Journal articles: 'Deployable structure'

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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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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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Du, Yuwen. "A New Design of the 3D Deployable Space Antenna Structure." Journal of Physics: Conference Series 2469, no. 1 (March 1, 2023): 012013. http://dx.doi.org/10.1088/1742-6596/2469/1/012013.

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Abstract Communication and energy supply are critical in different sophisticated space missions in the aerospace industry. However, rockets have limited launch space and cannot carry such a massive support system. A space antenna deployable structure based on the scissor element and ring truss structure is proposed to overcome this challenge. This research studies the basic unit and its connection structure separately to investigate the mobility of the deployable structure. The connection structure and the basic units have one degree of freedom. Subsequently, a deployable ring truss system for satellite antennas is demonstrated. The kinematic models of the basic units and common deployment mechanisms have been constructed to demonstrate the mechanism deployment performance. The designed deployable structure can further increase the mechanism’s deployment area by splicing multiple basic ring deployable structures. This newly designed space antenna deployable structure has greater flexibility and can effectively increase the deployment area of the ring truss.

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Song, Yi Jie, Chi On Ho, and Zi Fei Qing. "A Study of New Deployable Structure." Advanced Materials Research 1049-1050 (October 2014): 1083–89. http://dx.doi.org/10.4028/www.scientific.net/amr.1049-1050.1083.

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Deployable structures are new prefabricated frames that can be transformed from a closed stage or compact configuration to a predetermined, stable expanded form. The structure is very convenient for transportation and recycling because it can be stretched out, drawn back and disassembled into pieces easily. This paper describes a new deployable structure composed of scissor composite members, each of which consists of universal scissor components, connected by bolts, and braced by pre-tensioned ropes out-of-plane, conforming a stable system. An aluminum-alloy deployable model was fabricated and a test program was carried out under vertical load to evaluate the capacity of the structure. Numerical analysis using FEM was conducted for validation purpose. By studying the stability and capacity of the structure, comprehensive evaluations of the structure were made. Possessing several advantages stated in this paper, deployable structures can be used as semi-permanent and temporary large spatial buildings.

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Zhang, Hao, Chao Chao Zhou, Xi Ling Xie, and Tao Tao Li. "Analysis and Simulation of a New Type of Radial Deployable Structures." Advanced Materials Research 753-755 (August 2013): 1128–32. http://dx.doi.org/10.4028/www.scientific.net/amr.753-755.1128.

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Against the application of spatial structure field, a configuration design about hexagonal radial deployable structures is presented, and illustrates its working principle. According to the characteristics of its motion, the moving space of the structure is analyzed; the mechanical property of the deployable mast is fully analyzed. The stretch and shrink of the deployable mast is simulated by ADAMS, and modal of hinge joint is analyzed by Partran . Results show that the new type of radial deployable structures is reasonable and reliable to promote.

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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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Sun, Shu Feng, Jin Guo Liu, and Hang Chen. "Simulation and Analysis of Butterfly-Inspired Eclosion Deployable Structure." Applied Mechanics and Materials 461 (November 2013): 114–21. http://dx.doi.org/10.4028/www.scientific.net/amm.461.114.

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Deployable structures, as an important kind of structure, have been widely used in a variety of satellite antennas and space reflectors. The research of deployable structures usually faces a series of theoretical and technical challenges because the size and mass are not only the limitations of deployable structure but also the key issues in the design process. Nevertheless, the appearance of bionic provides a new concept to develop the deployable structures. Inspired by the eclosion and development of butterfly wings, a bionic inflatable deployment structure has been presented in this paper. The whole system of emulate model is established and has a simulation analyzed with the help of dynamic analysis software. This simulation is aimed at emulating the deploying process, and calculating the stress distribution of the structure. Then some relative curve fitting is conducted on the deploying trajectory. A prototype has been fabricated and tested to be able to deploy smoothly and steadily.

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Wang, Ying, and Bin Sun. "A Computational Method for Dynamic Analysis of Deployable Structures." Shock and Vibration 2020 (June 27, 2020): 1–10. http://dx.doi.org/10.1155/2020/2971784.

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A computational method is developed to study the dynamics of lightweight deployable structures during the motion process without regard to damping. Theory and implementation strategy of the developed method are given in this study. As a case study, the motion process of a bar-joint structure and a ring array scissor-type structure was simulated under external dynamic loading. In order to verify the effectiveness of the method, the simulation results are compared with the results predicted by the authenticated multibody system dynamics and simulation program. It shows that the method is effective to dynamic analysis of deployable structures no matter the structures are rigid or elastic. Displacement, velocity, and acceleration for the entire deployable structures during the motion process can be computed, as well as strain if the deployable structure is elastic.

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Chai, T. J., and C. S. Tan. "Review on deployable structure." IOP Conference Series: Earth and Environmental Science 220 (February 21, 2019): 012034. http://dx.doi.org/10.1088/1755-1315/220/1/012034.

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Lin, Fei, Chuanzhi Chen, Jinbao Chen, and Meng Chen. "Modelling and analysis for a cylindrical net-shell deployable mechanism." Advances in Structural Engineering 22, no. 15 (June 27, 2019): 3149–60. http://dx.doi.org/10.1177/1369433219859400.

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Existing cylindrical deployable structures have poor controllability of deployment or weak bearing capacity. In order to satisfy the application needs of cylindrical deployable structures in the space industry, a cylindrical net-shell deployable mechanism is established in this article. The proposed cylindrical net-shell deployable mechanism has a regular cuboid shape in the folded state and a truss structure in the deployed state, and it can fit cylindrical surface, parabolic cylindrical surface, sine cylindrical surface and so on. Furthermore, based on reciprocal screw theory and screw synthesis theory, the mobility of cylindrical net-shell deployable mechanism in the whole motion cycle is analysed by the proposed equivalent model method. Results show that the cylindrical net-shell deployable mechanism is a single-degree-of-freedom mechanism. Moreover, a prototype is manufactured, and its motion performance is tested. The experiment shows that the cylindrical net-shell deployable mechanism has a smooth motion performance, and the mobility analysis method for complex coupled mechanism in this study is valid. This study has a certain significance in expanding the application field of cylindrical shell structure.

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Wang, Dan Dan, Qiang Cong, Rong Qiang Liu, Cong Fa Zhang, Yan Wang, and Hong Wei Guo. "Driving Characteristic Analysis of a Planar Deployable Support Truss Structure for Space Antenna." Applied Mechanics and Materials 373-375 (August 2013): 54–64. http://dx.doi.org/10.4028/www.scientific.net/amm.373-375.54.

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As the development of space structures is increasing fast, analysis on the characteristics of those deployable structures deserve to be paid enough attention to ensure a reliable deployment on orbit. For a deployable truss structure, more than one position can be chosen as the driving positions, especially when the structure has not only 1 degree of freedom (DOF), an available choice of the driving positions shows significant importance on the performance of the space deployable structure. This paper mainly deals with a planar deployable support truss structure for space antenna by means of the closed loop equations and the Kane equation to discuss the deployment characteristics by comparison of the driving torque needed over time. A full comparison of all the possible examples of deployment analysis results under different driving modes is presented. The results show the importance of the choice of driving movements and the design of parameters and also provide a useful reference to other related truss structures.

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You, Z. "A Pantographic Deployable Conic Structure." International Journal of Space Structures 11, no. 4 (December 1996): 363–70. http://dx.doi.org/10.1177/026635119601100403.

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A pantographic structure, capable of forming a conic shape while deployed, is presented in this paper. It can be used as the backbone of a foldable tent or other mobile shelters. Different from most of the existing deployable structures, its deployment process induces no strain in the structural components. The geometric conditions given, together with a design for the joints, guarantee that the structure has only one internal degree of freedom. The concept has been successfully demonstrated by a small scale model. The same approach could be adopted while attempting to design other domed three-dimensional foldable pantographs.

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Zhou, Huai Dong, Peng Zhen, and Wu Sheng Chou. "Kinematic Analysis and Simulation of the Tri-Prism Deployable Structure." Applied Mechanics and Materials 799-800 (October 2015): 1183–87. http://dx.doi.org/10.4028/www.scientific.net/amm.799-800.1183.

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The Tri-prism deployable structure is a complex mechanism which consists of six deployable structure units in series. All deployable structure units have the similar movements; the screw theory is used to establish the kinematic equation of each unit and the entire tri-prism deployable structure. Meanwhile, the motion stability, drive mode and mechanical design of the tri-prism deployable structure have been comprehensively researched. Finally, extensive simulations in ADAMS have been conducted to obtain the relationship between the motions of ends and inputs, which are further compared with theoretical results.

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Chen, Yao, Jiayi Yan, and Jian Feng. "Mechanism Design with Singularity Avoidance of Crystal-Inspired Deployable Structures." Crystals 9, no. 8 (August 14, 2019): 421. http://dx.doi.org/10.3390/cryst9080421.

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Although deployable structures have important applications in various fields, developing a new form of structural configuration faces some scientific challenges. Furthermore, kinematic singularity frequently exists in these structures, which has a negative impact on deployment performance and stiffness. To deal with these problems, this paper obtains inspiration from crystals on two-dimensional (2D) space, and aims at developing symmetric deployable structures assembled by identical link members and periodic units. Mobility and compatibility conditions of crystal-inspired deployable structures are given, and a detailed design for novel joints with bevels gears is proposed to avoid singularity of these symmetric structures. According to feasible solutions to the compatibility conditions, several types of deployable structures are developed and verified to be mobile with a single degree of freedom. The results show that the proposed joint with bevel gears has a satisfactory singularity avoidance capability, and the assembled structures exhibit a good deployment performance. Because a crystal-inspired deployable structure can be gradually deployed to cover a large area, it has a potential engineering application as a macroscopic or mesoscale structure.

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Liu, Tinghao, and Guangbo Hao. "Design of Deployable Structures by Using Bistable Compliant Mechanisms." Micromachines 13, no. 5 (April 19, 2022): 651. http://dx.doi.org/10.3390/mi13050651.

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A deployable structure can significantly change its geometric shape by switching lattice configurations. Using compliant mechanisms as the lattice units can prevent wear and friction among multi-part mechanisms. This work presents two distinctive deployable structures based on a programmable compliant bistable lattice. Several novel parameters are introduced into the bistable mechanism to better control the behaviour of bistable mechanisms. By adjusting the defined geometry parameters, the programmable bistable lattices can be optimized for specific targets such as a larger deformation range or higher stability. The first structure is designed to perform 1D deployable movement. This structure consists of multi-series-connected bistable lattices. In order to explore the 3D bistable characteristic, a cylindrical deployable mechanism is designed based on the curved double tensural bistable lattice. The investigation of bistable lattices mainly involves four types of bistable mechanisms. These bistable mechanisms are obtained by dividing the long segment of traditional compliant bistable mechanisms into two equal parts and setting a series of angle data to them, respectively. The experiment and FEA simulation results confirm the feasibility of the compliant deployable structures.

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Kato, Junichi, Susumu Yoshinaka, and Yoshiya Taniguchi. "C03 System of deployable structure with stretchable membrane: DCMS (Deployable Closed-Membrane Structure)." Proceedings of the Space Engineering Conference 2013.22 (2013): _C03–1_—_C03–6_. http://dx.doi.org/10.1299/jsmesec.2013.22._c03-1_.

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Chew, M., and P. Kumar. "Conceptual Design of Deployable Space Structures from the Viewpoint of Symmetry." International Journal of Space Structures 8, no. 1-2 (April 1993): 17–27. http://dx.doi.org/10.1177/0266351193008001-203.

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The concept of symmetry is applied to the design of some existing as well as some new deployable space structures. Through the use of axis or plane symmetry, including anti-symmetry, a bay of a deployable structure may be reduced to an equivalent simple kinematic linkage. This axis of symmetry may be in the direction of deployment of the structure so that by providing a fictitious sliding joint along this axis, the problem of the design and analysis of such deployable structures can be simplified to the study of a plane or a face of the given structure. Such axis or plane of symmetry can also be used for the synthesis of new concepts. As an aid to synthesis, platonic solids can also be used for determining the orientation of these symmetric planes. Several examples are considered. A brief discussion on structural symmetry observed in graphs and dual graphs of some deployable structures will also be presented.

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Chen, Congcong, Tuanjie Li, Yaqiong Tang, and Zuowei Wang. "Analysis and control of state jump in space deployable structures under alternating temperature loads." Mechanical Sciences 12, no. 1 (February 4, 2021): 59–67. http://dx.doi.org/10.5194/ms-12-59-2021.

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Abstract. State jump has been experimentally observed in space deployable structures working in alternating temperature environments. State jump is a phenomenon in which the geometric shape of the structure changes after the temperature loading and unloading process, which makes the working accuracy of the space deployable structure intrinsically unpredictable. This paper aims to investigate the causes of this state jump phenomenon and seek measures to reduce its effect. Firstly, the static multiple-stable-state phenomenon resulting in state jump is analyzed for clearance joints in deployable structures. Then, an equivalent model consisting of a variable stiffness spring and a contact element for state jump analysis is proposed, which is verified by a finite element simulation. Influence factors and control methods of state jump are further explored. Finally, numerical results of a space deployable structure of an umbrella-shaped antenna show the effectiveness of the developed analytical method.

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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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Liu, Daoming, Davide Pellis, Yu-Chou Chiang, Florian Rist, Johannes Wallner, and Helmut Pottmann. "Deployable strip structures." ACM Transactions on Graphics 42, no. 4 (July 26, 2023): 1–16. http://dx.doi.org/10.1145/3592393.

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We introduce the new concept of C-mesh to capture kinetic structures that can be deployed from a collapsed state. Quadrilateral C-meshes enjoy rich geometry and surprising relations with differential geometry: A structure that collapses onto a flat and straight strip corresponds to a Chebyshev net of curves on a surface of constant Gaussian curvature, while structures collapsing onto a circular strip follow surfaces which enjoy the linear-Weingarten property. Interestingly, allowing more general collapses actually leads to a smaller class of shapes. Hexagonal C-meshes have more degrees of freedom, but a local analysis suggests that there is no such direct relation to smooth surfaces. Besides theory, this paper provides tools for exploring the shape space of C-meshes and for their design. We also present an application for freeform architectural skins, namely paneling with spherical panels of constant radius, which is an important fabrication-related constraint.

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YASAKA, Tetsuo, Isao OHTOMO, and Masahiro MINOMO. "Structure of deployable satellite antennas." Journal of the Japan Society for Aeronautical and Space Sciences 34, no. 389 (1986): 291–302. http://dx.doi.org/10.2322/jjsass1969.34.291.

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Fenci, Giulia E., and Neil GR Currie. "Deployable structures classification: A review." International Journal of Space Structures 32, no. 2 (June 2017): 112–30. http://dx.doi.org/10.1177/0266351117711290.

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Deployable structures have the capacity to transform and predictably adopt multiple predetermined configurations, moving through known paths, while deploying in a controlled and safe way. These characteristics introduce benefits when considering issues such as ease of transportation, erection and the overall sustainability of the structure by means of high material efficiency, modularisation and maximum use of natural energy resources. The aim of this article is to provide a critical review of existing attempts at classifying deployable structures identifying connections between different families through their mechanical and structural behaviours. The classifications selected consider theoretical and applied deployable structures, not focusing on a single application of deployable structures but including those ranging from spatial applications, to temporary and disaster relief structure, through to medical applications, providing coherence where terminology varies between applications. In order to gain a consistent understanding, tree diagrams were created for the review/classification to allow drawing commonalities and establishing differences between authors. A chronological approach was adopted, using key review work as focal points for the timeline, complemented by smaller more specific pieces of work. This enabled the identification of common features and divergences between the different authors, bringing to the conclusion that a clear, comprehensive, consistent and unified classification of deployable structures is currently missing within the field.

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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 (February 2, 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 deployable mechanisms. Thus, deployable parallel mechanisms have tremendous potential to be applied in the design of spatial solar panels, elastic reconfigurable robotic modules, etc. With reference to the kinematic analysis of parallel mechanisms, a finite and instantaneous screw method for kinematics of deployable parallel mechanisms is proposed, which is a generic method that is suitable for displacement and velocity modeling and analysis of any deployable parallel mechanism. A typical mechanism with symmetrical structure is taken as an example to show the validity of the proposed method, and simulation and experiment are carried out to verify the obtained results of kinematics. This paper puts forth the basic concepts of deployable parallel mechanisms and lays a theoretical foundation for their kinematic modeling and analysis.

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Chai, Teck Jung, Cher Siang Tan, and Shahrin Mohammad. "Structural performance of half scissor-like elements deployable structure." E3S Web of Conferences 347 (2022): 01005. http://dx.doi.org/10.1051/e3sconf/202234701005.

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An experimental investigation on the Half Scissor-Like Elements (H-SLEs) mechanism deployable structure under compression axial load is presented. Two prefab cylindrical shape H-SLEs mechanism deployable steel structures namely M1 (Bolted base column) and model M2 (Unbolted base column) were tested on their performance in term of strength and stability performance. The model prototype consists coldformed and hot roll steel with bolted connection and tested at deployed vertical configuration. Compression axial load was applied at the middle top of loading platform, transferred equally to the six H-SLEs deployable mechanism through supporting beams. The experimental results obtained indicated that three types of failure modes, i.e. excessive bearing capacity failure at lipped C-section flange around bolt hole perimeter, instability due to horizontal displacement at mid-height of H-SLEs deployable mechanism (Bolted joint area) and member buckling. Among these failures, horizontal displacement nominated the overall structure stability while section thickness impacts member bucking and bearing capacity. The experimental ultimate load was 1.63% greater than BS EN 1993 design load resistance for M1 condition while 30% less for M2 condition. The applied load difference between these two model prototypes was 31.15%. Thus, M1 ultimate loads capacity was satisfactory since less than 15% acceptable level while M2 not satisfactory. Beside, horizontal displacement was identify highly impacted scissor mechanism deployable structure instability and suitable member thickness may avoid section premature failure.

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Freire-Tellado, M. J., M. Muñoz-Vidal, and J. Pérez-Valcárcel. "Scissor-Hinged Deployable Structures Supported Perimetrally on Rectangular Bases." Journal of the International Association for Shell and Spatial Structures 61, no. 2 (June 1, 2020): 158–72. http://dx.doi.org/10.20898/j.iass.2020.204.009.

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Deployable bar structures on a rectangular base present the problems of closing the ends and longitudinal stabilization. Some proposals have been made to resolve them, mainly by creating mouths, but their application to composite geometries is problematic.<br/> On-the-bias deployable structures adequately solve both problems as they are supported around their entire perimeter, have a strong three-dimensional operation and only use load-bearing bars. The text analyses this type of deployable structures, their requirements and possibilities.<br/> A study on the combination of polar and translational units in a single deployable structure is then carried out, focusing on the study of on-the-bias deployable structures with perimeter polar modules that allow the effective height of the designs to be increased. Finally, the architectural possibilities of the system are studied, which make it possible to resolve overhangs, vertical openings in the roof, and T- or L-shaped ground plans, guaranteeing the modularity of the system.

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Tian, Dake, Xiaodong Fan, Junwei Zhang, Lu Jin, Rongqiang Liu, and Yu Zhang. "Networking Method for the Structure of a Large Modular Deployable Space Antenna." International Journal of Aerospace Engineering 2022 (September 26, 2022): 1–13. http://dx.doi.org/10.1155/2022/4583374.

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A high-precision networking method for a modular deployable antenna with ultramultiple modules is proposed to solve the problem of achieving an accurate formation of the structure of a large-aperture modular deployable space antenna. In accordance with the general requirements for the deployment surface of deployable antennas, the structure composition and deployment principle of a deployable antenna are analyzed, and the topological law of a hexagonal prism modular structure is expounded. On the basis of basic theories of differential geometry, analytical geometry, and robotics, the mathematical model of an envelope circle and that of its center are established. Then, a networking model of structure that includes 61 modules in the fully deployed state is established. Finally, the established model is verified via a numerical simulation method, and the influence law of structural parameters on networking characteristics is analyzed and studied. Simulation results show that the networking method can realize an accurate connection of multiple modules. The networking method for the structure of a modular deployable antenna proposed in this study can provide a reference for research on basic theory of a deployable antenna’s mechanism and related engineering applications.

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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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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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Yao, Huaibo, Yixin Huang, Wenlai Ma, Lei Liang, and Yang Zhao. "Dynamic Analysis of a Large Deployable Space Truss Structure Considering Semi-Rigid Joints." Aerospace 10, no. 9 (September 21, 2023): 821. http://dx.doi.org/10.3390/aerospace10090821.

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Joints are widely used in large deployable structures but show semi-rigidity due to performance degradation and some nonlinear factors affecting the structure’s dynamic characteristics. This paper investigates the influence of semi-rigid joints on the characteristics of deployable structures in orbit. A virtual connection element of three DOFs is proposed to model the semi-rigid joints. The governing equations of semi-rigid joints are established and integrated into the dynamic equation of the structures. A series of numerical experiments are carried out to validate the proposed model’s accuracy and efficiency, and the deployable truss structures’ static and dynamic responses are analyzed. The results show that semi-rigid joints exacerbate the effects of an in-orbit microvibration on the stability of deployable truss structures. Semi-rigid joints lower the dominant frequencies of structures, leading to a ‘closely-spaced-frequencies’ phenomenon and altering the dynamic responses significantly. The effects of semi-rigid joints on deployable truss structures are long-term and can be used to establish a relationship model between structural performance and service life. Nonlinear effects vary with the external load and depend on the structures’ instantaneous status. These results indicate that semi-rigid joints significantly influence the characteristics of deployable structures, which must be considered in the design and analysis of high-precision in-orbit deployable structures.

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Razevicius, Gvidas, Anne Roudaut, and Abhijit Karnik. "HoberUI: An Exploration of Kinematic Structures as Interactive Input Devices." Multimodal Technologies and Interaction 8, no. 2 (February 13, 2024): 13. http://dx.doi.org/10.3390/mti8020013.

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Deployable kinematic structures can transform themselves from a small closed configuration to a large deployed one. These structures are widely used in many engineering fields including aerospace, architecture, robotics and to some extent within HCI. In this paper, we investigate the use of a symmetric spherical deployable structure and its application to interface control. We present HoberUI, a bimanual symmetric tangible interface with 7 degrees of freedom and explore its use for manipulating 3D environments. We base this on the toy version of the deployable structure called the Hoberman sphere, which consists of pantographic scissor mechanisms and is capable of homogeneous shrinkage and expansion. We first explore the space for designing and implementing interactions through such kinematic structures and apply this to 3D object manipulation. We then explore HoberUI’s usability through a user evaluation that shows the intuitiveness and potential of using instrumented kinematic structures as input devices for bespoke applications.

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Kwan, A. S. K. "A Parabolic Pantographic Deployable Antenna (PDA)." International Journal of Space Structures 10, no. 4 (December 1995): 195–203. http://dx.doi.org/10.1177/026635119501000402.

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This paper introduces a new proposal in deployable structures using the ‘active/passive substructure concept’. The proposed structure is a parabolic deployable antenna consisting of radial planar pantograph masts deployed by long multi-segmented deployment cables, and intermediate cablenets. Analytical techniques and results of static load tests on a simple validation model are also presented.

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Ding, Shuyong, Min Sun, Yang Li, Weili Ma, and Zheng Zhang. "Novel Deployable Panel Structure Integrated with Thick Origami and Morphing Bistable Composite Structures." Materials 15, no. 5 (March 5, 2022): 1942. http://dx.doi.org/10.3390/ma15051942.

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This paper proposes a novel deployable panel structure integrated with a bistable composite structure and thick panel based on the thick origami technique. To overcome the interference effects between thick panels, the axis shift method is used in this deployable structure design. Bistable composite structures are employed as hinges for morphing characteristics. The trigger force and load-displacement curves of the structure are obtained by experiments and numerical simulations. The factors that affect the coverage area-to-package volume ratio and trigger force are discussed. The experimental and numerical results verify that the structure has two stable configurations and a large coverage area-to-package volume ratio.

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ARITA, Shoko, Kazunari TODA, and Yoshiki YAMAGIWA. "Examination of Thermal Structure of Deployable Cubic Structure." Proceedings of Mechanical Engineering Congress, Japan 2020 (2020): J19202. http://dx.doi.org/10.1299/jsmemecj.2020.j19202.

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Salamah, Hafshah, Andry Widyowijatnoko, Surjamanto Wonorahardjo, and Rakhmat Fitranto Aditra. "Deployable structure as architectural active structure on sports building in Bandung." MATEC Web of Conferences 197 (2018): 17004. http://dx.doi.org/10.1051/matecconf/201819717004.

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Buildings not only can be resilient from environmental changing by passive design, but also have ability to adapt the environment by active system. By using deployable structure, this system can be provided by changing multiple form based on its purpose to cover the building. To provide these conditions, deployable structure need to be explored and analyzed to develop compatible structure in the building. Case of study in this research is Pajajaran sports building in Bandung. The research method is exploration of form and movement based on limited variables, there are activities and weather changing/climate condition. These variables formulated into two conditions, open and closed building. Open building state in sports building have requirement that either natural or artificial lighting should not cause glare in field area. So, natural lighting was simulated by using Ecotect Analysis to find solar path movement and shadow angle. The result of the solar path simulation shows that daily solar movement must be responded directly because high rotation rate and regular changes, while the monthly sun path does not require significant movement due to low rotation rate and insignificant changes. This study will show design process of deployable structure into sports building.

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Jin, Yulong, Tao Liu, Rongxin Lyu, Bin Ji, and Qifeng Cui. "Theoretical Analysis and Experimental Investigation on Buckling of FASTMast Deployable Structures." International Journal of Structural Stability and Dynamics 15, no. 05 (May 27, 2015): 1450075. http://dx.doi.org/10.1142/s0219455414500758.

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FASTMast (Folding Articulated Square Truss Mast) deployable structure is the main bracing structure for the flexible solar array of the international space stations. This study investigates the buckling of FASTMast deployable structures. To this end, the buckling modes and the stiffness characteristics of this structure using the flex batten as an elastic bearing member were theoretically analyzed. The analytical results show that (1) the buckling mode of a FASTMast deployable structure is similar to the elbow joint movement failure when the stiffness of the flex batten is below a critical stiffness value. Once this critical stiffness is reached, the buckling mode takes on the form of Euler buckling. (2) The stiffness of the flex batten is proportional to its cross-sectional second moment of area. Furthermore, an experimental study was carried out to validate the accuracy of the theoretical analysis. The results from experimental work agree fairly well with those from theoretical analysis. The research findings herein are expected to be useful for future studies on similar structures.

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Luo, Ani, Heping Liu, Cheng Li, and Yongfan Wang. "Study of a Flowerlike Deployable Structure." Strojniški vestnik – Journal of Mechanical Engineering 59, no. 4 (April 15, 2013): 216–22. http://dx.doi.org/10.5545/sv-jme.2012.482.

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Zhang, Hong-Hua, H. Matsuo, Y. Morita, and H. Yamakawa. "Stabilization of a deployable flexible structure." Acta Astronautica 43, no. 7-8 (October 1998): 369–76. http://dx.doi.org/10.1016/s0094-5765(98)00172-6.

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IMURA, Nobuyoshi, Takeshi YAMADA, Hiroshi SAEGUSA, Yasumasa HISADA, and Yasuyuki ITOH. "Large Deployable Structure on Space Craft." Journal of the Society of Mechanical Engineers 88, no. 805 (1985): 1355–60. http://dx.doi.org/10.1299/jsmemag.88.805_1355.

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Gonzalo, F. Ama, Mariano Molina, Covadonga Lorenzo, M. I. Castilla, Pulido D. Gomez, Millan J. Garcia, and J. C. Sancho. "Geometric Analysis of a Modular, Deployable and Reusable Structure." Key Engineering Materials 805 (June 2019): 155–60. http://dx.doi.org/10.4028/www.scientific.net/kem.805.155.

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The use of deployable structures has a wide range of applications nowadays. They can be transformed from a closed compact configuration to a predetermined expanded form, in which they are stable and can carry loads. This article describes a sort of deployable structure that has been patented by researchers of two Spanish institutions: San Pablo CEU University and Eduardo Torroja Institute. Geometric aspects are key to accomplish an efficient folding and unfolding procedure along with an optimum structural behavior when the structure is deployed. Tensioned cables are essential in these structures. The main goal is to make the cable acquire its maximum length when the structure is fully deployed. This will avoid complex operations of post-tensioning in order to make the cable perform its function.

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Li, Xiaohan, and Sigen A. "Optimization of Deployable Antennas: Material, Structure and Drive Mode." Innovation in Science and Technology 3, no. 2 (March 2024): 55–65. http://dx.doi.org/10.56397/ist.2024.03.08.

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This research investigates the optimisation of deployable antennas by focusing on material selection, structural design, and drive mode. Deployable antennas are crucial for applications such as satellite communication and remote sensing. The study aims to enhance their efficiency and reliability through a comprehensive optimisation approach. A systematic review identifies suitable materials based on mechanical, electrical, and environmental properties. The structural design analysis explores various deployment mechanisms, such as foldable, inflatable, and tensegrity structures. Additionally, the drive mode optimisation examines actuation methods, including motor-driven, shape memory alloy, and piezoelectric systems, assessing their precision, energy consumption, and adaptability. The findings contribute to the development of more efficient, reliable, and versatile deployable antennas, improving the capabilities of communication systems.

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Wu, Xin Yan, and An Ping Luo. "Asynchronous Phenomenon of the Ring Truss Deployable Antenna." Applied Mechanics and Materials 170-173 (May 2012): 3415–18. http://dx.doi.org/10.4028/www.scientific.net/amm.170-173.3415.

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The deployable structure of the ring truss have advantage properties, which can be used as an effective supporting structure of deployable antenna. The deployable experiment of ring truss antenna showed that there was asynchronous phenomenon at the course of the deployment. Dynamics theory including constraint equations and considering friction factor are built firstly. Then simulation is studied systematically for the deployment process of ring truss deployable antenna. At last, the conclusions are obtained that the friction insulted in tensile forces of the cable drive decrease and the asynchronous phenomenon in the process of the deployment. It will give some help to the design and manufacture of the ring truss antenna.

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Luo, Ani, He Ping Liu, Yong Fan Wang, Jian Hua Song, Wen Tao Ma, Wen Jin Mao, and Qing Fu Zeng. "Analysis of Instability for the String-Net Structure in the Deployable Antenna." Key Engineering Materials 572 (September 2013): 529–32. http://dx.doi.org/10.4028/www.scientific.net/kem.572.529.

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There is a wide application for the string-net structure in the areas of architecture and spaceflight. In the area of spaceflight, the string-net structure is mainly used in the deployable antenna. The three-dimensional string-net structure is a kind of typical string-net structures applied on the deployable antenna. Here the string-net structure is analyzed. At first, composition of the string-net structure is presented. Then the dynamical relaxation method is used to obtain the solution for movement of the structure after its instability. At last, using numerical simulation, tensions in the strings are computed. It is proved finally that the three-dimensional string-net structure still possesses the capability of keeping its shape and stiffness after its instability.

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Lin, Fei, Chuanzhi Chen, Jinhua Zhou, and Yuhang Dai. "Hanger forces optimization of ground test device on deployable structure." International Journal of Space Structures 36, no. 2 (March 26, 2021): 127–36. http://dx.doi.org/10.1177/09560599211005099.

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When using suspension method to simulate the microgravity environment, part of the hanger forces are used to offset the influence of gravitational field on the deployable structure, while the other part produces additional forces that affect the driving forces and precision of the deployable structure. In order to reduce the adverse effect of hanger forces, and avoid the construction of complex finite element theoretical model, an optimization method based on adaptive genetic algorithm with MATLAB and Nastran co-simulation is proposed. Then, the hanger forces are optimized, and the deployable structure deformation has been reduced 49%. It suggests that the adverse effect of hanger forces has been effectively reduced and the proposed optimization method works well.

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Chen, Mei, Fei Zheng, and Na Li. "Mesh Mapping of Large Deployable Reflector in Mechanical - Electromagnetic Analyses." Advanced Materials Research 460 (February 2012): 43–47. http://dx.doi.org/10.4028/www.scientific.net/amr.460.43.

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Ultra lightweight large deployable reflector antenna is gradually used nowadays in space applications. Both lightweight structures and materials are used. The relationship between the structure design and the electromagnetic performances is much tighter than other ground electric devices. This paper presents a mesh mapping method of large deployable reflector in mechanical - electromagnetic analyses. By using this method, the mechanical deformations can be precisely transformed on the electromagnetic model. It can be used to understand the relationship between the mechanical deformations and the electromagnetic performances on such a huge, complex structure.

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Hu, Haotian, Zhenmeng Xia, Qiang Tao, Zixin Ye, Kaifeng Yuan, and Leying Song. "Self-Unfolding Properties of Smart Grid-Reinforced Membrane Origami." Journal of Composites Science 8, no. 2 (February 7, 2024): 64. http://dx.doi.org/10.3390/jcs8020064.

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Origami-based membrane structures have shown great potential to revolutionize the construction of deployable and lightweight space structures in the future. However, the efficient unfolding mechanism puts forward major challenges to the practical realization of space-deployable structures. Here, a smart grid-reinforced membrane origami (SGRMO) is presented. The unfolding action hinges upon the application of forces facilitated by shape memory polymer composites (SMPCs). Subsequent locking action ensues through the restoration of the initial rigidity, accomplished via cooling mechanisms. This novel structure achieves the required lightweight and functionality by employing the grid design concept and effectively reduces the decline in unfolding extent caused by irreversible plastic deformation at the crease. Its recovery properties, including unfolding angle, distance, and surface precision, are experimentally and analytically investigated under different conditions. The results indicate that the structure can be reliably unfolded into the predefined shapes. In the case of Miura-SGRMO, the optimal surface precision is attained when the angle-ψ registers at 30°. The results of this study are expected to serve as the design of ultra-large flexible solar arrays and deployable antenna structures.

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Jin, Lu, Feiyang Zhang, Dake Tian, Qinghe Wang, and Quanyu Cao. "Thermal-Structural Analysis of the Support Structure for a Modular Space Deployable Antenna." International Journal of Aerospace Engineering 2022 (June 3, 2022): 1–13. http://dx.doi.org/10.1155/2022/2164485.

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A modular space deployable antenna has the advantages of extensibility, adaptability, and versatility, which is an ideal structure to meet the development trend of large aperture, high precision, and light weight for the deployable antenna in the future. To date, there are few reports on the temperature response of a modular deployable antenna in the thermal alternating environment in orbit. The aim of this study is at investigating the influence of a modular deployable antenna support structure on the surface accuracy and stability under the space thermal alternating environment. For this purpose, the thermal-structure analysis of the deployable antenna support structure was carried out by ANSYS APDL finite-element software. Using the transient temperature field obtained by thermal analysis as the boundary condition, the coupling law of stress development and thermal deformation of the support chord and cable caused by the antenna structure constraint position and other parameters is analyzed. In a uniform thermal field, the thermal stress of cables in the central module of the structure is the highest and that of the chord components in the same-circle modules is essentially the same. The thermally stress of the upper chords increases progressively toward the outer module, whereas that of cables decreases in the same direction. The thermal deformation at the upper-layer centroid of the structure can reach about 15 mm, so the influence on the accuracy of the antenna cannot be ignored. When the splicing vertical rod of adjacent modules in the outermost of the support structure is taken as the constraint connecting with the extension arm, the thermal deformation of the structure is minimum. The heat-insulating composite coating should be adopted on the surface of the antenna structure to reduce the thermal deformation and improve the adaptability. The thermal-structural analysis model proposed in this study could accurately estimate the behaviour of thermal deformation for the modular space deployable antenna, but the further coupling condition of the nonuniform temperature field could still be conducted. The results can provide a reference for the basic theory and engineering application of thermal-structural analysis for extralarge-aperture modular deployable antennas in the future.

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Friedman, Noémi, György Farkas, and Adnan Ibrahimbegovic. "Parametric Study of the Elementary Segment of an Antiprismatic Pop-Up Deployable Lattice Column." YBL Journal of Built Environment 2, no. 2 (December 1, 2014): 65–86. http://dx.doi.org/10.1515/jbe-2014-0011.

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Abstract In this article the primary segment of an antiprismatic pop-up mast is analyzed, that can be applied for largely flexible architectural designs, like deployable bridges or transportable look-out towers. This deployable column, consisting of rigid plates, rigid and elastic bars, is characterized by its selfdeploying behavior due to the energy accumulated from lengthening the elastic bars during packing. The main goal of this paper is to prepare the analysis of the complex structure by a herein detailed investigation of the behavior of one, basic element of the deployable mast. After the analytical examination of the general behavior of the basic segment a geometrically nonlinear finite element formulation is used to trace the force-displacement diagram. Besides the parametric study, approximations of main mechanical parameters are herein given for facilitating preliminary design of such deployable structures.

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Peng, Qi’an, Sanmin Wang, Bo Li, Changjian Zhi, and Jianfeng Li. "Dynamics Analysis of Deployable Structures considering a Two-Dimensional Coupled Thermo-Structural Effect." International Journal of Aerospace Engineering 2018 (October 4, 2018): 1–10. http://dx.doi.org/10.1155/2018/1752815.

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The deployment accuracy of deployable structures is affected by temperature and flexibility. To obtain the higher accuracy, various measures such as the optimization design and the control process are employed, and they are all based on deployment dynamics characteristics of deployable structures. So a precise coupled thermo-structural deployment dynamics analysis is important and necessary. However, until now, only a one-dimensional thermal effect is considered in the literatures because of simplicity, which reduces the accuracy of the model. Therefore, in this paper, a new model coupling mechanical field with a temperature field is presented to analyze the deployment dynamics of a deployable structure with scissor-like elements (SLEs). The model is based on the absolute nodal coordinate formulation (ANCF) and is established via a new locking-free beam element whose formulation is extended to account for the two-dimensional thermally induced stresses due to the heat expansion for the first time. Namely, in the formulation, the thermal influences are along two-dimensional directions, the axial direction and the transverse direction, rather than along a one-dimensional direction. The validity and precision of the proposed model are verified using a flexible pendulum example. Finally, the dynamics of a linear deployable structure with three SLEs modeled by the element is simulated under a temperature effect.

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Schmidt, Lewis C., and Hewen Li. "Shape Formation of Deployable Metal Domes." International Journal of Space Structures 10, no. 4 (December 1995): 189–94. http://dx.doi.org/10.1177/026635119501000401.

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This paper presents a new approach for forming and erecting deployable metal domes. The approach is basically one where the whole structure is assembled initially at ground level in an essentially flat condition. By the use of appropriate post-tensioning, the space structure can be erected and shaped simultaneously. Based on previous studies on deployment principle and geometric models, this paper present an approach to investigate the appropriate way of post-tensioning for the shape formation and erection of the metal domes by means of finite element analyses. An example is given to illustrate the main steps in shape formation of the deployable metal domes, and the results of the example show that this new approach is reliable and feasible. Potentially, the procedure can offer economies over traditional methods of construction of such structures.

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Pérez-Egea, Adolfo, Pedro García Martínez, Martino Peña Fernández-Serrano, Pedro Miguel Jiménez Vicario, and Manuel Alejandro Ródenas-López. "The influence of joint eccentricity on the foldability of four deployable structure systems." International Journal of Space Structures 37, no. 1 (October 4, 2021): 3–21. http://dx.doi.org/10.1177/09560599211048441.

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The study of deployable structures has been carried out traditionally by simplifying their constituent elements—joints and rods—to ideal entities. However, in this paper the dimensional thickness of these elements is taken into account, in order to evaluate their incidence on the foldability of four deployable structure systems. We have examined the eccentricity that occurs specifically at the joints themselves. Our study ultimately characterizes the incidence of this factor by defining noteworthy parameters common to both tube bundle and scissor systems, enabling us to establish a comparison and draw relevant conclusions.

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Pérez-Egea, Adolfo, Pedro García Martínez, Martino Peña Fernández-Serrano, Pedro Miguel Jiménez Vicario, and Manuel Alejandro Ródenas-López. "The influence of joint eccentricity on the foldability of four deployable structure systems." International Journal of Space Structures 37, no. 1 (October 4, 2021): 3–21. http://dx.doi.org/10.1177/09560599211048441.

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The study of deployable structures has been carried out traditionally by simplifying their constituent elements—joints and rods—to ideal entities. However, in this paper the dimensional thickness of these elements is taken into account, in order to evaluate their incidence on the foldability of four deployable structure systems. We have examined the eccentricity that occurs specifically at the joints themselves. Our study ultimately characterizes the incidence of this factor by defining noteworthy parameters common to both tube bundle and scissor systems, enabling us to establish a comparison and draw relevant conclusions.

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50

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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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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Journal articles on the topic 'Deployable structure'

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