon of the photoelectric effect. The article provides an overview of the development of solar cells and the classification of modern designs of solar cells for spacecraft. The review considers stationary and deployable solar batteries used both on the first spacecraft and on space stations. Th

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18

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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19

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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20

Wu, Shuang, Zhijun Zhao, Dongping Liang, Qunzhi Li, and Shougen Zhao. "Nonlinear Dynamic Modeling of Joints between Solar Panels on Spacecraft." Aerospace 9, no. 8 (2022): 459. http://dx.doi.org/10.3390/aerospace9080459.

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Multiple linear and nonlinear dynamic parameters of the joints at the root of solar panels and between solar panels on spacecraft, both of which have complex nonlinear dynamic properties, were identified by using the force state mapping method for modeling complex nonlinear joints in deployable mechanisms of spacecraft, and the differential equations representing the nonlinear dynamic model of the joints were derived. On the basis of the actual force characteristics of the joints, test systems were developed to investigate the vibration response of the complex nonlinear joints in spacecraft so

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21

L, Mrs Gayathri,. "RF based Automatic Traffic Route Clearance System for Emergency Vehicle." INTERANTIONAL JOURNAL OF SCIENTIFIC RESEARCH IN ENGINEERING AND MANAGEMENT 08, no. 04 (2024): 1–5. http://dx.doi.org/10.55041/ijsrem30249.

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Traditional time-based traffic management systems are often inadequate for addressing the complexities of modern urban traffic, resulting in delays for emergency service vehicles such as ambulances and fire services. This project proposes a wireless communication-based approach to alleviate ambulance congestion in urban areas, presenting an innovative traffic clearance system that is easily deployable and cost-effective. Keywords— Arduino, ESP 32 Microcontroller, Solar panel ,GPS,RFID Sensor.

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22

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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Park, Jae-Hyeon, Sung-Woo Park, Jong-Pil Kim, and Hyun-Ung Oh. "Passive Damping of Solar Array Vibrations Using Hyperelastic Shape Memory Alloy with Multilayered Viscous Lamina." Aerospace 10, no. 8 (2023): 704. http://dx.doi.org/10.3390/aerospace10080704.

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A novel passive vibration-damping device is proposed and investigated for a large deployable solar array. One strategy for achieving high damping in a solar panel is using a yoke structure comprising a hyperelastic shape memory alloy and multiple viscous adhesive layers of acrylic tape. The effectiveness of the proposed system in achieving a high damping performance was demonstrated by conducting free vibration and low-level sine sweep tests using a solar array, and a 0.75-m-long flexible dummy structure was simulated. We also investigated the dependence of the damping performance of the propo

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Awais, Muhammad, Syed Suleman Abbas Zaidi, Murk Marvi, and Muhammad Khurram. "A Remotely Deployable Wind Sonic Anemometer." Sukkur IBA Journal of Computing and Mathematical Sciences 1, no. 2 (2017): 1. http://dx.doi.org/10.30537/sjcms.v1i2.45.

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Communication and computing shape up base for explosion of Internet of Things (IoT) era. Humans can efficiently control the devices around their environment as per requirements because of IoT, the communication between different devices brings more flexibility in surrounding. Useful data is also gathered from some of these devices to create Big Data; where, further analysis assist in making life easier by developing good business models corresponding to user needs, enhance scientific research, formulating weather prediction or monitoring systems and contributing in other relative fields as wel

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Nabanita Brahmachari, Mohamed Abdullah K, and Vishnuprakash B. "Aerodynamic Panel Shape Optimization for CubeSats to Reduce Chaotic Motion in Lower Earth Orbit." Acceleron Aerospace Journal 4, no. 2 (2025): 911–20. https://doi.org/10.61359/11.2106-2509.

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CubeSats are increasingly employed in various low-Earth orbit (LEO) missions. However, their stability is often compromised by chaotic motion induced by aerodynamic disturbances and the deployment of appendages, such as solar panels or fins. Addressing these challenges is critical to ensuring mission reliability and extending operational lifetimes. This study explores the aerodynamic performance and stability implications of deployable fin geometries for CubeSats, where two configurations of square-shaped and elliptical fins are chosen for analysis. Using computational fluid dynamics (CFD) sim

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26

Zhao, Yaoli, Gayatri Ranade, Michael Tidwell, Charles Van Neste, and Thomas Thundat. "Field Deployable Sensor Arrays with Molecular Selectivity for Soil Health." ECS Meeting Abstracts MA2023-01, no. 52 (2023): 2596. http://dx.doi.org/10.1149/ma2023-01522596mtgabs.

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Monitoring soil health is very important in agriculture. Soil health can be monitored by the sensing the metabolomic activities of microbiota as increased concentrations in CO2, CH4, N2O, vapors in the soil. A vapor sensor based on microfabricated cantilever array is an ideal sensor platform for field deployable miniature sensors. Many such platforms, such as cantilever arrays, have been demonstrated as sensitive sensors for chemical and biological detection. In fact, the array-based sensor platform satisfies almost all of the requirements of an ideal high-performance sensor, such as its very

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27

Jiang, Guoqing, Ting Dong, and Zhenkun Guo. "Nonlinear Dynamics of an Unsymmetric Cross-Ply Square Composite Laminated Plate for Vibration Energy Harvesting." Symmetry 13, no. 7 (2021): 1261. http://dx.doi.org/10.3390/sym13071261.

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The nonlinear behaviors and energy harvesting of an unsymmetric cross-ply square composite laminated plate with a piezoelectric patch is presented. The unsymmetric cross-ply square composite laminated plate has two stable equilibrium positions by applying thermal stress, thus having snap-through with larger amplitude between the two stable equilibrium positions relative to the general laminated plate. Based on the von-Karman large deformation theory, the nonlinear electromechanical coupling equations of motion of the unsymmetric composite laminated plate with a piezoelectric patch are derived

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Shen, Yingyong, Cong Wang, Shiyu Tan, Ning Zhang, and Jingbo Gao. "Effects of different deployment strategies on the dynamic characteristics of bidirectional solar array." Journal of Physics: Conference Series 2746, no. 1 (2024): 012037. http://dx.doi.org/10.1088/1742-6596/2746/1/012037.

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Abstract Based on natural coordinate method, a multi-rigid-body dynamic model of a bidirectional solar array is established. A typical solar array composed of a spacecraft main-body, a yoke, three main solar panels and two side solar panels is utilized as a demonstration case. Three deployment strategies have been designed for bidirectional solar array. Different deployment strategies are evaluated by analysing the attitude and kinetic energy of the spacecraft main-body, angular velocities of deployable components and constraint forces. The simulation results reveal that the strategy of the si

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Yang, Shuofei, and Yangmin Li. "Kinematic analysis of deployable parallel mechanisms." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 234, no. 1 (2019): 263–72. http://dx.doi.org/10.1177/0954406218825325.

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Inspired by the existing closed-loop deployable mechanisms and parallel mechanisms, a new kind of mechanisms, named deployable parallel mechanisms, is introduced in this paper, and the kinematic analysis is presented. As the combination of deployable mechanisms and parallel mechanisms, deployable parallel mechanisms have advantages of both the two kinds of mechanisms. They can be easily constructed by origami and folded from spatial structures into paper slices. Due to the parallel structures, they can be designed to have higher stiffness and larger volume compressibility than the existing dep

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JIN Guang, 金光, 谢晓光 XIE Xiao-guang, 谷松 GU Song, and 张镝 ZHANG Di. "Dynamic simulation and application of deployable mechanism of satellite solar panels." Optics and Precision Engineering 22, no. 3 (2014): 745–53. http://dx.doi.org/10.3788/ope.20142203.0745.

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Park, Yeon-Kyu, Geuk-Nam Kim, and Sang-Young Park. "Novel Structure and Thermal Design and Analysis for CubeSats in Formation Flying." Aerospace 8, no. 6 (2021): 150. http://dx.doi.org/10.3390/aerospace8060150.

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The CANYVAL-C (CubeSat Astronomy by NASA and Yonsei using a virtual telescope alignment for coronagraph) is a space science demonstration mission that involves taking several images of the solar corona with two CubeSats—1U CubeSat (Timon) and 2U CubeSat (Pumbaa)—in formation flying. In this study, we developed and evaluated structural and thermal designs of the CubeSats Timon and Pumbaa through finite element analyses, considering the nonlinearity effects of the nylon wire of the deployable solar panels installed in Pumbaa. On-orbit thermal analyses were performed with an accurate analytical m

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Son, Min-Young, Bong-Geon Chae, Hyun-Mo Sung, and Hyun-Ung Oh. "Numerical Investigation on the Thermal Characteristics of Lightweight Metal Mesh-Based Reflector Antenna with Various Knitting Conditions." Aerospace 11, no. 9 (2024): 780. http://dx.doi.org/10.3390/aerospace11090780.

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Proper prediction of the temperature variation in a metallic wire mesh for spaceborne large deployable reflector antennas is essential for evaluating the dimensional stability of the antenna under extreme on-orbit thermal environments. However, predicting the temperature of a mesh is difficult because of its complex yarn configuration. To analyze the thermal behavior of the spaceborne mesh antenna reflector, the thermal optical characteristics with various knitting methods of the metallic mesh were obtained experimentally in this study. Subsequently, to analyze the thermal sensitivity of the r

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Mungiguerra, S., G. Zuppardi, L. Spanò Cuomo, and R. Savino. "Effects of solar panels on Aerodynamics of a small satellite with deployable aero-brake." Acta Astronautica 151 (October 2018): 456–66. http://dx.doi.org/10.1016/j.actaastro.2018.06.040.

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Chen, Yan, Huijuan Feng, Jiayao Ma, Rui Peng, and Zhong You. "Symmetric waterbomb origami." Proceedings of the Royal Society A: Mathematical, Physical and Engineering Sciences 472, no. 2190 (2016): 20150846. http://dx.doi.org/10.1098/rspa.2015.0846.

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The traditional waterbomb origami, produced from a pattern consisting of a series of vertices where six creases meet, is one of the most widely used origami patterns. From a rigid origami viewpoint, it generally has multiple degrees of freedom, but when the pattern is folded symmetrically, the mobility reduces to one. This paper presents a thorough kinematic investigation on symmetric folding of the waterbomb pattern. It has been found that the pattern can have two folding paths under certain circumstance. Moreover, the pattern can be used to fold thick panels. Not only do the additional const

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Park, Tae-Yong, Su-Hyeon Kim, Hongrae Kim, and Hyun-Ung Oh. "Experimental Investigation on the Feasibility of Using Spring-Loaded Pogo Pin as a Holding and Release Mechanism for CubeSat’s Deployable Solar Panels." International Journal of Aerospace Engineering 2018 (September 9, 2018): 1–10. http://dx.doi.org/10.1155/2018/4854656.

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A spring-loaded pogo pin as a holding and release mechanism of solar panels for cube satellite applications is proposed which functions as an electrical interface, a separation spring, and a status switch. The proposed mechanism has many advantages, including an increased loading capability, negligible induced shock level, synchronous release of multiple panels, and handling simplicity during integration. A demonstration model of the mechanism was fabricated and functionally tested under various test conditions such as different input voltages, different numbers of tightened nylon wires, and d

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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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Prakash, Thombare* Ravindra Patil. "Performance Assessment of Solar Cooling Technologies for Cold Warehouse Storage Efficiency." International Journal of Scientific Research and Technology 2, no. 4 (2025): 415–21. https://doi.org/10.5281/zenodo.15247615.

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The ecological implications associated with conventional air cooling systems, which are primarily fossil fuel-based, are significant in terms of both greenhouse gas emissions and energy consumption. Based on these challenges, the current study investigates the feasibility of a solar-powered air cooling system as an alternative solution. An evaluation of the effectiveness of this research work is made through experimental analysis and detailed Life Cycle Assessment (LCA) where criteria include energy efficiency, carbon emission, and generally ecological benefits. Results were obtained such that

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Zanette, Luca, Leonardo Reyneri, and Giuseppe Bruni. "Swarm system for CubeSats." Aircraft Engineering and Aerospace Technology 90, no. 2 (2018): 379–89. http://dx.doi.org/10.1108/aeat-07-2016-0119.

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Purpose This paper aims to present an innovative system able to establish an inter-satellite communication crosslink and to determine the mutual physical positioning for CubeSats belonging to a swarm. Design/methodology/approach Through a system involving a smart antenna array managed by a beamforming control strategy, every CubeSat of the swarm can measure the direction of arrival (DOA) and the distance (range) to estimate the physical position of the received signal. Moreover, during the transmission phase, the smart antenna shapes the beam to establish a reliable and directive communication

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Greco, Adriana, Edison Gundabattini, Darius S. Gnanaraj, and Claudia Masselli. "A Comparative Study on the Performances of Flat Plate and Evacuated Tube Collectors Deployable in Domestic Solar Water Heating Systems in Different Climate Areas." Climate 8, no. 6 (2020): 78. http://dx.doi.org/10.3390/cli8060078.

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Using TRNSYS software, a comparison of the energy performances of flat-plate collectors (FPCs) and evacuated-tube collectors (ETCs) in domestic solar water heating systems located in different climate areas was carried out in order to ascertain solar energy utilization. Investigations were carried out on single FPCs and ETCs and also for strings of four panels connected in series. Tests were conducted using simulations for water as heat transfer fluid with a fixed fluid flow rate and varying the temperature of the collector’s returning fluid. The maximum power peak decreases with the increase

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Piccinni, Marco, Davide Carrea, Sawssen Slimani, et al. "Empowering Advanced Photovoltaic Pioneers: A Bilateral Italy-USA Project." ECS Meeting Abstracts MA2024-02, no. 19 (2024): 1753. https://doi.org/10.1149/ma2024-02191753mtgabs.

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The sun bathes our planet with far more energy than humankind will possibly ever need (> 8,000 times the current demand). Yet, sustainable energy provision is among the most pressing challenges faced today. In order to unlock the vast potential of clean solar energy, we need disruptive technologies capable of efficiently harvesting sunlight, while being deployable at unprecedented scales. Available commercial photovoltaics (PV) can hardly cope sustainably with the sheer scale of this challenge. Silicon solar panels are the major commercial PV, they are based on a very Earth-abundant element

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Dalbins, Janis, Kristo Allaje, Hendrik Ehrpais, et al. "Interplanetary Student Nanospacecraft: Development of the LEO Demonstrator ESTCube-2." Aerospace 10, no. 6 (2023): 503. http://dx.doi.org/10.3390/aerospace10060503.

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Nanosatellites have established their importance in low-Earth orbit (LEO), and it is common for student teams to build them for educational and technology demonstration purposes. The next challenge is the technology maturity for deep-space missions. The LEO serves as a relevant environment for maturing the spacecraft design. Here we present the ESTCube-2 mission, which will be launched onboard VEGA-C VV23. The satellite was developed as a technology demonstrator for the future deep-space mission by the Estonian Student Satellite Program. The ultimate vision of the program is to use the electri

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Ji, Huawei, Chuanping Zhou, Jiawei Fan, et al. "Angular Displacement Control for Timoshenko Beam by Optimized Traveling Wave Method." Aerospace 9, no. 5 (2022): 259. http://dx.doi.org/10.3390/aerospace9050259.

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The vibration of flexible structures in spacecraft, such as large space deployable reflectors, solar panels and large antenna structure, has a great impact on the normal operation of spacecraft. Accurate vibration control is necessary, and the control of angular displacement is a difficulty of accurate control. In the traditional control method, the mode space control has a good effect on suppressing low-order modes, but there is control overflow. The effect of traveling wave control on low-order modes is worse than the former, but it has the characteristics of broadband control. It can better

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Zane, Brough, and Paoloni Claudio. "Advanced Deployable/Retractable Solar Panel System for Satellite Applications." February 1, 2015. https://doi.org/10.5281/zenodo.1099402.

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Modern low earth orbit (LEO) satellites that require multi-mission flexibility are highly likely to be repositioned between different operational orbits. While executing this process the satellite may experience high levels of vibration and environmental hazards, exposing the deployed solar panel to dangerous stress levels, fatigue and space debris, hence it is desirable to retract the solar array before satellite repositioning to avoid damage or failure. A novel concept of deployable/retractable hybrid solar array systemcomposed of both rigid and flexible solar panels arranged within a petal

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Qiu, Xuesong, Jian Liu, Peng Gui, and Ya’nan Wang. "Identification of chaotic phenomena in a flexible deployable solar panel with multiple clearances." Transactions of the Canadian Society for Mechanical Engineering, April 1, 2020, 1–15. http://dx.doi.org/10.1139/tcsme-2019-0240.

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Deployable solar panels are widely used in spacecraft, and the dynamic characteristics of the deployment process directly affect the accuracy, stability, and reliability of the deployment. The flexibility and hinge clearance of a solar panel are important factors affecting the dynamic characteristics of the deployment system. The finite element method (FEM) was used to deal with the deformations of the solar panel. A dynamic model of the deployment process of a flexible solar panel with multiple clearances was established by combining the Lagrange equation with the FEM. The dynamic characteris

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Shen, Yingyong, Jingbo Gao, Cong Wang, Shiyu Tan, Dehua Zhang, and Yuanyuan Li. "Dynamic Analysis of Bidirectional Solar Arrays with Flexible Panels and Clearance Joints." Journal of Spacecraft and Rockets, April 16, 2023, 1–12. http://dx.doi.org/10.2514/1.a35541.

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The dynamic characteristics of a two-step deployable bidirectional solar array system with flexible panels and clearance joints are studied in this paper. Driving mechanisms, closed cable loop configurations, and latch mechanisms are considered in this system where normal contact force is established using a nonlinear spring damping model and the friction effect is determined by a modified Coulomb friction model. With the simulation strategy of activating different constraint states and applying latch torques, the multiple deployment and locking processes of the system are implemented. The res

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"Evaluating Deployable Solar Panel Option in Earth Observation Micro-satellite Design Optimization." International Journal of Advances in Mechanical & Automobile Engineering 3, no. 1 (2016). http://dx.doi.org/10.15242/ijamae.iae0716207.

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Wang, Cunfu, and Bifa Chen. "Bending and torsional vibration attenuation of multi-panel deployable solar array using reaction wheel actuators." Aircraft Engineering and Aerospace Technology, July 8, 2022. http://dx.doi.org/10.1108/aeat-12-2021-0380.

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Purpose This paper aims to present a multi-axis actuating approach to attenuate the bending and torsional vibration of the solar array through the reaction wheel (RW) actuators. Design/methodology/approach The motion equation of the solar array with the RW actuators is derived in modal coordinates for controller design. The reaction torques, induced by the speed change of the RW actuators, are controlled for vibration attenuation through the constraints on the actuators’ rotating speed. The proposed control approach is firstly verified with numerical simulation on the finite element model of a

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Yang, Jingyi, Xiao Zhang, Yan Chen, and Zhong You. "Folding arrays of uniform-thickness panels to compact bundles with a single degree of freedom." Proceedings of the Royal Society A: Mathematical, Physical and Engineering Sciences 478, no. 2261 (2022). http://dx.doi.org/10.1098/rspa.2022.0043.

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Flat arrays consisting of panels of finite thickness are widely used in aerospace applications such as solar panels and reflectarray antennas. Packaging them into compact bundles without any voids and then deploying them bi-directionally to flat, continuous and accurate surfaces with a single degree of freedom (DoF) has challenged engineers for decades. Here, we present a solution based on origami of thick panels. In modular construction, we first created two deployable unit arrays, each of which comprises four eight-panel elements where panels in regular shapes are connected by simple but rob

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Horne, John K., Jackson A. Swan, Tommy J. Tracy, and Gordon W. Holtgrieve. "Automated acoustic monitoring of fish for near-real-time resource management." ICES Journal of Marine Science, December 12, 2023. http://dx.doi.org/10.1093/icesjms/fsad196.

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Abstract Freshwater fisheries in developing regions provide livelihoods and nutrition for millions of people worldwide. These fisheries are frequently data poor, which limits fisheries management. The seasonal Cambodian dai platform fishery on the Tonle Sap River is one of the best monitored inland fisheries in Southeast Asia, yet catch sampling is limited and there is no fishery-independent monitoring. A monitoring system is needed to characterize fish migration and mortality, be cost effective, and be deployable in areas with minimal infrastructure. We integrated a Simrad wide-band transceiv

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Nap, Ana, Fabian Walter, Martin Lüthi, and Adrien Wehrlé. "Self-sufficient seismic boxes for monitoring glacier seismology." Seismica 2, no. 1 (2023). http://dx.doi.org/10.26443/seismica.v2i1.245.

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Glacier seismology is a valuable tool for investigating ice flow dynamics, but sufficient data acquisition in remote and exposed glaciated terrain remains challenging. For data acquisition on a highly crevassed and remote outlet glacier in Greenland we developed self-sufficient and easily deployable seismic stations, "SG-boxes". The SG-boxes contain their own power supply via solar panel, a three-component omni-directional geophone and a GNSS receiver. The SG-boxes can be deployed and retrieved from a hovering helicopter, allowing for deployment in difficult terrain. To assess their performanc

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