Journal articles: 'Large space deployable antennas'

1

Henriksen, T. K., and C. Mangenot. "Large deployable antennas." CEAS Space Journal 5, no. 3-4 (November 23, 2013): 87–88. http://dx.doi.org/10.1007/s12567-013-0055-4.

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He, Xing Xing, Ying Liao, and Ya Jun Yang. "Research on the Natural Frequency Prediction Method for Ring Tension Truss Deployable Antenna." Applied Mechanics and Materials 105-107 (September 2011): 2200–2203. http://dx.doi.org/10.4028/www.scientific.net/amm.105-107.2200.

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It is nearly impossible to carry out prototype experiments of large deployable space antennas because of their large dimensions. To solve this problem, a performance prediction approach is proposed in this paper. The prototype’s working performance is predicted by the scale model of the large deployable antenna. Based on this method, the natural frequency of the ring tension truss deployable antenna working in space is studied. The effect of the structural parameter distortion is taken into consideration by similarity criteria, and a similarity experimental formula of structural natural frequency is obtained. Four finite element models are established to validate the correction of the prediction method. The simulation results show that it’s valid for the prediction method to analyze the prototype in space, and it can be applied to promote the design, and performance prediction of the large deployable antennas.

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Lokman, Abdul Halim, Ping Jack Soh, Saidatul Norlyana Azemi, Herwansyah Lago, Symon K. Podilchak, Suramate Chalermwisutkul, Mohd Faizal Jamlos, Azremi Abdullah Al-Hadi, Prayoot Akkaraekthalin, and Steven Gao. "A Review of Antennas for Picosatellite Applications." International Journal of Antennas and Propagation 2017 (2017): 1–17. http://dx.doi.org/10.1155/2017/4940656.

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Cube Satellite (CubeSat) technology is an attractive emerging alternative to conventional satellites in radio astronomy, earth observation, weather forecasting, space research, and communications. Its size, however, poses a more challenging restriction on the circuitry and components as they are expected to be closely spaced and very power efficient. One of the main components that will require careful design for CubeSats is their antennas, as they are needed to be lightweight, small in size, and compact or deployable for larger antennas. This paper presents a review of antennas suitable for picosatellite applications. An overview of the applications of picosatellites will first be explained, prior to a discussion on their antenna requirements. Material and antenna topologies which have been used will be subsequently discussed prior to the presentation of several deployable configurations. Finally, a perspective and future research work on CubeSat antennas will be discussed in the conclusion.

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Cherniavsky, A. G., V. I. Gulyayev, V. V. Gaidaichuk, and A. I. Fedoseev. "Large Deployable Space Antennas Based on Usage of Polygonal Pantograph." Journal of Aerospace Engineering 18, no. 3 (July 2005): 139–45. http://dx.doi.org/10.1061/(asce)0893-1321(2005)18:3(139).

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5

Fanning, P., and L. Hollaway. "The Deployment Analysis of a Large Space Antenna." International Journal of Space Structures 8, no. 3 (September 1993): 209–20. http://dx.doi.org/10.1177/026635119300800307.

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The volume constraints imposed by current launch modules and the desirability of large reflectors and communication booms for space applications has given rise to active research in the field of deployable systems. These systems are stowed in a compact package for launch before being deployed into their operating configurations in orbit. A new concept for a deployable antenna is presented. The deployment of one such 5.0 m antenna is investigated. The antenna is deployed by a number of mechanical joints. The energy stored in these joints is quantified and the deployment times and stresses at ‘latch-up’ are predicted.

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6

Zheng, Fei, Mei Chen, Hai Ming Hao, and Jiu Li Zhang. "Deploying Analyses of Large Deployable Space Antenna under Gravity Environment." Advanced Materials Research 479-481 (February 2012): 2493–98. http://dx.doi.org/10.4028/www.scientific.net/amr.479-481.2493.

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The gravity is a serious problem for the deploying experiments of a large deployable space antenna on the ground. With the increasing trend for much bigger size deployable structures, new ground experiment methods with expected effects or with low cost should be explored. On this special object, we propose several deploying schemes from theoretical design, to practical design and then to actual design on a new folded hoop-rib mesh antenna structure we proposed before. Through the fundamental processes from theoretical analyses to actual experiments, it shows that the fairly complex mechanism can be deployed successfully, which reveals that the new deploying antenna structure design is feasible and reasonable.

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7

Ponomarev, Viktor S., Alexander V. Gerasimov, and Sergey V. Ponomarev. "Thermomechanical analysis of large deployable space reflector antenna." MATEC Web of Conferences 23 (2015): 01059. http://dx.doi.org/10.1051/matecconf/20152301059.

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8

Harada, Satoshi, Satoru Ozawa, Akira Meguro, and Mitsunobu Watanabe. "A shape analysis of membrane and cable structures for large space deployable antennas." Proceedings of the Space Engineering Conference 2003.11 (2003): 49–52. http://dx.doi.org/10.1299/jsmesec.2003.11.49.

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9

Zheng, Fei, Jie He, and Pan Zhang. "Simulating evaluation of new space deployable antenna." Aircraft Engineering and Aerospace Technology 88, no. 6 (October 3, 2016): 835–45. http://dx.doi.org/10.1108/aeat-08-2014-0123.

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Purpose The purpose of this paper is to build a new deployable antenna with folded scissors ribs and to evaluate the reasonable characteristics of this new structure. Design/methodology/approach Based on the TerrStar-1 satellite, virtual design and shapes forming are considered in this paper with the structure design of the new antenna. Considering the relaxation units in net surface, form-finding evaluation is used to build mathematical model and operate the optimization algorithm so that the design of the new antenna with folded scissors ribs is achieved. Simulations are carried out to verify the antenna proposed. Findings It is found that the antenna with folded scissors ribs can be developed smoothly in the space. Practical implications The proposed the antenna with folded scissors ribs can be considered as a fall-back alternative for large antenna, with a diameter of over 10 m in the space, or is seen as another option for the system with a simple rigid structure. Originality/value Different from traditional antenna, it provides a valuable reference for the further research of large deployable antenna in space. The antenna in this paper is able to develop more than 30 m of diameter. Meanwhile, the surface density and the natural frequency and the root-mean-square error in surface are superior to those of the traditional antenna.

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10

Chen, Mei, Fei Zheng, and Yuan Yuan Zhang. "Virtual Surface Measurement of Large Deployable Space Antenna Structure." Advanced Materials Research 479-481 (February 2012): 2586–92. http://dx.doi.org/10.4028/www.scientific.net/amr.479-481.2586.

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Virtual surface measurement is necessary to assist the actual measurement of large deployable space antenna structure. To realize a virtual surface measurement on this kind of structures, we take several steps to get the virtual measurement images. A virtual 3D model of the antenna structure and virtual hung system are constructed; virtual measure rules, coded marks and uncoded marks are also built up. The pinhole camera model is used to simulate the actual photogrammetric measurement tools. Through examples with OpenCV tools, the virtual measurement method is verified to be reasonable. Then different resolution images of perspective projections of the virtual measurement in virtual camera positions and orientations are obtained. Proper selections of the camera resolution and proper positions and orientations of the camera are found through virtual measurement experiments. Such results can be used in an actual photogrammetric measurement. The virtual measurement method can be used to reduce the attempt times and to assist the actual measurement with available photogrammetric measurement tools.

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11

Qi, Xiaozhi, Hailin Huang, Bing Li, and Zongquan Deng. "A large ring deployable mechanism for space satellite antenna." Aerospace Science and Technology 58 (November 2016): 498–510. http://dx.doi.org/10.1016/j.ast.2016.09.014.

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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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13

Zheng, Fei, and Mei Chen. "New Conceptual Structure Design for Affordable Space Large Deployable Antenna." IEEE Transactions on Antennas and Propagation 63, no. 4 (April 2015): 1351–58. http://dx.doi.org/10.1109/tap.2015.2404345.

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14

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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15

Zhou, Yi Jun, Fu Ling Guan, and Li Feng Qian. "The Application of Shape Memory Polymer Composite in Space Deployable Truss Structure." Advanced Materials Research 287-290 (July 2011): 2756–59. http://dx.doi.org/10.4028/www.scientific.net/amr.287-290.2756.

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In this paper, the advantages of smart materials and structures are introduced. Because of the influence of friction, it’s difficult to deploy the large ring truss antenna driving by cable. The SPMC hinge is added in the deployable joint, the deployable antenna is deployed by heating the material to cause recovery strain, which substitutes for the driving by cable. Describe the behavior of SPMC material, and do the simulation, from the analysis results, we can aim that the stress of SPMC satisfies the yielding stress when the node is furled. At the same time, the force to expand the antenna caused by heating SPMC is also obtained. Compared the different size of width, the variation of recovery force can be got.

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EBISUI, Takashi, Akio ISO, Teruaki ORIKASA, Toshio SUGIMOTO, Teruki OKAMOTO, and Miyoshi UENO. "Characteristics of Scale Models of Large Deployable Mesh Reflector Antennas and Study on Space Verification Test Plan." Journal of the Japan Society for Aeronautical and Space Sciences 40, no. 467 (1992): 667–73. http://dx.doi.org/10.2322/jjsass1969.40.667.

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17

Li, Yanyong, Juanfang Wei, and Lu Dai. "Structural design and dynamic analysis of new ultra-large planar deployable antennas in space with locking systems." Aerospace Science and Technology 106 (November 2020): 106082. http://dx.doi.org/10.1016/j.ast.2020.106082.

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Guo, Wei, Yunhua Li, Yun-Ze Li, Shaoping Tian, and Shengnan Wang. "Thermal–structural analysis of large deployable space antenna under extreme heat loads." Journal of Thermal Stresses 39, no. 8 (June 17, 2016): 887–905. http://dx.doi.org/10.1080/01495739.2016.1189776.

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19

Meshkovsky, V. Ye, A. N. Sdobnikov, and Yu A. Kisanov. "An approach to design of large-sized deployable hoop space antenna reflector." Journal of Physics: Conference Series 1902, no. 1 (May 1, 2021): 012125. http://dx.doi.org/10.1088/1742-6596/1902/1/012125.

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20

Sheth, Dhwanil, Hemant Arora, Shashikant Joshi, B. S. Munjal, and Dhaval B. Shah. "Investigation on design methods for cable mesh configuration of deployable space antenna reflector." International Journal of Space Structures 35, no. 4 (September 30, 2020): 126–34. http://dx.doi.org/10.1177/0956059920960305.

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Mesh reflectors are always a preferable option for large size deployable antenna reflector over solid surface reflectors due to their flexibility of adjustment in minimum possible space and ability to get deployed to full configuration in space. Maintaining surface properties and accuracy are two important requirements in the design of the mesh reflector for the performance of cable network antenna reflectors. The present work considers the various design approaches for cable mesh configuration of space deployable antenna reflectors. The equal force density shape forming criteria such is applied for obtaining the desired parabolic curvature of the mesh configuration. The ring structure for the deployable mechanism is considered as rigid linkages for designing mesh configuration. A generalized numbering scheme for nodes and cable mesh link is formulated for carrying forward various shapes forming criteria which help in making an algorithm. The algorithm for a better understanding of these methods is developed using MATLAB with nodal coordinates and its connection. Mesh configuration is developed with a different number of divisions. A study is also carried out for finding the required number of divisions for a highly accurate parabolic profile for a particular band frequency. A demonstration model is developed and a comparison of the coordinates of the prototype is made with those arrived at using the model.

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21

Sun, Zihan, Yiqun Zhang, and Dongwu Yang. "Structural design, analysis, and experimental verification of an H-style deployable mechanism for large space-borne mesh antennas." Acta Astronautica 178 (January 2021): 481–98. http://dx.doi.org/10.1016/j.actaastro.2020.09.032.

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22

Fraux, V., M. Lawton, J. R. Reveles, and Z. You. "Novel large deployable antenna backing structure concepts for foldable reflectors." CEAS Space Journal 5, no. 3-4 (August 10, 2013): 195–201. http://dx.doi.org/10.1007/s12567-013-0046-5.

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23

Zheng, Tao, Zheng Fei, Xi Rui, and Lide Yan. "A Novel Space Large Deployable Paraboloid Structure with Power and Communication Integration." International Journal of Antennas and Propagation 2019 (November 13, 2019): 1–17. http://dx.doi.org/10.1155/2019/3980947.

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The combination of a solar array and a communication antenna can reduce the entire mass, physical size, and cost in space applications. Currently, related studies mainly focus on the combination of the two structures on the one flat plate structure (FPS). Compared with the FPS, a paraboloid structure has a lower surface density and higher conversion efficiency. Therefore, a novel space large deployable paraboloid structure with power and communication integration (SSPCI) is proposed and designed in detail, for spacecraft on a sun synchronous earth orbit; it consists of a cable mesh membrane reflector (CMMR), an energy conversion device (ECD), and a three-extensible-rod (TER) pointing mechanism. To achieve the goal of integrating power and communication, the TER pointing mechanism drives the CMMR/ECD to track the sun in the sunshine region or to turn to face the ground station/other target in the Earth’s shadow region. Then, through simulation analyses of the deploying process, static force at a limit orientation, and sun tracking process of the SSPCI, it is proved that the SSPCI is feasible and has satisfactory performance. Finally, deploying experiments of the folded hoop of the CMMR and sun tracking experiments of the TER pointing mechanism on the ground were carried out successfully, which proves that the folded hoop can be deployed successfully with fairly high deploying dependability, and the TER pointing mechanism is feasible for the SSPCI from the mechanism principle and the control mode in space applications indirectly. Moreover, the tracking accuracy of the TER pointing mechanism is estimated to be within ±0.4° although the machining precision of its components is not high.

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24

Hu, Fei, Yanping Song, Yundou Xu, and Huaizhou Wen. "Synthesis and optimization of modular deployable truss antenna reflector." Aircraft Engineering and Aerospace Technology 90, no. 8 (November 5, 2018): 1288–94. http://dx.doi.org/10.1108/aeat-11-2017-0234.

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Purpose This paper aims to synthesize a modular deployable truss antenna with the lower degree of freedom (DOF) and larger folding ratio. Because of the advantages of this kind of new truss antenna, the modules that make up the antenna can be deployed together by the synchronous motor drivers instead of twist springs to realize the controllable deployment. Design/methodology/approach The closed-loop branch equivalence method is proposed to synthesize the single DOF module and the large deployable reflector. The complex mechanism can be equivalently replaced by a simpler mechanism based on screw theory. The motion pairs are synthesized and optimized to make the curved surface achieve to the maximum folding ratio when the modular parabolic truss antenna is folded. Findings The results show that the 3(3RR-3RRR)-3RRR-3RRR planar module is a single DOF mechanism. Additionally, the adjacent parts of every two modules are connected with universal joints to obtain the new truss antenna when the modules are networked. Practical implications The configuration of this new modular deployable truss antenna can be synthesized to design the structure, and the proposed method can be applied to other space multi-loop coupling mechanism and other spacecraft. Originality/value This paper presents an approach to synthesizing the motion pairs, as well as the DOF analysis. The results lay a foundation for the further analysis of the deployable control and dynamics of this kind of antenna. And the new modular truss antenna has a practical application in aerospace engineering.

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Datashvili, L., S. Endler, B. Wei, H. Baier, H. Langer, M. Friemel, N. Tsignadze, and J. Santiago-Prowald. "Study of mechanical architectures of large deployable space antenna apertures: from design to tests." CEAS Space Journal 5, no. 3-4 (October 31, 2013): 169–84. http://dx.doi.org/10.1007/s12567-013-0050-9.

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Liu, Likun, Jinjun Shan, and Yan Zhang. "Dynamics Modeling and Analysis of Spacecraft with Large Deployable Hoop-Truss Antenna." Journal of Spacecraft and Rockets 53, no. 3 (May 2016): 471–79. http://dx.doi.org/10.2514/1.a33464.

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27

Tsunoda, H., K. Nakajima, and A. Miyasaka. "Thermal design verification of a large deployable antenna for a communications satellite." Journal of Spacecraft and Rockets 29, no. 2 (March 1992): 271–78. http://dx.doi.org/10.2514/3.26345.

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28

Shoji, Kaori, Daigoro Isobe, and Motofumi Usui. "Numerical investigations to suppress thermal deformation of the large deployable reflector during earth eclipse in space." Aeronautical Journal 121, no. 1241 (May 17, 2017): 970–82. http://dx.doi.org/10.1017/aer.2017.33.

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ABSTRACTIn space, structures encounter various severe environments, including severe thermal conditions. The signal level of the radio wave from the Large Deployable Reflector (LDR) mounted on the Engineering Test Satellite-VIII (ETS-VIII) was observed to change during an Earth eclipse. This phenomenon was assumed to be caused by the thermal deformation of the LDR. Therefore, in this study, a means to suppress the thermal deformation is proposed and demonstrated by focusing on the internal force generated at the springs used to deploy the antenna. According to the numerical results obtained from finite element analyses, the thermal deformations at all apices that support the reflectors were suppressed at a high correction rate by adjusting the coefficients of thermal expansion in the structural members and by controlling spring forces differently in four areas depending on the distances from the constraint point.

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Wu, R. Q., W. Zhang, and K. Behdinan. "Vibration Frequency Analysis of Beam–Ring Structure for Circular Deployable Truss Antenna." International Journal of Structural Stability and Dynamics 19, no. 02 (February 2019): 1950012. http://dx.doi.org/10.1142/s0219455419500123.

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The circular truss antenna of the large aperture is considered to be a flexible structure which may cause vibration in space and may affect its performance. The frequency analysis of the circular truss antenna is an important problem for understanding its vibration mechanism. In this paper, we investigate the frequency characteristics of a beam–ring structure which is proposed for the first time to model the circular truss antenna in the case of the antenna expended and locked. Based on describing the displacements of the beam–ring system in detail, the kinetic energy and potential energy are calculated. The partial differential governing equations of motion and boundary conditions for the beam–ring structure are derived by Hamilton principle. From the linear parts of the governing equations of motion and the corresponding boundary conditions, the linear frequencies of the beam–ring structure are theoretically obtained. The effects of the physical parameters on the frequency characteristics of the beam–ring structure are studied, which are further verified by the numerical results. The finding phenomena of this paper are helpful for designing and controlling the beam–ring structure such as the circular truss antenna.

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30

Lin, Guo Chang, Hui Feng Tan, and Xiang Hong Bai. "Deformation Measurement of an Inflatable Reflector Using Digital Image Correlation." Applied Mechanics and Materials 66-68 (July 2011): 822–26. http://dx.doi.org/10.4028/www.scientific.net/amm.66-68.822.

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Inflatable antenna is a potential technique for large space deployable antenna and knowing its reflector’s deformation behavior is quite important for its accuracy improvement. A 1.5m-diameter inflatable reflector’s deformations at different internal pressures are studied using digital image correlation(DIC) in the paper. Because of the symmetry of the reflector, only two representative gores on the reflector are chosen to study. During the digital image correlation measurement, some article random dot patterns are drawn on the reflector’s surface. The 2D and 3D displacement maps of the reflector at different internal pressures are gained by DIC measurement and the cross-section of one gore of the reflector according to the internal pressure are analyzed from the measurement results.

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31

Ma, Hongcai, Guang Jin, Xing Zhong, Kai Xu, and Yanjie Li. "Optical Design of a Solar Dish Concentrator Based on Triangular Membrane Facets." International Journal of Photoenergy 2012 (2012): 1–5. http://dx.doi.org/10.1155/2012/391921.

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The design of a solar dish concentrator is proposed based on triangular membrane facets for space power applications. The facet concentrator approximates a parabolic surface supported by a deployable perimeter truss structure, which originates from a large aperture space antenna. For optimizing the number of facets rows and focal-diameter ratio of the concentrator, Monte Carlo ray-tracing method is utilized to determine optical performance of the concentrator, and the system root-mean-square (RMS) deviation is considered in this design procedure. A 600-facet concentrator with focal-diameter ratio of 1.1 will achieve 83.63% of radiative collection efficiency over a 15 cm radius disk located in the focal plane, with a mean solar concentration ratio exceeding 300. The study in this paper is helpful for the development of the membrane facet concentrator.

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Akioka, M., T. Orikasa, M. Satoh, A. Miura, H. Tsuji, M. Toyoshima, and Y. Fujino. "APPLICATION OF VISION METROLOGY TO IN-ORBIT MEASUREMENT OF LARGE REFLECTOR ONBOARD COMMUNICATION SATELLITE FOR NEXT GENERATION MOBILE SATELLITE COMMUNICATION." ISPRS - International Archives of the Photogrammetry, Remote Sensing and Spatial Information Sciences XLI-B5 (June 15, 2016): 3–6. http://dx.doi.org/10.5194/isprs-archives-xli-b5-3-2016.

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Satellite for next generation mobile satellite communication service with small personal terminal requires onboard antenna with very large aperture reflector larger than twenty meters diameter because small personal terminal with lower power consumption in ground base requires the large onboard reflector with high antenna gain. But, large deployable antenna will deform in orbit because the antenna is not a solid dish but the flexible structure with fine cable and mesh supported by truss. Deformation of reflector shape deteriorate the antenna performance and quality and stability of communication service. However, in case of digital beam forming antenna with phased array can modify the antenna beam performance due to adjustment of excitation amplitude and excitation phase. If we can measure the reflector shape precisely in orbit, beam pattern and antenna performance can be compensated with the updated excitation amplitude and excitation phase parameters optimized for the reflector shape measured every moment. Softbank Corporation and National Institute of Information and Communications Technology has started the project "R&D on dynamic beam control technique for next generation mobile communication satellite" as a contracted research project sponsored by Ministry of Internal Affairs and Communication of Japan. In this topic, one of the problem in vision metrology application is a strong constraints on geometry for camera arrangement on satellite bus with very limited space. On satellite in orbit, we cannot take many images from many different directions as ordinary vision metrology measurement and the available area for camera positioning is quite limited. Feasibility of vision metrology application and general methodology to apply to future mobile satellite communication satellite is to be found. Our approach is as follows: 1) Development of prototyping simulator to evaluate the expected precision for network design in zero order and first order 2) Trial measurement for large structure with similar dimension with large deployable reflector to confirm the validity of the network design and instrumentation. In this report, the overview of this R&D project and the results of feasibility study of network design based on simulations on vision metrology and beam pattern compensation of antenna with very large reflector in orbit is discussed. The feasibility of assumed network design for vision metrology and satisfaction of accuracy requirements are discussed. The feasibility of beam pattern compensation by using accurately measured reflector shape is confirmed with antenna pattern simulation for deformed parabola reflector. If reflector surface of communication satellite can be measured routinely in orbit, the antenna pattern can be compensated and maintain the high performance every moment.

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Kamegai, Kazuhisa, and Masato Tsuboi. "Measurements of an Antenna Surface for a Millimeter-Wave Space Radio Telescope. II. Metal Mesh Surface for Large Deployable Reflector." Publications of the Astronomical Society of Japan 65, no. 1 (February 25, 2013): 21. http://dx.doi.org/10.1093/pasj/65.1.21.

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Siriguleng, B., W. Zhang, T. Liu, and Y. Z. Liu. "Vibration modal experiments and modal interactions of a large space deployable antenna with carbon fiber material and ring-truss structure." Engineering Structures 207 (March 2020): 109932. http://dx.doi.org/10.1016/j.engstruct.2019.109932.

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Dong, Bo, Han Zhang, Yiqun Zhang, and Na Li. "Geometry Modeling of Truss Structure for a Space Deployable Parabolic Cylindrical Antenna." MATEC Web of Conferences 256 (2019): 05006. http://dx.doi.org/10.1051/matecconf/201925605006.

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To meet the requirements for larger aperture and high storage rate deployable antenna in the space missions, a geometry modeling design scheme for parabolic cylindrical antenna was proposed based on module connection. The scheme raised in this paper realized geometry modeling for different aperture of antenna utilizing several kinds of modules. According to the shape feature of mesh surface of the parabolic cylindrical antenna, the schematic design for module division was carried out in the parabolic direction and baseline. The number of modules and the size of links were calculated meanwhile. The validity of the scheme was proved by numerical analysis for the deployable process.

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Liu, T., W. Zhang, Y. Zheng, and Y. F. Zhang. "Andronov-Hopf bifurcations, Pomeau-Manneville intermittent chaos and nonlinear vibrations of large deployable space antenna subjected to thermal load and radial pre-stretched membranes with 1:3 internal resonance." Chaos, Solitons & Fractals 144 (March 2021): 110719. http://dx.doi.org/10.1016/j.chaos.2021.110719.

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37

SENBOKUYA, Yumi, and Hiroaki TSUNODA. "Modular Configuration Method of Large Deployable Antennas." Journal of the Japan Society for Aeronautical and Space Sciences 48, no. 560 (2000): 273–76. http://dx.doi.org/10.2322/jjsass.48.273.

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38

Tang, Yaqiong, Tuanjie Li, Zuowei Wang, and Hanqing Deng. "Surface accuracy analysis of large deployable antennas." Acta Astronautica 104, no. 1 (November 2014): 125–33. http://dx.doi.org/10.1016/j.actaastro.2014.07.029.

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39

You, Z. "Deployable Structure of Curved Profile for Space Antennas." Journal of Aerospace Engineering 13, no. 4 (October 2000): 139–43. http://dx.doi.org/10.1061/(asce)0893-1321(2000)13:4(139).

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40

Rogers, C. A., W. L. Stutzman, T. G. Campbell, and J. M. Hedgepeth. "Technology Assessment and Development of Large Deployable Antennas." Journal of Aerospace Engineering 6, no. 1 (January 1993): 34–54. http://dx.doi.org/10.1061/(asce)0893-1321(1993)6:1(34).

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DUAN, Baoyan. "Large Spaceborne Deployable Antennas (LSDAs) -A Comprehensive Summary." Chinese Journal of Electronics 29, no. 1 (January 1, 2020): 1–15. http://dx.doi.org/10.1049/cje.2019.09.001.

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42

Zhang, Yiqun, Baoyan Duan, and Tuanjie Li. "A controlled deployment method for flexible deployable space antennas." Acta Astronautica 81, no. 1 (December 2012): 19–29. http://dx.doi.org/10.1016/j.actaastro.2012.05.033.

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Li, Tuanjie, and Yao Wang. "Performance relationships between ground model and space prototype of deployable space antennas." Acta Astronautica 65, no. 9-10 (November 2009): 1383–92. http://dx.doi.org/10.1016/j.actaastro.2009.03.037.

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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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45

Hanayama, Eiji, Shinsuke Araki, and Tadashi Takano. "Measurement of a mesh reflecting surface for large deployable antennas." Electronics and Communications in Japan (Part I: Communications) 77, no. 1 (January 1994): 95–105. http://dx.doi.org/10.1002/ecja.4410770110.

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46

Yang, Guigeng, Baoyan Duan, Jingli Du, and Yiqun Zhang. "Shape pre-adjustment of deployable mesh antennas considering space thermal loads." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, no. 1 (November 25, 2016): 143–55. http://dx.doi.org/10.1177/0954410016678432.

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Abstract:

On-orbit space deployable antennas withstand periodic thermal loads, which will degrade the antenna surface accuracy. Thus, it is necessary to preliminarily adjust the antenna before launch to make it adapt to the space temperature environment as much as possible. Aiming at this problem, a pre-adjustment method based on min-max concept is presented in this study. First, according to the force equilibrium equation of the cable element, the incremental equilibrium equation of the cable mesh antenna is derived, and the incremental expressions of the reflector's surface displacement and cable tension with respect to cable length variation and element temperature variation are also developed. Then, the optimization model for shape pre-adjustment is established using min-max method, and the pre-adjustment process is implemented by sequence planning strategy. Finally, an AstroMesh antenna is employed to demonstrate the validity of the method.

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47

Misawa, Masayoshi, and Yoshiaki Ohkami. "Stiffness Design of Deployable Satellite Antennas in Deployed Configuration." Journal of Spacecraft and Rockets 35, no. 3 (May 1998): 380–86. http://dx.doi.org/10.2514/2.3339.

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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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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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Wang, Yan, Rongqiang Liu, Hui Yang, Qiang Cong, and Hongwei Guo. "Design and Deployment Analysis of Modular Deployable Structure for Large Antennas." Journal of Spacecraft and Rockets 52, no. 4 (July 2015): 1101–11. http://dx.doi.org/10.2514/1.a33127.

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Journal articles on the topic 'Large space deployable antennas'

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