Relevant bibliographies by topics / Deployable structure

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  1. Journal articles
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Academic literature on the topic 'Deployable structure'

Author: Grafiati
Published: 4 June 2021
Last updated: 25 May 2024

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Journal articles on the topic "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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Dissertations / Theses on the topic "Deployable structure"

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Sibai, Munira. "Optimization of an Unfurlable Space Structure." Thesis, Virginia Tech, 2020. http://hdl.handle.net/10919/99908.

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Deployable structures serve a large number of space missions. They are vital since spacecraft are launched by placing them inside launch vehicle payload fairings of limited volume. Traditional spacecraft design often involves large components. These components could have power, communication, or optics applications and include booms, masts, antennas, and solar arrays. Different stowing methods are used in order to reduce the overall size of a spacecraft. Some examples of stowing methods include simple articulating, more complex origami inspired folding, telescoping, and rolling or wrapping. Wrapping of a flexible component could reduce the weight by eliminating joints and other components needed to enable some of the other mechanisms. It also is one of the most effective methods at reducing the compaction volume of the stowed deployable. In this study, a generic unfurlable structure is optimized for maximum natural frequency at its fully deployed configuration and minimal strain energy in its stowed configuration. The optimized stowed structure is then deployed in simulation. The structure consists of a rectangular panel that tightly wraps around a central cylindrical hub for release in space. It is desired to minimize elastic energy in the fully wrapped panel and hinge to ensure minimum reaction load into the spacecraft as it deploys in space, since that elastic energy stored at the stowed position transforms into kinetic energy when the panel is released and induces a moment in the connected spacecraft. It is also desired to maximize the fundamental frequency of the released panel as a surrogate for the panel having sufficient stiffness. Deployment dynamic analysis of the finite element model was run to ensure satisfactory optimization formulation and results.
Master of Science
Spacecraft, or artificial satellites, do not fly from earth to space on their own. They are launched into their orbits by placing them inside launch vehicles, also known as carrier rockets. Some parts or components of spacecraft are large and cannot fit in their designated space inside launch vehicles without being stowed into smaller volumes first. Examples of large components on spacecraft include solar arrays, which provide power to the spacecraft, and antennas, which are used on satellite for communication purposes. Many methods have been developed to stow such large components. Many of these methods involve folding about joints or hinges, whether it is done in a simple manner or by more complex designs. Moreover, components that are flexible enough could be rolled or wrapped before they are placed in launch vehicles. This method reduces the mass which the launch vehicle needs to carry, since added mass of joints is eliminated. Low mass is always desirable in space applications. Furthermore, wrapping is very effective at minimizing the volume of a component. These structures store energy inside them as they are wrapped due to the stiffness of their materials. This behavior is identical to that observed in a deformed spring. When the structures are released in space, that energy is released, and thus, they deploy and try to return to their original form. This is due to inertia, where the stored strain energy turns into kinetic energy as the structure deploys. The physical analysis of these structures, which enables their design, is complex and requires computational solutions and numerical modeling. The best design for a given problem can be found through numerical optimization. Numerical optimization uses mathematical approximations and computer programming to give the values of design parameters that would result in the best design based on specified criterion and goals. In this thesis, numerical optimization was conducted for a simple unfurlable structure. The structure consists of a thin rectangular panel that wraps tightly around a central cylinder. The cylinder and panel are connected with a hinge that is a rotational spring with some stiffness. The optimization was solved to obtain the best values for the stiffness of the hinge, the thickness of the panel, which is allowed to vary along its length, and the stiffness or elasticity of the panel's material. The goals or objective of the optimization was to ensure that the deployed panel meets stiffness requirement specified for similar space components. Those requirements are set to make certain that the spacecraft can be controlled from earth even with its large component deployed. Additionally, the second goal of the optimization was to guarantee that the unfurling panel does not have very high energy stored while it's wrapped, so that it would not cause large motion the connected spacecraft in the zero gravity environments of space. A computer simulation was run with the resulting hinge stiffness and panel elasticity and thickness values with the cylinder and four panels connected to a structure representing a spacecraft. The simulation results and deployment animation were assessed to confirm that desired results were achieved.
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Tulloss, Jr Robert Stuart. "Optimization of Geometric Parameters for a Deployable Space Structure." Thesis, Virginia Tech, 2021. http://hdl.handle.net/10919/104873.

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Deployable structures are used for many different spacecraft applications like solar arrays, antennas, and booms. They allow spacecraft with large structural components to comply with the volume restrictions of launch platforms. This research optimizes the shape and size of these structural components with both the stowed and deployed configurations in mind. HEEDS, a commercial optimization software, and ABAQUS, a commercial finite element analysis software, are used to evaluate and alter the structure using a single simulation. This makes the design process more efficient than running many different simulations individually. The optimization objectives, design variables, and constraints are chosen to fit the mission requirements of the structure. The structure analyzed in this research is a composite tube with a compressible cross-section wrapped around a cylinder. The change in cross-section reduces the bending stiffness of the tube and allows it to be wrapped without damaging the material. The dimensions controlling cross-section shape and the thickness of the composite layers are the design variables for the optimization. The maximum strain energy stored in the wrapped tube, the minimum volume of the structure, and the minimum weight of the tube are the objectives for the optimization. The strain energy is maximized to get the stiffest possible structure and satisfy the minimum natural frequency constraint. The weight and volume of the tube are minimized because reducing weight and volume is important for any spacecraft structure. Constraints are placed on the design variables and objectives and the Hashin damage criteria are used to ensure wrapping does not cause material failure. Three optimization runs from different initial designs are completed using SHERPA and genetic algorithm optimization methods. The results are compared to determine which optimization method performs best and how the different starting points affect the final results. After the optimized design is found, the full wrapping and deployment simulation is completed to analyze the behavior of the optimized design.
Master of Science
Spacecraft are launched into space using launch vehicles. There is limited room inside the launch vehicle for the spacecraft, but the spacecraft often needs large components like solar panels, antennas, and booms to complete the mission. These components must be designed in a way that allows them to be stowed in a smaller space. This can be accomplished by designing a system that can change the configuration of the component once the spacecraft is in orbit. This is referred to as a deployable structure, and the objective of this research is to create an optimization method for designing this type of structure. This is challenging because both the stowed and deployed configurations must be considered during the optimization. HEEDS, a commercial optimization software, and ABAQUS, a commercial structural analysis software, are used to evaluate and optimize the structure in a single simulation. The optimization objectives, design variables, and constraints are chosen to fit the mission requirements of the structure. The structure examined in this research is a composite tube with a compressible cross-section wrapped around a cylinder. As the tube is wrapped, it flattens, reducing the bending stiffness so the tube can be wrapped without damaging the material. The variables controlling cross-section shape and the thickness of the composite material layers will be altered during the optimization. The maximum strain energy stored in the wrapped tube, the volume of the tube, and the minimum weight of the tube are the objectives for the optimization. The strain energy is maximized to get the stiffest possible tube when it is unwrapped to ensure there is enough stored energy to facilitate the full deployment and to satisfy the minimum natural frequency constraint. The weight and volume of the tube are minimized because reducing weight and volume is important for any spacecraft structure. Constraints are placed on the design variables and objectives and the Hashin damage criteria are used to ensure wrapping does not cause material failure. The Hashin damage criteria use the strength of the material and the stresses on the material to determine if it is likely to fail. Three optimization runs with different starting points are completed for both the SHERPA and genetic algorithm optimization methods. The results are compared to determine which optimization method performs best and how the different starting points affect the final results. After the optimized design is found, the full wrapping and deployment simulation is completed to analyze the behavior of the optimized design.
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Gan, Wei Woei. "Analysis and design of closed-loop deployable frame structure." Thesis, University of Cambridge, 2009. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.599290.

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With the advancement of membrane/blanket technology as an alternative choice to the conventional solid panels deployment for assemblies such as solar arrays, solar sails and radar antennas, the need for new ultra-lightweight to deployable frame design is rapidly growing. The demand requires the structure to be more robust, more reliable, have a higher payload-to-area ratio and easier to control. Answering the call is a frame structure consisting of rigid bars and mechanical joints, which should ideally have only one uniquely defined mechanism and a relatively high packaging ratio. Presented herewith is a systematic study of the kinematics of the family of structures in numerical way. We are able to reveal considerable insights of the structural mechanism which can be obtained through careful study of singular values and rank deficit of the kinematic matrix of a structure, from which issues important for design, such as sensitivity can be analysed. The study also enables the simulation of deployment of structure with certain degrees of manufacture imperfection where under rigid body hypothesis, has no mechanism. Presented also is a novel deployable structure which belongs to a spatial over-constrained mechanical linkages family. Consisting of six bars, this structure can form an expanded quadrilateral rectangular frame and folded up to a compact bundle. Our analysis and experimental results both confirm that the structure has only one mechanism along its deployment path. The mechanism appears to be a favourable potential for deploying and supporting flexible active surface of solar/radar structures, as its two outer and opposite bars always remain parallel throughout the whole deployment process. With the development of this analytical approach, considerable insights into the kinematic behaviour of spatial over-constrained linkages can be revised and analysed. It has also become possible to design assemblies with special properties, e.g. frame with some particular dimension or non-symmetry.
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Jian, Bingcong. "Origami-based design for 4D printing of deployable structures." Thesis, Bourgogne Franche-Comté, 2020. http://www.theses.fr/2020UBFCA029.

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Les structures déployables peuvent être déformées entre les différentes configurations par des mécanismes prédéterminés, ce qui montre le grand potentiel de nombreuses applications d'ingénierie. Cependant, leurs mécanismes complexes rendent également très difficile la conception de leur structure. Avec les développements croissants en impression 4D, ses caractéristiques d'auto-transformation sous des stimuli externes offrent de nouvelles possibilités pour le déploiement de structures actives, complexes et difficiles. En outre, l'ingénierie basée sur les origamis a fourni un soutien technique considérable pour la transformation des structures, en particulier en passant par les états 2D à 3D, ce qui a conduit à de nombreuses études de conception basées sur des structures déployables inspirées de l'origami. Toutefois, la relation complexe entre la géométrie de la structure déployable et les matériaux et paramètres techniques connexes de l'impression 4D n'a pas été étudiée en profondeur. Actuellement, le manque de méthodologie de conception basée sur les origamis pour l'impression 4D fait toujours défaut. Dans ce travail de recherche, nous nous concentrons sur l'exploration des connexions internes entre les multiples niveaux d'abstraction allant de la structure globale du produit et l'affectation spécifique des matériaux et la conception géométrique afin d'aligner la bonne stratégie de conception sur une technique d'impression 4D spécifique. En bref, ce travail se veut être une ligne directrice pour la conception de structures actives déployables. Pour démontrer cet objectif, nous avons d'abord introduit les informations de base de l'impression 4D, de la conception basée sur les origamis et des structures déployables. Ensuite, nous avons analysé et résumé l'état d'avancement de leurs recherches et les difficultés existantes. Ensuite, nous proposons un cadre de conception systématique pour la conception de structures actives par impression 4D. Chaque étape de l'ensemble du processus de conception est présentée en détail, en particulier la conception de modèles d'origami basée sur la stratégie "3D-2D-3D" et la planification et le contrôle de la séquence de pliage. Enfin, sur la base des connaissances existantes, nous appliquons ce processus de conception à la structure active déployable et fournissons quelques études de cas illustratives
Deployable structures can be deformed between the different configurations through predetermined mechanisms, showing the great potential in many engineering applications. However, their exquisite and intricate mechanisms also bring a great difficulty to the design of its structure. With the growing 4D printing efforts, its self-transforming characteristics under external stimuli provide new possibilities for deploying complex and challenging driving structures. Furthermore, origami-based engineering has provided tremendous technical support for structural conversion, especially from 2D to 3D states, leading to many design studies based on origami-inspired deployable structures. However, the complicated relationship between the deployable structure's geometry and the related materials and engineering parameters of 4D printing has not been thoroughly explored. Currently, the origami-based design methodology for 4D printing is still missing. In this research work, we focus on exploring the internal connections between the multiple abstraction levels over the overall product structure to the specific material allocation and geometric design to make the right design strategy aligned to a specific 4D printing technique. In short, this work intends to be a guideline for designing active deployable structures. To demonstrate this objective, we first introduced the basic information of 4D printing, origami-based design, and deployable structures. Then we analyzed and summarized their research status and existing difficulties. Secondly, we propose a systematic design framework for active structure design by 4D printing. Each step in the entire design process is then introduced in detail, especially the origami pattern design based on the "3D-2D-3D" strategy and the folding sequence planning and control. Finally, based on the existing knowledge, we apply this design process to the active deployable structure and provide some illustrative case studies
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Huang, Weimin. "Shape memory alloys and their application to actuators for deployable structures." Thesis, University of Cambridge, 1998. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.299009.

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Dahl, Marcus. "Design and Construction of a Self-Deployable Structure for the Moon House Project." Thesis, KTH, Lättkonstruktioner, 2015. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-185024.

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This master thesis describes the design and construction of a prototype for the Moon House project. The goal was to develop a structural concept which ultimately will allow a 2 × 2.5 × 3 m3 house to be deployed on the surface of the Moon as an art installation. A 1 to 5 scale model was built and tested. Provided is background information on lightweight and inflatable technology for space applications. This is then reviewed together with earlier work related to the Moon House project in order to come up with a feasible design. The structure consists of a frame made out of plain-weave glass fiber tape springs. These are joined with plastic connectors and the frame is covered in a thin rip-stop polyester film. Elastic folds and pin-jointed hinges allow the structure to be folded, thus reducing its stowed volume. Deployment of the house is achieved with a combination of pressurization and elastically stored strain energy in the tape springs from folding of the structure. The tape springs have been tailored using specific lay-up and geometry to achieve an efficient folding scheme. The final structure was designed in Solid Edge and connectors were 3D-printed in plastic material. Deployment tests have been performed with partial success. Points of improvement have been identified and recommendations are made for future work.
Detta examensarbete behandlar design och konstruktion av en prototyp för Månhusprojektet. Målet var att ta fram ett strukturellt koncept för en stuga med dimensionerna 2 × 2, 5 × 3 m3 som skall kunna veckla ut sig själv på månens yta. En modell i skala 1 till 5 byggdes och testades. Rapporten innehåller bakgrundsinformation om olika konstruktioner, uppblåsbara och utfällningsbara, för rymdapplikationer. Detta utvärderas sedan, tillsammans med tidigare arbete relaterat till projektet, mot kravspecifikationer, f¨or att ta fram en ny design. Resultatet ¨ar en struktur bestående av s.k. “Tape springs” tillverkade i vävd glasfiber. De olika elementen kopplas samman med skarvar av plast. Detta utgör en ram, som sedan kläds med tunn rip-stop polyester. Elastiska veck kombinerat med mekaniska gångjärn gör att strukturen kan packas ihop till en mindre volym. Utfällning av strukturen möjliggörs med en kombination av trycksättning och elastiskt lagrad energi från den påtvingade vikningen. Genom att variera laminatens egenskaper och geometri fås strukturella element som ger ett effektivt vikningsschema. Strukturen togs fram med hjälp av Solid Edge ST6 och plastskarvarna 3D-printades. Test av utfällningen har gjorts med delvis lyckade resultat. Problem och potentiella förbättringar har identifierats och rekommendationer ges för fortsatt utveckling av konceptet.
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Nelson, Todd G. "Art to Engineering: Curved Folding and Developable Surfaces in Mechanism and Deployable Structure Design." BYU ScholarsArchive, 2018. https://scholarsarchive.byu.edu/etd/6865.

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This work investigates how curved-crease origami and the developable surfaces which compose it can be transitioned to engineering design. Methods for creating flexible, tailorable-property surfaces that function as thick panels in place of paper are presented. Concepts from curved-crease origami and developable surfaces that can describe and extend engineering applications are discussed and demonstrated. These concepts are particularly beneficial to applications where curved surfaces are integral to the function, deployability is desired, and planar manufacturing could be beneficial.The first part of this work uses arrays of compliant elements to create flexible-tailorable property surfaces. The key feature to these arrays is the alignment of the most flexible bending axis of the individual elements to the ruling line arrangement of a developable surface. This alignment can enable bending of thick panels while maintaining lower stresses, a quality necessary for the transitioning of curved-crease origami into thick materials. The stiffness and stress of these arrays is modeled and physical prototypes are demonstrated. Additionally, shape factors are developed for these compliant arrays (CAs) to facilitate material selection for the panels and understand how the geometry of the array changes the effective properties of the panel. The second part of this work describes and demonstrates several concepts of curved-crease origami and developable surfaces that can benefit mechanism and structure design, particularly in the context of rolling-contact mechanisms. The design of a rolling-contact joint connected by flexible bands similar to a Jacob's Ladder toy is extended through incorporating curved creases into the design. The resulting design is deployable from a compact state to a functional state and can be manufactured from a single plane and folded into shape. Mathematical formulations are presented to describe the classes of developable surfaces in terms of properties which are frequently important in mechanism design. These natural equations for a single class of developable surface are conducive to modeling the folding motion of rigid-ruling developables, developables whose ruling lines do change location in a surface during folding. These formulations are used to generalize the design of rolling-contact joints to a family of joints capable of single degree of freedom spatial motions, being manufactured from a plane, and exhibiting a tailorable force response. Finally practical design suggestions for the implementation of rolling-contact joints is given. These include methodology to create sunken flexures which serve to increase the normal force between rolling bodies to prevent slip.
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Smith, Samuel Porter. "Development of an Origami Inspired Composite Deployable Structure Utilizing Compliant Joints as Surrogate Folds." BYU ScholarsArchive, 2021. https://scholarsarchive.byu.edu/etd/9270.

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This work presents the design and construction of a self-deployable, self-stiffening,and retractable (SDSR) space array from carbon fiber reinforced polymers (CFRP’s) and a working prototype is demonstrated. The effort required developing principles for the design of high-strain composite flexural joints and their integration into angled composite panels. Designing LET arrays in angled panels is explored. Analysis of simple composite LET joints is presented for two degrees of freedom. Validation of the composite LET modeling is sought through numerical methods and empirical testing. Testing of several composite LET joint specimens is conducted and the results are reported. Results indicate that (while not as compact as their isotropic material counterparts) composite laminates can successfully use LET joints as surrogate folds.
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Donley, Stephen John. "Initial identification and investigation of parameters for choosing the most appropriate rapidly assembled or deployable structure." Thesis, Springfield, Va. : Available from National Technical Information Service, 2001. http://handle.dtic.mil/100.2/ADA393183.

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ACCETTURA, ANTONIO GABRIELE. "Self-deployable structures for advanced space applications: analysis, design and small scale testing." Doctoral thesis, Università degli Studi di Roma "Tor Vergata", 2014. http://hdl.handle.net/2108/203118.

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The aim of this PhD project is to evaluate, design, manufacture and test Self- Deployable structures using a Shape Memory Composite (SMC) technology to be used on advanced space applications, including both small and large space structures such as solar sails, antennas, solar panels and de-orbiting systems. This technology can also enable innovative missions from debris capture to solar system exploration and more. In particular SMPs based mechanisms are here proposed, and feasibility is demonstrated by means of experimental tests targeted to show their suitability to space applications. After a review on space mechanisms and SMC applications, selected designs have been proposed and test campaigns have been performed, including material characterization and the deployment of small scale prototypes. Even if this is only a starting point, achieved results are in accordance with literature and provide an original contribution to the self-deployable structures for space applications.
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Books on the topic "Deployable structure"

1

George C. Marshall Space Flight Center., ed. Ground test article for deployable space structure systems. [Marshall Space Flight Center], Ala: National Aeronautics and Space Administration, George C. Marshall Space Flight Center, 1985.

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Baumeister, Joseph F. Comparative thermal analysis of the space station Freedom Photovoltaic Deployable Boom structure using TRASYS, NEVADA, and SINDA programs. [Washington, DC]: National Aeronautics and Space Administration, 1989.

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Pellegrino, S., ed. Deployable Structures. Vienna: Springer Vienna, 2001. http://dx.doi.org/10.1007/978-3-7091-2584-7.

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1974-, Chen Yan, ed. Motion structures: Deployable structural assemblies of mechanisms. London: Spon Press, 2011.

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Deployable structures: Analysis and design. Southampton: WIT Press, 2001.

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Schenk, Axel. Modal identification of a deployable space truss. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1990.

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S, Pappa Richard, and Langley Research Center, eds. Modal identification of a deployable space truss. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1990.

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Center, Langley Research, ed. Structures for remotely deployable precision antennas. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1989.

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M, Mikulas Martin, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., eds. Deployable controllable geometry truss beam. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1985.

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Dyer, J. E. Development of a verification program for deployable truss advanced technology. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1988.

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Book chapters on the topic "Deployable structure"

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Sokolowski, Witold M. "Comparison with Other Space Deployable Structures." In Cold Hibernated Elastic Memory Structure, 169–72. First edition. | Boca Raton, FL : CRC Press/Taylor & Francis Group, 2018.: CRC Press, 2018. http://dx.doi.org/10.1201/9780429425950-22.

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Melnyk, Virginia Ellyn. "Customized Knit Membrane Deployable Hyperboloid Tower." In Computational Design and Robotic Fabrication, 433–42. Singapore: Springer Nature Singapore, 2024. http://dx.doi.org/10.1007/978-981-99-8405-3_36.

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AbstractDeployable structures have become increasingly popular due to their ability to transform from a compact form into a larger structure. They are also typically lightweight, resulting in a lower carbon footprint than heavy permanent building methods. These structures are popular within the field of architecture, as well as in robotics, aerospace engineering, and other fields.This paper explores the design and development of a deployable hyperboloid structure with a connected knitted membrane. The knitted material is specifically designed to stretch and fit the transforming geometry of the hyperboloid. This is achieved by manipulating the types of yarn used across the membrane, as well as the number of short rows in the knit material, to create a more specified material. The design for this material was developed using Rhino3d and Grasshopper. Throughout the design and fabrication process, there was a feedback loop between the digital design models and physical material test samples to ensure that the knit would fit the final hyperboloid structure. The result is a two-meter-tall structure when upright and a two-meter-diameter circle when collapsed, with a knit membrane that supports the structure and transforms seamlessly by stretching and shrinking to the different shapes of transformation.
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Liu, Liwu, Haiyang Du, Wei Zhao, Yanju Liu, and Jinsong Leng. "Applications of SMPC in Deployable Space Structures." In Cold Hibernated Elastic Memory Structure, 177–205. First edition. | Boca Raton, FL : CRC Press/Taylor & Francis Group, 2018.: CRC Press, 2018. http://dx.doi.org/10.1201/9780429425950-24.

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Mitsugi, Jin, Kazuhide Ando, and Yumi Senbokuya. "A FEM for Complex Deployable Structure Analysis." In IUTAM-IASS Symposium on Deployable Structures: Theory and Applications, 281–90. Dordrecht: Springer Netherlands, 2000. http://dx.doi.org/10.1007/978-94-015-9514-8_30.

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Haas, Fabian. "Wing Folding in Insects: A Natural, Deployable Structure." In IUTAM-IASS Symposium on Deployable Structures: Theory and Applications, 137–42. Dordrecht: Springer Netherlands, 2000. http://dx.doi.org/10.1007/978-94-015-9514-8_15.

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Kobayashi, Hidetoshi, Masashi Daimaruya, and Hirofumi Fujita. "Unfolding of Morning Glory Flower as a Deployable Structure." In Solid Mechanics and Its Applications, 207–16. Dordrecht: Springer Netherlands, 2003. http://dx.doi.org/10.1007/978-94-017-0371-0_21.

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Kobayashi, H., M. Daimaruya, and J. F. V. Vincent. "Folding/Unfolding Manner of Tree Leaves as a Deployable Structure." In IUTAM-IASS Symposium on Deployable Structures: Theory and Applications, 211–20. Dordrecht: Springer Netherlands, 2000. http://dx.doi.org/10.1007/978-94-015-9514-8_23.

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Wang, Xingze, Biao Li, Lin Li, Xiao Li, Duanling Li, and Kaijie Dong. "Modal Optimization Analysis of Large-Scale Modular Deployable Structure for SAR." In Advances in Mechanical Design, 1389–400. Singapore: Springer Singapore, 2017. http://dx.doi.org/10.1007/978-981-10-6553-8_90.

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Goorts, K., and S. Narasimhan. "The Role of Control-Structure Interaction in Deployable Autonomous Control Systems." In Conference Proceedings of the Society for Experimental Mechanics Series, 301–8. Cham: Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-74421-6_40.

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Arora, Hemant, Vrushang Patel, B. S. Munjal, and Sudipto Mukherjee. "Parametric Optimization of Joints and Links of Space Deployable Antenna Truss Structure." In Lecture Notes in Mechanical Engineering, 363–74. Singapore: Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-16-1769-0_33.

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Conference papers on the topic "Deployable structure"

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Luo, Ani, Quanhe Li, Te Xiao, Lingying Kong, Longkun Wang, Qinghua Zhang, Yuanyuan Wang, and Heping Liu. "Cylindrical Tensegrity Deployable Structure." In ASME 2015 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/imece2015-50861.

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The string-bar deployable structure should be a main direction for creating the new truss deployable structure applied in the spaceflight. A cylindrical tensegrtiy deployable structure is researched in the text. At first, referring to a cylinder folded with papers, a cylindrical tensegrity is presented in the text. Relationship between nodes and members of the structure is researched to set up the connectivity matrix. The coordinates of the nodes and connectivity matrix are applied further to obtain the lengths of all the members. Using nodes matrix, member matrices, connectivity matrix and external force matrix, the internal force density matrix of the tensegrity structure in equilibrium is solved. Considering the failure constraints, the force density of the members is optimized to get minimal mass of the structure. A model is built to verify the feasibility of the method for designing the tensegrity structure. Considering that lengths of all the bars are constant, length changes of all the strings are researched when the tensegrity structure is compressed and elongated along its axis. The methods for connecting the strings are analyzed further. All the analytical results are applied to set up an experimental model. The experimental model is tested to prove that the designed mechanism can be deployed and folded. So the design is successful. Through research in the text, a cylindrical tensegrity deployable structure is obtained. Methods for building the tensegrity structure and transforming it into a deployable structure can be proper to design of other deployable structures.
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WEEKS, G. "Dynamic analysis of a deployable space structure." In 26th Structures, Structural Dynamics, and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1985. http://dx.doi.org/10.2514/6.1985-593.

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Gdoutos, Eleftherios, Alan Truong, Antonio Pedivellano, Fabien Royer, and Sergio Pellegrino. "Ultralight Deployable Space Structure Prototype." In AIAA Scitech 2020 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2020. http://dx.doi.org/10.2514/6.2020-0692.

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Smith, Ralph, and Lawrence Robertson. "Design of a Membrane Aperture Deployable Structure." In 44th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/6.2003-1494.

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Ng, Tang-Tat. "Numerical Simulations of a Deployable Structure." In 10th Biennial International Conference on Engineering, Construction, and Operations in Challenging Environments and Second NASA/ARO/ASCE Workshop on Granular Materials in Lunar and Martian Exploration. Reston, VA: American Society of Civil Engineers, 2006. http://dx.doi.org/10.1061/40830(188)10.

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Bullock, S., and L. Peterson. "Nonlinear micron-level mechanics of a precision deployable space structure joint." In 37th Structure, Structural Dynamics and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1996. http://dx.doi.org/10.2514/6.1996-1333.

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Hachkowski, M., and L. Peterson. "Friction model of a revolute joint for a precision deployable spacecraft structure." In 37th Structure, Structural Dynamics and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1996. http://dx.doi.org/10.2514/6.1996-1331.

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Lake, Mark, Peter Warren, and Lee Peterson. "A revolute joint with linear load-displacement response for precision deployable structures." In 37th Structure, Structural Dynamics and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1996. http://dx.doi.org/10.2514/6.1996-1500.

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Tsunoda, Hiroaki, Ken-ichi Hariu, Yoichi Kawakami, Toshio Sugimoto, Mitsuteru Yamato, and Kazuo Miyoshi. "Evaluation of asynchronization in synchronous deployable space structure." In 39th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1998. http://dx.doi.org/10.2514/6.1998-1935.

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Footdale, Joseph, Jeremy Banik, and Thomas Murphey. "Design Developments of a Non-Planar Deployable Structure." In 51st AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
18th AIAA/ASME/AHS Adaptive Structures Conference
12th. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-2608.

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Reports on the topic "Deployable structure"

1

Richards, John, Melisa Nallar, Christina Rinaudo, Mary Margaret Mitchell, James Richards, Caitlin Callaghan, and Peter Larsen. RISC TAMER Framework : Resilient Installation Support Against Compound Threats Analysis and Mitigation for Equipment and Resources Framework. Engineer Research and Development Center (U.S.), January 2024. http://dx.doi.org/10.21079/11681/48073.

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Every day, decision-makers must allocate resources based on the best available information at the time. Military installations face a variety of threats which challenge sustained functionality of their supporting and supported deployable systems. Considering the compounding and interdependent impacts of the threats, both specified (what is known) and unspecified (what is not known) and the investments needed to address these threats adds value to the decision-making process. Current risk management practices are generally evaluated via scenario analyses that do not consider compound threats, resulting in limited risk management solutions. Current practices also challenge the ability of decision-makers to increase resilience against such threats. The Resilient Installation Support against Compound Threats Analysis and Mitigation for Equipment and Resources (RISC TAMER) Framework establishes a decision support structure to identify and categorize system components, compound threats and risks, and system relationships to provide decision-makers with more complete and comprehensive information from which to base resilience-related decisions, for prevention and response. This paper focuses on the development process for RISC TAMER framework to optimize resilience enhancements for a wide variety of deployable systems in order to implement resilience strategies to protect assets, to increase adaptability, and to support power projection and global operations.
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Crane Ill, Carl D. The Theoretical Analysis of Self-Deployable Tensegrity Structures. Fort Belvoir, VA: Defense Technical Information Center, February 2004. http://dx.doi.org/10.21236/ada424114.

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Bloxom, Andrew, Abel Medellin, Chris Vince, and Solomon Yim. Modeling & Testing of Inflatable Structures for Rapidly Deployable Port Infrastructures. Fort Belvoir, VA: Defense Technical Information Center, July 2010. http://dx.doi.org/10.21236/ada554336.

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Phlipot, Gregory. Prediction and Optimization of Truss Performance for Lightweight Intelligent Packaging and Deployable Structures. Office of Scientific and Technical Information (OSTI), August 2018. http://dx.doi.org/10.2172/1463955.

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Riley, Charles. Development of RDSETGO: A Rapidly Deployable Structural Evaluation Toolkit for Global Observation. Transportation Research and Education Center, March 2018. http://dx.doi.org/10.15760/trec.196.

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DESIGN OF THE DEPLOYABLE-FOLDABLE ACTUATOR AND VIBRATION CONTROL DEVICE BASED ON THE SHAPE MEMORY ALLOYS WITH A TWO-WAY EFFECT. The Hong Kong Institute of Steel Construction, August 2022. http://dx.doi.org/10.18057/icass2020.p.306.

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The paper aims at the design method of the space deployable-foldable actuator and vibration control device, and the selected material is the shape memory alloy. These devices can repeatedly adjust the deploy and fold states by changing the temperature, and also present a large energy dissipation to keep the stability of the structures in the vibration control. It can be observed that the fabricated two-way shape memory alloy actuator can present steady fold-deploy procedures more than five times, in which the recoverable rate is higher than 95.83%, and the required time in the complete deploying process is 15 s. Meanwhile, the vibration control device based on the shape memory alloys also gives an excellent performance, the lightweight device is only 315 g, and the vibration in the vertical direction can be limited to the millimeter-level (0.917 mm), it can also endure the repeated loadings in the applications and keep a good operating condition.
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