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Journal articles on the topic 'Deployable boom'

Author: Grafiati

Published: 4 June 2021

Last updated: 28 January 2023

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1

Iuvshin, A. M., Y. S. Andreev, and S. D. Tretyakov. "Development of Forming Method of Deployable Boom from Thermoplastic Polymer Composite." Key Engineering Materials 887 (May 2021): 105–9. http://dx.doi.org/10.4028/www.scientific.net/kem.887.105.

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This paper studies deployable elements which are used in satellites and different terrestrial antenna devices. Many deployable elements are made from steel or thermoset polymer composite materials and have the following disadvantages like length limitation of deployable elements, labour intensity of manufacturing process of deployable elements etc. For this purpose a deployable tube boom element was chosen and a forming method for manufacturing deployable tube element from thermoplastic polymer composite material was developed.

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2

Yang, Hui, Shuoshuo Fan, Yan Wang, and Chuang Shi. "Novel Four-Cell Lenticular Honeycomb Deployable Boom with Enhanced Stiffness." Materials 15, no. 1 (2022): 306. http://dx.doi.org/10.3390/ma15010306.

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Composite thin-walled booms can easily be folded and self-deployed by releasing stored strain energy. Thus, such booms can be used to deploy antennas, solar sails, and optical telescopes. In the present work, a new four-cell lenticular honeycomb deployable (FLHD) boom is proposed, and the relevant parameters are optimized. Coiling dynamics analysis of the FLHD boom under a pure bending load is performed using nonlinear explicit dynamics analysis, and the coiling simulation is divided into three consecutive steps, namely, the flattening step, the holding step, and the hub coiling step. An optim

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3

Chen, Manming, Zonghao Pan, Tielong Zhang, et al. "Deployable boom for Mars Orbiter Magnetometer onboard Tianwen-1." JUSTC 52, no. 5 (2022): 7. http://dx.doi.org/10.52396/justc-2022-0001.

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A more than 3 m-long deployable boom is an essential component of the Mars Orbiter Magnetometer (MOMAG) onboard the orbiter of Tianwen-1. The boom was developed to place fluxgate magnetometer (FGM) sensors away from the satellite to reduce the influence of the satellite magnetic field. It was designed as an articulated spring-driven deployable mechanism for single-shot deployment. Functionality, reliability and system constraints are fully considered in the boom design. Mechanical analyses and proof tests show that the boom has sufficient safety margin to withstand environmental conditions, ev

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4

Chen, Manming, Zonghao Pan, Tielong Zhang, et al. "Deployable boom for Mars Orbiter Magnetometer onboard “Tianwen-1”." JUSTC 52, no. 3 (2022): 1. http://dx.doi.org/10.52396/justc-2021-0001.

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A more than 3-m long deployable boom is an essential component of the Mars Orbiter Magnetometer (MOMAG) onboard the orbiter of “Tianwen-1”. The boom was developed to place fluxgate magnetometer (FGM) sensors away from the satellite to reduce the influence of the satellite magnetic field. It was designed as an articulated spring-driven deployable mechanism for single-shot deployment. Functionality, reliability and system constraints are fully considered in the boom design. Mechanical analyses and proof tests show that the boom has sufficient safety margin to withstand environmental conditions,

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5

Silver, Mark J., Lee D. Peterson, and Lisa M. R. Hardaway. "Experimental Measurement of Picometer Scale Spontaneous Vibrations in a Precision Deployable Boom under Thermal Loading." Shock and Vibration 14, no. 2 (2007): 133–49. http://dx.doi.org/10.1155/2007/393578.

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This paper reports observations and analysis of picometer scale spontaneous vibrations in a precision deployable boom under thermal loading. The structural test article is a deployable boom previously flown in space. It exhibited spontaneous vibrations during the temperature rise following a night to day transition on orbit. In an attempt to reproduce the spontaneous vibrations on the ground, the test article was thermally loaded within a mechanically stabilized test environment. Spontaneous vibrations were induced in these ground experiments. The vibrations were at a scale of motion for which

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6

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

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7

Bai, Jiang-Bo, Di Chen, Jun-Jiang Xiong, and R. Ajit Shenoi. "Folding analysis for thin-walled deployable composite boom." Acta Astronautica 159 (June 2019): 622–36. http://dx.doi.org/10.1016/j.actaastro.2019.02.014.

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8

Kim, Sang Ki, and Jae Young Kang. "Deployable Carbon-Fiber-Reinforced Polymer Boom with Bi-stability." Transactions of the Korean Society of Mechanical Engineers - A 45, no. 6 (2021): 465–71. http://dx.doi.org/10.3795/ksme-a.2021.45.6.465.

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9

Chu, ZhongYi, and YiAn Lei. "Design theory and dynamic analysis of a deployable boom." Mechanism and Machine Theory 71 (January 2014): 126–41. http://dx.doi.org/10.1016/j.mechmachtheory.2013.09.009.

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10

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

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11

Stabile, A., and S. Laurenzi. "Coiling dynamic analysis of thin-walled composite deployable boom." Composite Structures 113 (July 2014): 429–36. http://dx.doi.org/10.1016/j.compstruct.2014.03.043.

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12

Nakajima, A., M. Abe, Y. Nishio, and H. Yahagi. "Space experiments of deployable boom and umbrella test satellite (DEBUT)." Acta Astronautica 25, no. 12 (1991): 765–73. http://dx.doi.org/10.1016/0094-5765(91)90055-a.

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13

Wang, Li-Wu, Jiang-Bo Bai, and Yan Shi. "Simplified Analytical Model for Predicting Neutral Cross-Section Position of Lenticular Deployable Composite Boom in Tensile Deformation." Materials 14, no. 24 (2021): 7809. http://dx.doi.org/10.3390/ma14247809.

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Foldable and deployable flexible composite thin-walled structures have the characteristics of light weight, excellent mechanical properties and large deformation ability, which means they have good application prospects in the aerospace field. In this paper, a simplified theoretical model for predicting the position of the neutral section of a lenticular deployable composite boom (DCB) in tensile deformation is proposed. The three-dimensional lenticular DCB is simplified as a two-dimensional spring system and a rigid rod, distributed in parallel along the length direction. The position of the

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14

FAN, Shuo-shuo. "Optimization of single lenticular honeycomb boom for optical film deployable mechanism." Optics and Precision Engineering 28, no. 10 (2020): 2244–51. http://dx.doi.org/10.37188/ope.20202810.2244.

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15

Dolkens, Dennis, Hans Kuiper, and Victor Villalba Corbacho. "The deployable telescope: a cutting-edge solution for high spatial and temporal resolved Earth observation." Advanced Optical Technologies 7, no. 6 (2018): 365–76. http://dx.doi.org/10.1515/aot-2018-0043.

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Abstract The increase of spatial and temporal resolution for Earth observation (EO) is the ultimate driver for science and societal applications. However, the state-of-the-art EO missions like DigitalGlobe’s Worldview-3, are very costly. Moreover, this system has a high mass of 2800 kg and limited swath width of about 15 km which limits the temporal resolution. In this article, we present the status of the deployable space telescope (DST) project, which has been running for 6 years now at the Delft University of Technology, as a cutting-edge solution to solve this issue. Deployable optics have

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16

Mansourinejad, H., M. Sharavi, and K. Daneshjoo. "Design and Analysis of Oscillation-Decreasing Mechanism on the Deployable Composite Boom." Journal of Spacecraft and Rockets 52, no. 4 (2015): 1091–100. http://dx.doi.org/10.2514/1.a33252.

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17

FURUYA, Hiroshi, Yasutaka SATOU, Moto TAKAI, Hiraku SAKAMOTO, and Nobukatsu OKUIZUMI. "S1910202 Development of Boom-Membrane Deployable Space Structures for De-orbiting Satellites." Proceedings of Mechanical Engineering Congress, Japan 2015 (2015): _S1910202——_S1910202—. http://dx.doi.org/10.1299/jsmemecj.2015._s1910202-.

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18

Bai, J. B., R. A. Shenoi, and J. J. Xiong. "Thermal analysis of thin-walled deployable composite boom in simulated space environment." Composite Structures 173 (August 2017): 210–18. http://dx.doi.org/10.1016/j.compstruct.2017.04.022.

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19

Laurenzi, Susanna, Damiano Rufo, Marco Sabatini, Paolo Gasbarri, and Giovanni B. Palmerini. "Characterization of deployable ultrathin composite boom for microsatellites excited by attitude maneuvers." Composite Structures 220 (July 2019): 502–9. http://dx.doi.org/10.1016/j.compstruct.2019.04.003.

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20

Sakamoto, Hiraku, Hiroshi Furuya, Yasutaka Satou, and M. C. Natori. "P08 Development of Deployable Membrane Space Structures Enabling Boom-Membrane Stowed Together." Proceedings of the Space Engineering Conference 2013.22 (2013): _P08–1_. http://dx.doi.org/10.1299/jsmesec.2013.22._p08-1_.

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21

OKADA, Hideaki, Hiroshi FURUYA, and Akihito WATANABE. "Development of Retractable and Deployable CFRP Boom Mechanisms with Corrugated Closed Section." Proceedings of the Space Engineering Conference 2018.28 (2018): 2A2. http://dx.doi.org/10.1299/jsmesec.2018.28.2a2.

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22

Wei, Jianzheng, Huifeng Tan, Weizhi Wang, and Xu Cao. "Deployable dynamic analysis and on-orbit experiment for inflatable gravity-gradient boom." Advances in Space Research 55, no. 2 (2015): 639–46. http://dx.doi.org/10.1016/j.asr.2014.10.024.

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23

Wang, Sicong, Mark Schenk, Hongwei Guo, and Andrew Viquerat. "Tip force and pressure distribution analysis of a deployable boom during blossoming." International Journal of Solids and Structures 193-194 (June 2020): 141–51. http://dx.doi.org/10.1016/j.ijsolstr.2020.01.026.

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24

Takao, Yuki, Osamu Mori, and Jun’ichiro Kawaguchi. "Analysis and design of a spacecraft docking system using a deployable boom." Acta Astronautica 179 (February 2021): 172–85. http://dx.doi.org/10.1016/j.actaastro.2020.10.031.

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25

FURUYA, Hiroshi, Takashi YOKOMATSU, and Kyohei YASHIMA. "Gravity Compensation Systems for Ground Testing of Boom/Membrane Integrated Space Deployable Structures." Proceedings of Mechanical Engineering Congress, Japan 2016 (2016): G1900101. http://dx.doi.org/10.1299/jsmemecj.2016.g1900101.

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26

Chu, ZhongYi, YiAn Lei, and Dan Li. "Dynamics and robust adaptive control of a deployable boom for a space probe." Acta Astronautica 97 (April 2014): 138–50. http://dx.doi.org/10.1016/j.actaastro.2014.01.009.

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27

Kim, Sang Ki, Youn Sic Nam, and Jae Young Kang. "Theoretical Calculation of the Packaging Diameter and Transient Region Length of a Deployable CFRP Boom." Transactions of the Korean Society of Mechanical Engineers - A 45, no. 12 (2021): 1185–92. http://dx.doi.org/10.3795/ksme-a.2021.45.12.1185.

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28

SHIMA, Takeya, Hidekazu TANAKA, Hiroo YONECHI, et al. "Boom Deployment Angle Estimation and On-orbit Operation Results of ETS-VIII Large Deployable Reflectors." TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN 7, ists26 (2009): Pd_75—Pd_80. http://dx.doi.org/10.2322/tstj.7.pd_75.

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29

Yang, Hui, Hongwei Guo, Rongqiang Liu, Sicong Wang, and Yongbin Liu. "Coiling and deploying dynamic optimization of a C-cross section thin-walled composite deployable boom." Structural and Multidisciplinary Optimization 61, no. 4 (2019): 1731–38. http://dx.doi.org/10.1007/s00158-019-02429-x.

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30

Yang, Hui, Hongwei Guo, Yan Wang, Jian Feng, and Dake Tian. "Analytical solution of the peak bending moment of an M boom for membrane deployable structures." International Journal of Solids and Structures 206 (December 2020): 236–46. http://dx.doi.org/10.1016/j.ijsolstr.2020.09.005.

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31

Li, Zhanhua, Jingtao Han, Yufeng Zhang, Ruilong Lu, and Yong Yang. "Research on forming and mechanical properties for one dimensional linear deployable boom Stacer of spacecraft." Materials Today Communications 34 (March 2023): 105444. http://dx.doi.org/10.1016/j.mtcomm.2023.105444.

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32

Chu, ZhongYi, Jian Hu, ShaoBo Yan, and Miao Zhou. "Experiment on the retraction/deployment of an active–passive composited driving deployable boom for space probes." Mechanism and Machine Theory 92 (October 2015): 436–46. http://dx.doi.org/10.1016/j.mechmachtheory.2015.06.010.

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33

Li, Bingyan, Yuxuan Liu, Rongqiang Liu, et al. "Modeling and Analysis of a Large-Scale Double-Level Guyed Mast for Membrane Antennas." Mathematical Problems in Engineering 2020 (November 25, 2020): 1–16. http://dx.doi.org/10.1155/2020/3614625.

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This paper proposes a double-level guyed membrane antenna for stiffness improvement of a large-scale tri-prism deployable mast using the collapsible tubular mast (CTM). Initially, the construction of the antenna and the modeling of the CTM boom are illustrated. Afterwards, the central mast with isosceles triangular cross section is mathematically equivalent to a continuum beam, in which the equations of motion and the constitutive relations are derived. Based on the equivalent central beam, the double-level guyed mast for the membrane antenna is modeled as a 2(3-SPS-S) mechanism, and then velo

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34

Holback, B., Å. Jacksén, L. Åhlén, et al. "LINDA – the Astrid-2 Langmuir probe instrument." Annales Geophysicae 19, no. 6 (2001): 601–10. http://dx.doi.org/10.5194/angeo-19-601-2001.

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Abstract. The Swedish micro-satellite Astrid-2, designed for studies in magnetosperic physics, was launched into orbit on 10 December 1998 from the Russian cosmodrome Plesetsk. It was injected into a circular orbit at 1000 km and at 83 degrees inclination. The satellite carried, among other instruments, a double Langmuir Probe instrument called LINDA (Langmuir INterferometer and Density instrument for Astrid-2). The scientific goals of this instrument, as well as the technical design and possible modes of operation, are described. LINDA consists of two lightweight deployable boom systems, each

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35

Swiss, James J., Donald J. Smrke, and William M. Pistruzak. "UNIQUE DISPOSAL TECHNIQUES FOR ARCTIC OIL SPILL RESPONSE." International Oil Spill Conference Proceedings 1985, no. 1 (1985): 395–98. http://dx.doi.org/10.7901/2169-3358-1985-1-395.

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ABSTRACT Disposing of oil and oiled debris from Arctic oil spills presents problems not encountered in temperate regions. The remoteness of potential spill sites, the wide range of environmental conditions, the lack of support facilities like roads and dump sites, and the presence of permafrost make it impossible to use many standard disposal techniques used in the south. To solve this problem, Dome Petroleum Limited, has developed a number of unique techniques for disposing of oil and oiled debris in Arctic spill responses. These techniques include (1) a method for using air-deployable ignite

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36

Gurubaran, Subramanian, Manu Shanmugam, Kaliappan Jawahar, Kaliappan Emperumal, Prasanna Mahavarkar, and Suneel Kumar Buduru. "A high-altitude balloon experiment to probe stratospheric electric fields from low latitudes." Annales Geophysicae 35, no. 2 (2017): 189–201. http://dx.doi.org/10.5194/angeo-35-189-2017.

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Abstract. The Earth's electrical environment hosts a giant electrical circuit, often referred to as the global electric circuit (GEC), linking the various sources of electrical generators located in the lower atmosphere, the ionosphere and the magnetosphere. The middle atmosphere (stratosphere and mesosphere) has been traditionally believed to be passively transmitting electric fields generated elsewhere. Some observations have reported anomalously large electric fields at these altitudes, and the scientific community has had to revisit the earlier hypothesis time and again. At stratospheric a

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37

Yang, Hui, Fengshuai Lu, Hongwei Guo, and Rongqiang Liu. "Design of a New N-Shape Composite Ultra-Thin Deployable Boom in the Post-Buckling Range Using Response Surface Method and Optimization." IEEE Access 7 (2019): 129659–65. http://dx.doi.org/10.1109/access.2019.2934744.

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38

Le Boyer, Arnaud, Matthew H. Alford, Nicole Couto, et al. "Modular, Flexible, Low-Cost Microstructure Measurements: The Epsilometer." Journal of Atmospheric and Oceanic Technology 38, no. 3 (2021): 657–68. http://dx.doi.org/10.1175/jtech-d-20-0116.1.

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AbstractThe Epsilometer (“epsi”) is a small (7 cm diameter × 30 cm long), low-power (0.15 W), and extremely modular microstructure package measuring thermal and kinetic energy dissipation rates, χ and ε. Both the shear probes and FP07 temperature sensors are fabricated in house following techniques developed by Michael Gregg at the Applied Physics Laboratory/University of Washington (APL/UW). Sampling eight channels (two shear, two temperature, three-axis accelerometer, and a spare for future sensors) at 24 bit precision and 325 Hz, the system can be deployed in standalone mode (battery power

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39

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

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The stowing and deployment processes of a self-deployable sunshield are investigated numerically in this paper. The composition of the self-deployable sunshield is described. Deployed moment theoretical models for lenticular booms are formulated based on the bending theory of curved shell. The numerical analysis method of deployed moment is proposed. Two types of control methods for a fold crease are presented, and a dynamic analysis model considering geometry and nonlinear contact is built. The analysis results indicate that the press flattening method can be used effectively for controlling

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40

Wang, Sicong, Mark Schenk, Shengyuan Jiang, and Andrew Viquerat. "Blossoming analysis of composite deployable booms." Thin-Walled Structures 157 (December 2020): 107098. http://dx.doi.org/10.1016/j.tws.2020.107098.

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41

Fanning, P., and L. Hollaway. "The Deployment Analysis of a Large Space Antenna." International Journal of Space Structures 8, no. 3 (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 ‘l

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42

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

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43

Firth, Jordan A., and Mark R. Pankow. "Advanced Dual-Pull Mechanism for Deployable Spacecraft Booms." Journal of Spacecraft and Rockets 56, no. 2 (2019): 569–76. http://dx.doi.org/10.2514/1.a34243.

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44

Hoskin, Adam, Andrew Viquerat, and Guglielmo S. Aglietti. "Tip force during blossoming of coiled deployable booms." International Journal of Solids and Structures 118-119 (July 2017): 58–69. http://dx.doi.org/10.1016/j.ijsolstr.2017.04.023.

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45

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

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This work deals with the feasibility and reliability about the use of shape memory alloys (SMAs) as mechanical actuators for solar sail self-deployment instead of heavy and bulky mechanical booms. Solar sails exploit radiation pressure a as propulsion system for the exploration of the solar system. Sunlight is used to propel space vehicles by reflecting solar photons from a large and light-weight material, so that no propellant is required for primary propulsion. In this work, different small-scale solar sail prototypes (SSP) were studied, manufactured, and tested for bending and in three diff

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46

Schenk, Mark, Andrew D. Viquerat, Keith A. Seffen, and Simon D. Guest. "Review of Inflatable Booms for Deployable Space Structures: Packing and Rigidization." Journal of Spacecraft and Rockets 51, no. 3 (2014): 762–78. http://dx.doi.org/10.2514/1.a32598.

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47

Sickinger, Christoph, Lars Herbeck, and Elmar Breitbach. "Structural engineering on deployable CFRP booms for a solar propelled sailcraft." Acta Astronautica 58, no. 4 (2006): 185–96. http://dx.doi.org/10.1016/j.actaastro.2005.09.011.

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48

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

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49

Swetha Lakshmi, S., M. Varsha, G. M. Sabari Krishnaa, et al. "Thermo-structural analysis of deployable composite booms with slotted hinges for space applications." Materials Today: Proceedings 56 (2022): 3564–70. http://dx.doi.org/10.1016/j.matpr.2021.11.633.

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50

Mao, Huina, Pier Luigi Ganga, Michele Ghiozzi, Nickolay Ivchenko, and Gunnar Tibert. "Deployment of Bistable Self-Deployable Tape Spring Booms Using a Gravity Offloading System." Journal of Aerospace Engineering 30, no. 4 (2017): 04017007. http://dx.doi.org/10.1061/(asce)as.1943-5525.0000709.

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