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Статті в журналах з теми "Self deployable"

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Автор: Grafiati

Опубліковано: 26 травня 2023

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1

Neogi, Depankar, Craig Douglas, and David R. Smith. "Experimental Development of Self-Deployable Structures." International Journal of Space Structures 13, no. 3 (September 1998): 157–69. http://dx.doi.org/10.1177/026635119801300305.

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Анотація:

Deployable space structures are prefabricated structures which can be transformed from a closed, compact configuration to a predetermined expanded form in which they are stable and can bear loads. The present research effort investigates a new family of deployable structures, called self-deployable structures. Unlike other deployable structures, which have rigid members and moving joints, the self-deployable members are flexible while the connecting joints are rigid. The joints store the predefined geometry of the deployed structure in the collapsed state. The self-deployable structure is stress-free in both deployed and collapsed configurations and results in a self-standing structure which acquires its structural properties after a chemical reaction. Reliability of deployment is one of the most important features of the self-deployable structure, since it does not rely on mechanisms that can lock during deployment. The unit building block of these structures is the self-deployable structural element. Several of these elements can be linked to generate more complex building blocks such as a triangular or tetrahedral structures. Different self-deployable structural element and self-deployable structure concepts are investigated in the present research work, and the performance of triangular and tetrahedral prototype structures are experimentally explored.

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2

Dwiana ; Anastasia Maurina, Yosafat Bakti. "MODULAR BAMBOO STRUCTURE DESIGN EXPLORATION WITH DEPLOYABLE CONSTRUCTION SYSTEM." Riset Arsitektur (RISA) 3, no. 04 (October 5, 2019): 381–97. http://dx.doi.org/10.26593/risa.v3i04.3521.381-397.

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Abstract- Deployable structure is a type of structure that can be transformed from a closed configuration to an open configuration. This structure can be assembled and disassembled with ease. This easy construction is a reason why deployable structure is the right structure for after disaster scenario. In emergency, natural resources are needed since it can be found and used easily. Bamboo is a common plant that can be found everywhere in Indonesia. Research have been done by UNPAR’s architecture lecturer regarding deployable structure (deployable spatial and deployable planar) with bamboo as its material. It says that deployable spatial structure has easier and shorter time in instalation than deployable planar structure. Deployable spatial structure has tons of room for development. Some development that can be done is to make deployable structure module to be duplicated in every direction, and to implement self locking mechanism in this structure. This research is done to find deployable structure module that can be duplicated in every direction, and also implementing self locking mechanism in this structure Method that used in this research is qualitative by comparing some buildings that implementing deployable system (Resiploy and Triangle Prism) and modular system (Rising Canes and Y-BIO). The comparastion result is opportunity and thread from each building. This result which is opportunity and thread from each building then synthesized to find criteria for deployable structure that can be duplicated in every direction. Based on the research, it can be concluded that in deployable structure, nut and bolt is needed so that some building element can be rotated to create a movement. In modular building, we need a simple system that can be used in every joint so that building can be duplicated in every way with ease. Reciprocal structure is needed to make a building with self locking mechanism. By simplifying Resiploy’s joint and using Rising Canes’s modules, we can make a deployable structure that can be duplicated in every way with self locking mechanism Key Words: bamboo structure, deployable, modular, self locking mechanism

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3

Lyu, Tian, Shan Qin, ZiAng Tian, QiYue Zhang, YunJing Xu, and KeXin Lin. "Design of a Catapulted Self-deployable UAV." Journal of Physics: Conference Series 2181, no. 1 (January 1, 2022): 012042. http://dx.doi.org/10.1088/1742-6596/2181/1/012042.

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Abstract Unmanned Aerial Vehicle (UAV) is playing a gradually enhanced role in fields of recon and information acquisition, however restricted departure condition of fixed wing aircrafts, take-off preparation time of multirotor aircrafts etc. have limited its further applications. This research aims to combine advantage of hovering and self-deployable departure to reconcile the shortcomings, meanwhile adapts to drone swarm trend. A catapulted self-deployable quadrotor is designed using 3D modelling software, and later a compatible self-deployable control algorithm is developed using STM32F103 microcontroller, along with its circuitry. Eventually, a prototype of the design is 3D printed, assembled and tested. This design shows merits of easy to carry, low requirements for take-off conditions and good hovering performance and is compatible for multi-UAVs cooperation tendency.

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4

Bettini, William, Jérôme Quirant, Julien Averseng, and Bernard Maurin. "Self-Deployable Geometries for Space Applications." Journal of Aerospace Engineering 32, no. 1 (January 2019): 04018138. http://dx.doi.org/10.1061/(asce)as.1943-5525.0000967.

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5

del Grosso, Andrea E., and Paolo Basso. "Deployable Structures." Advances in Science and Technology 83 (September 2012): 122–31. http://dx.doi.org/10.4028/www.scientific.net/ast.83.122.

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Анотація:

Deployable structures have been developed for many different applications from space to mechanical and civil engineering. In the paper the general concepts of deployable structures, combining static and kinematic behaviour are presented first, also discussing their relationships with adaptive and variable geometry structures. Reported applications to civil engineering and architecture are then reviewed and categorized. The characteristics of the following systems are summarized : 1. Pneumatic Structures. 2. Tensegrity Structures. 3. Scissor-like Structures. 4. Rigid Foldable Origami. 5. Mutually Supported Structures. The problems of form finding, direct and inverse kinematics, actuation and self-deployability for some of the most interesting among the above structural types are then discussed in the paper. Some examples involving rigid foldable origami and mutually supported structures are finally presented.

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6

Cao, Xu, Yan Xu, Changhong Jiang, Qin Fang, and Hao Feng. "Simulation Investigation of the Stowing and Deployment Processes of a Self-Deployable Sunshield." International Journal of Aerospace Engineering 2021 (February 6, 2021): 1–14. http://dx.doi.org/10.1155/2021/6672177.

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The stowing and deployment processes of a self-deployable sunshield are investigated numerically in this paper. The composition of the self-deployable sunshield is described. Deployed moment theoretical models for lenticular booms are formulated based on the bending theory of curved shell. The numerical analysis method of deployed moment is proposed. Two types of control methods for a fold crease are presented, and a dynamic analysis model considering geometry and nonlinear contact is built. The analysis results indicate that the press flattening method can be used effectively for controlling the fold crease, and the analytical results of the deployed moment are very close to the theoretical results. A stowing and deployment process analysis of the self-deployable sunshield is conducted. Thus, the deployment configurations and the time history curves of the dynamic behaviors are obtained. The results verify the feasibility of the analysis model, and this study can provide technical support for the engineering application of the self-deployable sunshield.

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7

Mallikarachchi, H. M. Y. C., and S. Pellegrino. "Design of Ultrathin Composite Self-Deployable Booms." Journal of Spacecraft and Rockets 51, no. 6 (November 2014): 1811–21. http://dx.doi.org/10.2514/1.a32815.

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8

Zheng, Yuanqing, Guobin Shen, Liqun Li, Chunshui Zhao, Mo Li, and Feng Zhao. "Travi-Navi: Self-Deployable Indoor Navigation System." IEEE/ACM Transactions on Networking 25, no. 5 (October 2017): 2655–69. http://dx.doi.org/10.1109/tnet.2017.2707101.

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9

Sokolowski, Witold M., and Seng C. Tan. "Advanced Self-Deployable Structures for Space Applications." Journal of Spacecraft and Rockets 44, no. 4 (July 2007): 750–54. http://dx.doi.org/10.2514/1.22854.

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10

Jia, Bao Xian, Qing Cheng, and Wen Feng Bian. "Design of Deployable Antenna Based on SMPC." Advanced Materials Research 753-755 (August 2013): 1457–61. http://dx.doi.org/10.4028/www.scientific.net/amr.753-755.1457.

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Анотація:

In order to get the deployable antenna with light weight but large size and high stiffness, this study investigated SMPC self-deployable driver mechanism based on the deformation mechanism of SMPC, and designed the SMPC space deployable antenna. The laminated shell structure with two pieces of back-to-back configuration was analyzed. Finite element analysis revealed that the reasonable central angle of the laminated shell cross-section was 90°. The ends fixing structure of the SMPC hinge was given. The function and structure of the hoop truss deployable antenna were designed to meet the functional and accuracy requirements.

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11

Song, Ruiyu. "Manufacture Technologies for Magnetoactive Deployable Structures." Journal of Physics: Conference Series 2174, no. 1 (January 1, 2022): 012010. http://dx.doi.org/10.1088/1742-6596/2174/1/012010.

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Abstract Nowadays, smart materials like magnetoactive materials are utilized to manufacture deployable structures, enabling these mechanisms to self-fold under external magnetic fields. Fabrication of magneto-sensitive deployable structures have evolved from using discrete magnets to applying 4D printing-an emerging technique. The new printing concept expands the application area of magnetoactive mechanisms because properties of them can be predetermined and precise arrangement of magnetic domains are realized. This review summarizes fabrication technologies for magnetoactive deployable structures, including 4D printing.

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12

Rosenfeld, Yechiel, and Robert D. Logcher. "New Concepts for Deployable-Collapsable Structures." International Journal of Space Structures 3, no. 1 (March 1988): 20–32. http://dx.doi.org/10.1177/026635118800300103.

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Анотація:

Deployable-collapsable structures have many potential applications, ranging from emergency shelters and facilities, through relocatable semi-permanent structures, to space-station components. A new concept of self-stabilized/self-supported “clicking” structures – featuring stable, stress-free states in both deployed and collapsed forms – shows even greater promise. This article highlights the state-of-the-art in the field of deployable-collapsable structures and discusses their advantages and limitations. A unique concept of “clicking” structures is introduced, and its basic capabilities are presented and discussed. Finally future research needs are mapped out.

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13

Dai, Lu, and Fu Ling Guan. "Design and Manufacture of Double-Ring Deployable Truss." Advanced Materials Research 566 (September 2012): 357–60. http://dx.doi.org/10.4028/www.scientific.net/amr.566.357.

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Анотація:

To improve stiffness and strength of the deployable antenna truss and to keep the total weight and volume from increasing as caliber increases, this paper presents a new kind of deployable antenna truss with double-ring composed of hexahedrons. Numerical simulation was made by self-programming software and a scaled model of 4.2-meter diameter was designed and manufactured, which demonstrate the developability of double-ring deployable antenna truss. In addition, frequency analysis and experiment was taken to make sure of stiffness of the truss.

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14

Yang, Xu, Dongjingdian Liu, Jing Liu, Faren Yan, Pengpeng Chen, and Qiang Niu. "Follower: A Novel Self-Deployable Action Recognition Framework." Sensors 21, no. 3 (February 1, 2021): 950. http://dx.doi.org/10.3390/s21030950.

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Deep learning technology has improved the performance of vision-based action recognition algorithms, but such methods require a large number of labeled training datasets, resulting in weak universality. To address this issue, this paper proposes a novel self-deployable ubiquitous action recognition framework that enables a self-motivated user to bootstrap and deploy action recognition services, called FOLLOWER. Our main idea is to build a “fingerprint” library of actions based on a small number of user-defined sample action data. Then, we use the matching method to complete action recognition. The key step is how to construct a suitable “fingerprint”. Thus, a pose action normalized feature extraction method based on a three-dimensional pose sequence is designed. FOLLOWER is mainly composed of the guide process and follow the process. Guide process extracts pose action normalized feature and selects the inner class central feature to build a “fingerprint” library of actions. Follow process extracts the pose action normalized feature in the target video and uses the motion detection, action filtering, and adaptive weight offset template to identify the action in the video sequence. Finally, we collect an action video dataset with human pose annotation to research self-deployable action recognition and action recognition based on pose estimation. After experimenting on this dataset, the results show that FOLLOWER can effectively recognize the actions in the video sequence with recognition accuracy reaching 96.74%.

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15

Kim, Young Jo, Sang-Eun Chun, Jay Whitacre, and Christopher J. Bettinger. "Self-deployable current sources fabricated from edible materials." Journal of Materials Chemistry B 1, no. 31 (2013): 3781. http://dx.doi.org/10.1039/c3tb20183j.

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16

Zhuo, Shuyun, Gongzheng Zhang, Xianqi Feng, Haoyang Jiang, Jinli Shi, Huanqing Liu, and Huanjun Li. "Multiple shape memory polymers for self-deployable device." RSC Advances 6, no. 56 (2016): 50581–86. http://dx.doi.org/10.1039/c6ra06168k.

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17

Soykasap, Ömer. "Deployment analysis of a self-deployable composite boom." Composite Structures 89, no. 3 (July 2009): 374–81. http://dx.doi.org/10.1016/j.compstruct.2008.08.012.

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18

Pehrson, Nathan A., Daniel C. Ames, Samuel P. Smith, Spencer P. Magleby, and Manan Arya. "Self-Deployable, Self-Stiffening, and Retractable Origami-Based Arrays for Spacecraft." AIAA Journal 58, no. 7 (July 2020): 3221–28. http://dx.doi.org/10.2514/1.j058778.

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19

Pérez-Valcárcel, Juan, Manuel Muñoz-Vidal, Isaac López César, Félix Suárez Riestra, and Manuel Freire Tellado. "Deployable space grids with lockable joints." International Journal of Space Structures 36, no. 2 (March 17, 2021): 91–104. http://dx.doi.org/10.1177/09560599211002480.

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Анотація:

The use of deployable structures in architecture began in the 1960s, based on the pioneering work of Emilio Pérez Piñero. It has had an interesting development using bundle or scissor modules, but with solutions that are always based on through-bolted joints. In this document, a new system for deployable space grids is proposed. This new system is based on the use of self-lockable joints, opening up a new and interesting field of design possibilities. The resulting space grids can be deployed by means of joints arranged on the bars that have a self-locking mechanism which is engaged in the final open position. This configuration overcomes the significant buckling that is characteristic of deployable structures with through-bolted joints. Different solutions are proposed for various uses, and the data from the theoretical and experimental analysis are provided.

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20

Tuna, Turcan, Salih Ertug Ovur, Etka Gokbel, and Tufan Kumbasar. "Design and development of FOLLY: A self-foldable and self-deployable quadcopter." Aerospace Science and Technology 100 (May 2020): 105807. http://dx.doi.org/10.1016/j.ast.2020.105807.

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21

Li, Fengfeng, Liwu Liu, Xin Lan, Tong Wang, Xiangyu Li, Fanlong Chen, Wenfeng Bian, Yanju Liu, and Jinsong Leng. "Modal Analyses of Deployable Truss Structures Based on Shape Memory Polymer Composites." International Journal of Applied Mechanics 08, no. 07 (October 2016): 1640009. http://dx.doi.org/10.1142/s1758825116400093.

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Анотація:

With large spatial deployable antennas used more widely, the stability of deployable antennas is attracting more attention. The form of the support structure is an important factor of the antenna’s natural frequency, which is essential to study to prevent the resonance. The deployable truss structures based on shape memory polymer composites (SMPCs) have made themselves feasible for their unique properties such as highly reliable, low-cost, light weight, and self-deployment without complex mechanical devices compared with conventional deployable masts. This study offers deliverables as follows: an establishment of three-longeron beam and three-longeron truss finite element models by using ABAQUS; calculation of natural frequencies and vibration modes; parameter studies for influence on their dynamic properties; manufacture of a three-longeron truss based on SMPC, and modal test of the three-longeron truss. The results show that modal test and finite element simulation fit well.

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22

Lerouge, Sophie, Robert Guidoin, Tim Ashton, Marie-France Guidoin, André Pierre Legrand, Yvan Douville, and Gilles Soulez. "Nitinol self-deployable endovascular prostheses: variability in corrosion resistance." Annales de Chimie Science des Matériaux 29, no. 1 (January 31, 2004): 41–52. http://dx.doi.org/10.3166/acsm.29.41-52.

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23

Kristensen, Anders S., Martin D. Ulriksen, and Lars Damkilde. "Self-Deployable Deorbiting Space Structure for Active Debris Removal." Journal of Spacecraft and Rockets 54, no. 1 (January 2017): 323–26. http://dx.doi.org/10.2514/1.a33321.

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24

Neogi, Depankar, and Craig D. Douglas. "Design and Development of a Self Deployable Structural Element." International Journal of Space Structures 10, no. 2 (June 1995): 77–87. http://dx.doi.org/10.1177/026635119501000201.

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Over the past two decades there has been considerable need for reliable lightweight structures for various space applications, ranging from communication antennae to that of building the first space station. The impetus for research in the field of deployable space structures has been due to the volume constraint imposed by current launch vehicles. This paper describes the design and development of an advanced composite self deployable structural element (SDSE). In its predeployed state, the SDSE is a collapsed structural element designed to achieve minimum volume configuration. This makes it beneficial for space applications as it can be folded and compactly stowed in a space transport vehicle. Ideally, this structure will deploy at the site without human intervention. The SDSE is flexible in its unheated state. It is formed of a core of thermally activated expanding foam or pressurizing agent, an internal bladder, a load carrying member of braided advanced composite material, and an outer retaining jacket. The core material, upon hearing with a resistance wire, internally pressurizes the structural element which leads to deployment. The same heat source also cures the advanced composite material.

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25

Zhao, Longhai, Hao Wang, Genliang Chen, and Shunzhou Huang. "Sequentially Assembled Reconfigurable Extended Joints: Self-Lockable Deployable Structure." Journal of Aerospace Engineering 31, no. 6 (November 2018): 04018103. http://dx.doi.org/10.1061/(asce)as.1943-5525.0000877.

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26

Oueis, Jad, Vania Conan, Damien Lavaux, Herve Rivano, Razvan Stanica, and Fabrice Valois. "Core network function placement in self-deployable mobile networks." Computer Communications 133 (January 2019): 12–23. http://dx.doi.org/10.1016/j.comcom.2018.10.009.

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27

Santo, Loredana, Denise Bellisario, Leamdro Iorio, and Fabrizio Quadrini. "Shape memory composite structures for self-deployable solar sails." Astrodynamics 3, no. 3 (July 31, 2019): 247–55. http://dx.doi.org/10.1007/s42064-018-0044-7.

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28

Roh, Jin-Ho, and Jae-Sung Bae. "Softenable composite boom for reconfigurable and self-deployable structures." Mechanics of Advanced Materials and Structures 24, no. 8 (November 14, 2016): 698–711. http://dx.doi.org/10.1080/15376494.2016.1196776.

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29

ONO, Hayato, and Hiroshi FURUYA. "Concept of Convex Hinge Mechanisms for Self-Deployable Panels." Proceedings of Mechanical Engineering Congress, Japan 2022 (2022): J192–10. http://dx.doi.org/10.1299/jsmemecj.2022.j192-10.

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30

Tan, Zhong Qiang, Shi Jiao Wang, and Ming Yan Zhao. "Movement Function Reliability of Limit-Locking Mechanism of Space Cable-Strut Deployable Articulated Mast." Applied Mechanics and Materials 365-366 (August 2013): 344–50. http://dx.doi.org/10.4028/www.scientific.net/amm.365-366.344.

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The aim of the project is to study limit-locking mechanism of space cable-strut deployable articulated mast. Based on the discussion of structure and working principle, the mechanism's initial movement condition and self-locking angle are analyzed and a new analytical model of movement function reliability has been constructed. Combined with specific locking events, sliding pin's movement reliabilities are given in earlier and later stages. According to data from deployable mast, the reliability is calculated.

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31

Gillmer, Steven R., Mark J. Silver, and Sungeun K. Jeon. "A neural network-informed self-aware deployable structure with application to phased array antennas." Smart Materials and Structures 31, no. 4 (March 9, 2022): 045018. http://dx.doi.org/10.1088/1361-665x/ac58d2.

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Abstract State of the art radio frequency (RF) arrays are growing larger in pursuit of increased signal-to-noise ratio. In support of this goal, elaborate forms of metrology are being developed to support the increased footprints. This work provides a unique solution to fulfill the metrology requirements of large-scale deployable RF antennas through the implementation of neural network demodulation of fiber optic strain sensors. The fiber optics are patterned with fiber Bragg gratings (FBGs) to encode strain on to back-reflected shifts in the wavelength of incident light. Experiments show the neural network can predict the deformation of a test structure within single millimeters for small amplitude motions. Therefore, the current technique meets the required λ / 20 precision needed for large scale deployable RF arrays operating at S-band or longer wavelengths.

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32

Santo, Loredana, Fabrizio Quadrini, Antonio Accettura, and Walter Villadei. "Shape Memory Composites for Self-deployable Structures in Aerospace Applications." Procedia Engineering 88 (2014): 42–47. http://dx.doi.org/10.1016/j.proeng.2014.11.124.

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33

Wang, Wei, Nam-Geuk Kim, Hugo Rodrigue, and Sung-Hoon Ahn. "Modular assembly of soft deployable structures and robots." Materials Horizons 4, no. 3 (2017): 367–76. http://dx.doi.org/10.1039/c6mh00550k.

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Анотація:

The first soft deployable robot, called DeployBot, capable of both deploying itself and of movement without additional motors is introduced. This robot can serve as the first step toward a new class of soft robots that is modular, self-deploying, and capable of locomotion “out of the box”.

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34

Zeng, Chun Mei, Jing Chi Yu, and Pei Ji Guo. "Ultra-Lightweight Design and Analysis of a 1.25m SiC Segmented Mirror." Advanced Materials Research 230-232 (May 2011): 940–44. http://dx.doi.org/10.4028/www.scientific.net/amr.230-232.940.

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Анотація:

In order to explore the feasibility of large ultra-lightweight deployable optical systems, a 1.25m SiC segmented mirror is investigated. According to analysis and comparison, the mirror's material, ultra-lightweight structure pattern and support location are determined respectively. By FEM, an ultra-lightweight structure with areal density of 40kg/m2 is gotten. The results show that the self-weight deformation is 4.8nm RMS/22.6nm PV under supports, and the ultra-lightweight mirror has the enough strength to bear the stress at launch. The study may provide a technical scheme to develop the large ultra-lightweight deployable optical system.

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35

Russell, A. G. "Development of a Large Deployable Space Reflector Structure." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 206, no. 2 (July 1992): 111–23. http://dx.doi.org/10.1243/pime_proc_1992_206_248_02.

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This paper describes the selection, configuration, design and development of the 5 m diameter deployable reflector structure currently being undertaken jointly by British Aerospace Space Systems Limited and the University of Surrey. Large reflectors represent the most likely, near-term application of a large deployable space structure and offer the most promising opportunity for the development and qualification of the hardware required. Such a large, deployable reflector has to compete against other reflector designs which are not suitable for development into larger space structures but are optimized solely as reflector backing structures. These competitors provide a useful measurement of performance against which the development reflector may be compared in terms of mass, stiffness, cost and reliability. The proposed reflector comprises a radio frequency reflective surface of gold-plated molybdenum knitted wire mesh supported from the nodes of a tetrahedral truss. The development 5 m diameter reflector is made from six deployable tetrahedrons configured symmetrically around a central node. Larger reflectors are possible using the same concept with longer struts or by using an extension of this concept with extra rings of tetrahedrons. The solution is dependent upon the required reflector size and stowage volume restrictions. This design has brought together two critical items of hardware for a large deployable space structure: a simple, light, reliable self-latching hinge (developed by the Ministry of Defence and the University of Surrey) and a long, light, stiff, inexpensive carbon fibre tube (manufactured by the pultrusion technique).

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36

Gantes, C. J., R. D. Logcher, J. J. Connor, and Y. Rosenfeld. "Deployability Conditions for Curved and Flat, Polygonal and Trapezoidal Deployable Structures." International Journal of Space Structures 8, no. 1-2 (April 1993): 97–106. http://dx.doi.org/10.1177/0266351193008001-210.

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Prefabricated, deployable space frames that exhibit self-standing and stress-free states in both the deployed and collapsed configurations are investigated in this paper. This type of deployable structures shows considerable advantages as compared to previous designs that either required external stabilizing or had members with residual stresses in the deployed configuration. Following previous developments for flat deployable structures consisting of units with regular-polygon planviews, this study deals with flat structures made of trapezoidals, and curved structures assembled from regular-polygonal units. First, the general geometric constraints and deployability conditions for these units are formulated, and a methodology for using these constraints as geometric design criteria is presented. Furthermore, additional conditions for the assemblage of single units into larger structures are given. Then, structural analysis issues for this type of structures are discussed. The necessity of nonlinear analysis during deployment is emphasized. Finally, the above geometric design procedures are demonstrated with specific examples.

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37

Rosenfeld, Y., Y. Ben-Ami, and R. D. Logcher. "A Prototype “Clicking” Scissor-Link Deployable Structure." International Journal of Space Structures 8, no. 1-2 (April 1993): 85–95. http://dx.doi.org/10.1177/0266351193008001-209.

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The paper presents engineering details of a prototype scissor-link deployable structure and outlines a systematic development approach as an example of the steps involved in realizing a new idea. The arch-like structure consists of multiple pairs of scissor-linked rod elements, which can be deployed instantaneously to form a stable, spatial network and which can be collapsed to a compact bundle of nearly parallel rods. A momentary geometric non-fit during deployment causes large displacement bending or buckling and a self-stabilizing ာclickingိ effect which facilitates full deployment, and leaves the structure with no residual internal stresses after deployment. The paper concludes with recommendations for further experimental work on the subject.

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38

Gantes, Charis, Jerome J. Connor, and Robert D. Logcher. "A Systematic Design Methodology for Deployable Structures." International Journal of Space Structures 9, no. 2 (June 1994): 67–86. http://dx.doi.org/10.1177/026635119400900202.

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The deployable structures investigated in this paper are prefabricated space frames made of basic units consisting of two straight bars connected to each other by a pivot, the so called scissor-like-elements. They can be stored in a compact folded configuration, and can be easily deployed into large, load carrying forms by simple articulation. In order to avoid major disadvantages of previous designs, the structures examined here obey strict geometric rules so that they are self-standing and stress-free in both their folded and deployed configurations. During deployment however, geometric incompatibility between member lengths results in a geometrically nonlinear structural behaviour. The optimum design of such a structure has to provide a compromise between desired stiffness in the deployed configuration, and desired felxibility during deployment.

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39

Liu, Xinyuan, Fei Xing, Shaoyan Fan, and Zheng You. "A Compressed and High-Accuracy Star Tracker with On-Orbit Deployable Baffle for Remote Sensing CubeSats." Remote Sensing 13, no. 13 (June 26, 2021): 2503. http://dx.doi.org/10.3390/rs13132503.

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CubeSats have been widely used in remote sensing applications such as global coverage, hotspots revisited, etc. However, due to the strict size limitation, the high-accuracy measuring instruments such as star tracker are too large to be applied in CubeSat, thus causing insufficient accuracy in satellite attitude and image positioning. In order to reduce the volume of star tracker without compromising the performance, the relationship between the volume and pointing accuracy or dynamic performance is studied and an optimization model of star tracker with a minimum volume is proposed. Compared with the traditional star tracker, a deployable star tracker with a novel deployable baffle and surrounded circuit structure is designed. The baffle consists of nested three-stage sub-baffles with a scientifically analyzed and verified taper to achieve smooth deployment and compression. The special circuit structure surrounds the lens and can be compressed in the inner sub-baffle. Therefore, the deployable star tracker can be compressed to the smallest volume and the sub-baffles can be deployed to the accurate position without self-lock risk. The experimental results verify its deployment accuracy and reliability as well as space environmental adaptability. The deployable star tracker has almost the same results on stray light suppression ability, pointing accuracy (better than 3″ (3σ)) and dynamic performance (up to 3°/s) with the traditional star tracker. Furthermore, an integrated attitude determination and control system based on the deployable star tracker for CubeSat is further designed and implemented to support high-accuracy remote sensing.

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40

Yuan, S., B. Yang, and H. Fang. "Self-Standing Truss with Hard-Point-Enhanced Large Deployable Mesh Reflectors." AIAA Journal 57, no. 11 (November 2019): 5014–26. http://dx.doi.org/10.2514/1.j058446.

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41

Fernandes, P., R. Pinto, A. Ferrer, and N. Correia. "Performance analysis of a damage tolerant composite self-deployable elastic-hinge." Composite Structures 288 (May 2022): 115407. http://dx.doi.org/10.1016/j.compstruct.2022.115407.

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42

Todoroki, Akira, Keisuke Kumagai, and Ryosuke Matsuzaki. "Self-deployable Space Structure using Partially Flexible CFRP with SMA Wires." Journal of Intelligent Material Systems and Structures 20, no. 12 (May 27, 2009): 1415–24. http://dx.doi.org/10.1177/1045389x09337086.

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43

Wu, Rui, Peter C. E. Roberts, Shida Lyu, Constantinos Soutis, Fei Zheng, Carl Diver, Matthieu Gresil, and Jonny J. Blaker. "Rigidisation of deployable space polymer membranes by heat-activated self-folding." Smart Materials and Structures 27, no. 10 (September 18, 2018): 105037. http://dx.doi.org/10.1088/1361-665x/aadc72.

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44

TODOROKI, Akira, Keisuke KUMAGAI, and Ryosuke Matsuzaki. "1335 Self-deployable CFRP structures using Partially Flexible Composites with SMA." Proceedings of the JSME annual meeting 2008.6 (2008): 407–8. http://dx.doi.org/10.1299/jsmemecjo.2008.6.0_407.

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45

Senba, Atsuhiko, Yoichi Tsuji, and Hiroshi Furuya. "Fundamental characteristics of self-deployable convex shells using shape memory polymer." Acta Astronautica 180 (March 2021): 16–24. http://dx.doi.org/10.1016/j.actaastro.2020.11.037.

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46

Baek, Sang-Min, Sojung Yim, Soo-Hwan Chae, Dae-Young Lee, and Kyu-Jin Cho. "Ladybird beetle–inspired compliant origami." Science Robotics 5, no. 41 (April 15, 2020): eaaz6262. http://dx.doi.org/10.1126/scirobotics.aaz6262.

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Origami can enable structures that are compact and lightweight. The facets of an origami structure in traditional designs, however, are essentially nondeformable rigid plates. Therefore, implementing energy storage and robust self-locking in these structures can be challenging. We note that the intricately folded wings of a ladybird beetle can be deployed rapidly and effectively sustain aerodynamic forces during flight; these abilities originate from the geometry and deformation of a specialized vein in the wing of this insect. We report compliant origami inspired by the wing vein in ladybird beetles. The deformation and geometry of the compliant facet enables both large energy storage and self-locking in a single origami joint. On the basis of our compliant origami, we developed a deployable glider module for a multimodal robot. The glider module is compactly foldable, is rapidly deployable, and can effectively sustain aerodynamic forces. We also apply our compliant origami to enhance the energy storage capacity of the jumping mechanism in a jumping robot.

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47

Zawadzki, Adam, and Anna Al Sabouni-Zawadzka. "In Search of Lightweight Deployable Tensegrity Columns." Applied Sciences 10, no. 23 (December 4, 2020): 8676. http://dx.doi.org/10.3390/app10238676.

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In civil engineering, there is an occasional need to assure an additional support for a structure due to the loss of the load carrying capacity (e.g., as a result of natural disasters or aging) or for a lightweight structure to support temporary objects (e.g., tents, big advertisement banners, temporary antenna masts). In the present study, the authors propose deployable tensegrity columns to be used in such cases. This paper is aimed at answering the question: Which tensegrity column would be the best for the specified application? Four tensegrity columns are analyzed in various deployment configurations to find the answer to this question. Computer simulations are performed in the finite element (FE) and multibody dynamics (MBD) software to provide quantitative and qualitative results. The applied methods are validated by comparing self-stress states at various steps of the analysis. The most important part of the article is the comparative table, which contains quantitative results obtained from the performed analyses, which can be used to indicate the structures that are most appropriate for certain applications. The results may also be used as a starting point for research in other fields of science like robotics or mechatronics. This paper is focused on obtaining full data for building scaled models for laboratory tests in the future.

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48

Fernandes, P., R. Pinto, and N. Correia. "Design and optimization of self-deployable damage tolerant composite structures: A review." Composites Part B: Engineering 221 (September 2021): 109029. http://dx.doi.org/10.1016/j.compositesb.2021.109029.

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49

Bovesecchi, Gianluigi, Sandra Corasaniti, Girolamo Costanza, and Maria Elisa Tata. "A Novel Self-Deployable Solar Sail System Activated by Shape Memory Alloys." Aerospace 6, no. 7 (July 5, 2019): 78. http://dx.doi.org/10.3390/aerospace6070078.

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This work deals with the feasibility and reliability about the use of shape memory alloys (SMAs) as mechanical actuators for solar sail self-deployment instead of heavy and bulky mechanical booms. Solar sails exploit radiation pressure a as propulsion system for the exploration of the solar system. Sunlight is used to propel space vehicles by reflecting solar photons from a large and light-weight material, so that no propellant is required for primary propulsion. In this work, different small-scale solar sail prototypes (SSP) were studied, manufactured, and tested for bending and in three different environmental conditions to simulate as much as possible the real operating conditions where the solar sails work. Kapton is the most suitable material for sail production and, in the space missions till now, activated booms as deployment systems have always been used. In the present work for the activation of the SMA elements some visible lamps have been employed to simulate the solar radiation and time-temperature diagrams have been acquired for different sail geometries and environmental conditions. Heat transfer mechanisms have been discussed and the minimum distance from the sun allowing the full self-deployment of the sail have also been calculated.

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50

Roh, Jin-Ho, Hye-Jung Kim, and Jae-Sung Bae. "Shape memory polymer composites with woven fabric reinforcement for self-deployable booms." Journal of Intelligent Material Systems and Structures 25, no. 18 (July 22, 2014): 2256–66. http://dx.doi.org/10.1177/1045389x14544148.

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