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Relevant bibliographies by topics / Tethered satellites

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Academic literature on the topic 'Tethered satellites'

Author: Grafiati

Published: 4 June 2021

Last updated: 30 July 2024

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Journal articles on the topic "Tethered satellites"

1

Zhang, Fan, Panfeng Huang, Zhongjie Meng, and Zhengxiong Liu. "Dynamics modeling and model selection of space debris removal via the Tethered Space Robot." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 231, no. 10 (2016): 1873–97. http://dx.doi.org/10.1177/0954410016664914.

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This work proposes a scheme to select a proper dynamics model for space debris removal which is captured by a Tethered Space Robot. A proper dynamics model is crucial for the parameters estimation and controller design in a Tethered Space Robot mission, in particular, for the retrieval or de-orbiting of uncooperative target. A new dynamics model of the system is derived by treating the base satellite and the space debris as rigid bodies in the presence of offsets, and with the effect of the tether’s flexibility and elasticity. Then the equations of motion are simplified based on the attitude a

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2

Zhong, Yini, and Rui Zhong. "Dynamics, Deployment and Retrieval Strategy for Satellite-Sail Transverse Formation with Model Inaccuracy." Aerospace 9, no. 10 (2022): 602. http://dx.doi.org/10.3390/aerospace9100602.

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One of the important applications of the space tethered system is formation flying. To satisfy the requirement for interferometry of ground targets by remote-sensing satellites, a new type of tethered solar sail spacecraft has been proposed in recent research. The replacement of subsatellites of conventional tethered satellite systems with solar sail spacecraft allows for a special formation configuration in which the main satellite is in sun-synchronous orbit and the subsolar sail is in displaced orbit. If the solar sail is at the appropriate attitude, the main satellite and the solar sail sp

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Shan, Minghe, and Lingling Shi. "Comparison of Tethered Post-Capture System Models for Space Debris Removal." Aerospace 9, no. 1 (2022): 33. http://dx.doi.org/10.3390/aerospace9010033.

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The space debris problem poses a huge threat to operational satellites and has to be addressed. Multiple removal methods have been proposed to keep Earth’s orbit stable. Flexible connection capturing methods, such as the harpoon system, tether–gripper system and the net system, are potential candidate methods for space debris removal in the future. However, the tethered system is usually assumed as a dumbbell model where two end masses are connected by a rigid bar. This traditional model is not accurate enough to predict the motion of the target, neither the whole system. In this paper, three

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4

Sarego, Giulia, Lorenzo Olivieri, Andrea Valmorbida, et al. "Deployment requirements for deorbiting electrodynamic tether technology." CEAS Space Journal 13, no. 4 (2021): 567–81. http://dx.doi.org/10.1007/s12567-021-00349-5.

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AbstractIn the last decades, green deorbiting technologies have begun to be investigated and have raised a great interest in the space community. Among the others, electrodynamic tethers appear to be a promising option. By interacting with the surrounding ionosphere, electrodynamic tethers generate a drag Lorentz force to decrease the orbit altitude of the satellite, causing its re-entry in the atmosphere without using propellant. In this work, the requirements that drive the design of the deployment mechanism proposed for the H2020 Project E.T.PACK—Electrodynamic Tether Technology for Passive

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5

Zhao, Guo Wei, Bin Tang, Liang Sun, and Xing Min Zhang. "Effect and Control of Pendular Motion of Abandoned Satellite on Tether Drag System." Applied Mechanics and Materials 513-517 (February 2014): 3900–3906. http://dx.doi.org/10.4028/www.scientific.net/amm.513-517.3900.

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As a kind of typical on-orbit capture and aberrance technology, space tether de-orbit system has broad application prospect in terms of cleaning space debris and abandoned satellites. In the paper, the attitude dynamics equations of the tether de-orbit system is established based on law of moment of momentum; Against the background of de-orbiting under a constant thrust in the tangential direction, the optimized PD control law with limited attitude feedback on jet control and momentum wheel control is designed for the mission satellite; The oscillation characteristics of the attitude of abando

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6

Zhang, Kangyu, Kuan Lu, Xiaohui Gu, Chao Fu, and Shibo Zhao. "Dynamic Behavior Analysis and Stability Control of Tethered Satellite Formation Deployment." Sensors 22, no. 1 (2021): 62. http://dx.doi.org/10.3390/s22010062.

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In recent years, Tethered Space Systems (TSSs) have received significant attention in aerospace research as a result of their significant advantages: dexterousness, long life cycles and fuel-less engines. However, configurational conversion processes of tethered satellite formation systems in a complex space environment are essentially unstable. Due to their structural peculiarities and the special environment in outer space, TSS vibrations are easily produced. These types of vibrations are extremely harmful to spacecraft. Hence, the nonlinear dynamic behavior of systems based on a simplified

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7

Campbell, Ben, and Lawrence Dale Thomas. "Basic Orbit Design and Maneuvers for Satellite Constellations Deployed Using Momentum Exchange Tethers." Aerospace 11, no. 3 (2024): 182. http://dx.doi.org/10.3390/aerospace11030182.

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This article describes a new alternative approach to satellite constellation deployment by incorporating momentum exchange tethers (METs). Traditional methods of deploying satellite constellations have limitations, typically involving costly propulsion systems and extended dispersion times. METs offer a novel solution by efficiently transferring momentum between tethered objects, reducing the need for onboard propellants and streamlining the deployment process. This article discusses orbit design and maneuvers for different mission architectures using asymmetrical and symmetrical tether releas

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8

Schutte, Aaron D., and Brian A. Dooley. "Constrained Motion of Tethered Satellites." Journal of Aerospace Engineering 18, no. 4 (2005): 242–50. http://dx.doi.org/10.1061/(asce)0893-1321(2005)18:4(242).

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9

Tirop, Paul Kimutai, and Zhang Jingrui. "Control of pendular motion on tethered satellites systems." Aircraft Engineering and Aerospace Technology 90, no. 9 (2018): 1479–85. http://dx.doi.org/10.1108/aeat-07-2017-0169.

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Purpose This paper aims to present the control laws to be used in the control of pendular motion on tethered satellite systems in space during orbiting by using a nonlinear design technique. Design/methodology/approach This work presents both physical and mathematical models represented in a circular orbit. Euler equation of the rigid body is applied under reasonable assumption so as to form the equations of pendular motion. These equations are then used to develop the control laws using a nonlinear design technique. The control laws are required to drive the in-plane angles and out-of-plane a

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10

Zhang, Jinxiu, and Zhigang Zhang. "Effects of Separation Strategy on Deployment of Multitethered Chain-Type Satellite System." Mathematical Problems in Engineering 2016 (2016): 1–15. http://dx.doi.org/10.1155/2016/2853658.

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This paper investigates the effects of separation strategy and parameters related to deployment on the dynamic behavior of multitethered chain-type satellite system. The system, including several satellites connected by tethers which are considered as massless and straight, is modeled as an extension of a two-body dumbbell tethered system. The dynamic equations of system in absence of perturbations and external disturbances are derived using Newtonian Method. To observe the effect of deployment rate on the motion of system, a parametric analysis of the deployment of a three-body tethered syste

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Dissertations / Theses on the topic "Tethered satellites"

1

Amier, Zine-Eddine. "On some transportation problems involving tethered satellite systems." Thesis, McGill University, 1987. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=66256.

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2

Robertson, Michael James. "Command generation for tethered satellite systems." Available online, Georgia Institute of Technology, 2005, 2004. http://etd.gatech.edu/theses/available/etd-04142005-090018/.

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Thesis (Ph.D.)--School of Mechanical Engineering, Georgia Institute of Technology, 2005.<br>Singhose, William, Committee Chair ; Banerjee, Arun, Committee Member ; Chen, Ye-Hwa, Committee Member ; Ebert-Uphoff, Imme, Committee Member ; Olds, John, Committee Member. Includes bibliographical references.

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Robertson, Michael James. "Command Generation for Tethered Satellite Systems." Diss., Georgia Institute of Technology, 2005. http://hdl.handle.net/1853/6921.

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Command generation is a process by which input commands are constructed or modified such that the system's response adheres to a set of desired performance specifications. Previously, a variety of command generation techniques such as input shaping have been used to reduce residual vibration, limit transient deflection, conserve fuel or adhere to numerous other performance specifications or performance measures. This dissertation addresses key issues regarding the application of command generation techniques to tethered satellite systems. The three primary objectives of this research are as

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Woo, Pamela. "Satellite placement using a partial space elevator." Thesis, McGill University, 2009. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=115992.

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The space elevator has been proposed as an alternate method for launching cargo into space. However, the construction of such a structure requires a material much stronger than any currently in existence. Instead, a partial elevator is considered for satellite placement. In the first part of the thesis, the fundamentals of very long tethered systems are studied. From static analysis on a simple two-body system, it is demonstrated that an assumption made in the conventional analysis does not apply to very long tethered systems. For a uniform tether, the axial stress distribution is obtained. Fo

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Jokic, Michael. "Modeling and analysis of tethered systems performing orbital maneuvers /." [St. Lucia, Qld.], 2004. http://www.library.uq.edu.au/pdfserve.php?image=thesisabs/absthe18477.pdf.

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Mankala, Kalyan K. "Satellite tether systems dynamic modeling and control /." Access to citation, abstract and download form provided by ProQuest Information and Learning Company; downloadable PDF file 4.07 Mb., 233 p, 2006. http://gateway.proquest.com/openurl?url_ver=Z39.88-2004&res_dat=xri:pqdiss&rft_val_fmt=info:ofi/fmt:kev:mtx:dissertation&rft_dat=xri:pqdiss:3220809.

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Hayes, Elizabeth Jo Volovecky Cicci David A. "Identification of a tethered satellite using an extended Kalman filter." Auburn, Ala., 2007. http://repo.lib.auburn.edu/2007%20Fall%20Theses/Volovecky_Elizabeth_5.pdf.

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8

Kearney, Mike-Alec. "An attitude control system for the deployment and stabilisation of a tethered dual CubeSat mission." Thesis, Stellenbosch : Stellenbosch University, 2013. http://hdl.handle.net/10019.1/80205.

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Thesis (MScEng)--Stellenbosch University, 2013.<br>ENGLISH ABSTRACT: The use of electrodynamic tethers on-board satellites is an exciting scientific prospect. These conductive tethers provide the means for satellites to generate power and to do propulsion by electrodynamic interaction with the geomagnetic field. Although well researched in theory, the concept has not enjoyed much success in practice. This study aims to utilise low-cost CubeSats as experimental tool to verify many of the theoretical principles that govern the behaviour of conductive tethers in orbit. The study provides a theore

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9

Zanutto, Denis. "Analysis of Propellantless Tethered System for the De-Orbiting of Satellites at End of Life." Doctoral thesis, Università degli studi di Padova, 2013. http://hdl.handle.net/11577/3422590.

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The increase of orbital debris and the consequent proliferation of smaller objects through fragmentation is driving the need for mitigation strategies that address this issue at its roots. The present guidelines for mitigation point out the need to deorbit new satellites injected into low Earth orbit (LEO) within a 25-year time. The issue is then how to deorbit the satellite with an efficient system that does not impair drastically the propellant budget of the satellite and, consequently, reduces its operating life. In this contest a passive system, which makes use of an electrodynamics tether

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Flodin, Linus. "Attitude and Orbit Control During Deorbit of Tethered Space Debris." Thesis, KTH, Farkost och flyg, 2015. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-166824.

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Due to the unsustainable space debris environment in Low Earth Orbit, debris objects must be removed to ensure future safe satellite operations. One proposed concept for deorbiting larger space debris objects, such as decommissioned satellites or spent upper rocket stages, is to use a chaser spacecraft connected to the debris object by an elastic tether, but the required technology is immature and there is a lack of flight experience. The inoperable satellite, Envisat, has been chosen as a representative object for controlled re-entry by performing several high thrust burns. The aim of this pa

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Books on the topic "Tethered satellites"

1

Maggio, Elizabeth. Space tethers: Evolution of a new technology for space applications. Edited by Aeritalia Space Systems Group. Aeritalia Space Systems Group, 1987.

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2

Ryan, Robert S. The dynamic phenomena of a tethered satellite: NASA's first Tethered Satellite Mission (TSS-1). National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

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3

Luca, Luigi De. First evaluation of the main parameters in the dynamics of the Small Expendable Deployer System (SEDS) for a tethered satellite. Langley Research Center, 1990.

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United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., ed. First evaluation of the main parameters in the dynamics of the Small Expendable Deployer System (SEDS) for a tethered satellite. National Aeronautics and Space Administration, Scientific and Technical Information Division, 1990.

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5

Krischke, Manfred. Anwendungen von seilgefesselten Raumfahrtsystemen in der oberen Atmosphäre. Utz, Wissenschaft, 1996.

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6

Bevilacqua, Franco. Tethers in space, ISU - International Space University, Boston, July 25, 1988. Aeritalia; IRI finmeccanica, 1988.

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7

Kent, Rockaway J., and United States. National Aeronautics and Space Administration., eds. Aerodynamic calculations related to tethered sub-satellite experiments: Final report. Vanderbilt University, School of Engineering, Dept of Mechanical Engineering, 1991.

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8

W, Ioup Juliette, and United States. National Aeronautics and Space Administration., eds. Determination of design and operation parameters for upper atmospheric research instrumentation to yield optimum resolution with deconvolution: Final report. National Aeronautics and Space Administration, 1991.

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W, Ioup Juliette, and United States. National Aeronautics and Space Administration., eds. Determination of design and operation parameters for upper atmospheric research instrumentation to yield optimum resolution with deconvolution.: Final report. National Aeronautics and Space Administration, 1988.

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10

C, Cron Alfred, United States. National Aeronautics and Space Administration., George C. Marshall Space Flight Center., and Applications of Tethers in Space Workshop (1983 : Williamsburg, Va.), eds. Applications of tethers in space: Proceedings of a workshop sponsored by the National Aeronautics and Space Administration, Washington, D.C., and George C. Marshall Space Flight Center, Huntsville, Alabama, and held in Williamsburg, Virginia, June 15-17, 1983. National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1985.

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Book chapters on the topic "Tethered satellites"

1

Gilchrist, B. E., R. A. Heelis, and W. J. Raitt. "Ionospheric multi-point measurements using tethered satellite sensors." In Measurement Techniques in Space Plasmas: Fields. American Geophysical Union, 1998. http://dx.doi.org/10.1029/gm103p0317.

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2

Sun, Guanghui, Chengwei Wu, Xiaolei Li, Zhiqiang Ma, Shidong Xu, and Xiangyu Shao. "Fractional-Order Tension Control for Tethered Satellite Systems." In Fractional-Order Sliding Mode Control: Methodologies and Applications. Springer Nature Switzerland, 2024. http://dx.doi.org/10.1007/978-3-031-60847-6_3.

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3

Schagerl, Martin, Alois Steindl, and Hans Troger. "Dynamical Analysis of the Deployment Process of Tethered Satellite Systems." In IUTAM-IASS Symposium on Deployable Structures: Theory and Applications. Springer Netherlands, 2002. http://dx.doi.org/10.1007/978-94-015-9514-8_36.

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Gang, Lei, Xian Yong, Feng Jie, and Wang Kui. "Research of Dynamics and Deploying Control Method on Tethered Satellite." In Proceedings of International Conference on Soft Computing Techniques and Engineering Application. Springer India, 2013. http://dx.doi.org/10.1007/978-81-322-1695-7_8.

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5

Yingying, Liu, Zhou Jun, and Chen Huanlong. "Variable Structure Control for Tethered Satellite Fast Deployment and Retrieval." In Future Control and Automation. Springer Berlin Heidelberg, 2012. http://dx.doi.org/10.1007/978-3-642-31006-5_19.

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6

Sangeetha, G. R., and Harikumar Ganesan. "Simulation of the Dynamics and Control of Tethered Small Satellite Deployment." In Lecture Notes in Mechanical Engineering. Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-1724-2_4.

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7

Hu, Haiyan, H. Wen, and D. P. Jin. "Dynamic Control and Ground-Based Experiments of a Tethered Satellite System." In IUTAM Symposium on Nonlinear Dynamics for Advanced Technologies and Engineering Design. Springer Netherlands, 2012. http://dx.doi.org/10.1007/978-94-007-5742-4_29.

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8

Ben, Wang, Wang Changqing, Li Aijun, and Yu M. Zabolotnov. "Robust Sliding Mode Tracking Control for Linear Tethered Satellite Formation Deployment." In Lecture Notes in Electrical Engineering. Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-15-8155-7_287.

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9

Poth, W., M. Schagerl, A. Steindl, W. Steiner, and H. Troger. "Numerically Efficient Formulation of The Equations of Motion of Tethered Satellite Systems." In IUTAM Symposium on Discretization Methods in Structural Mechanics. Springer Netherlands, 1999. http://dx.doi.org/10.1007/978-94-011-4589-3_16.

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10

Uphoff, Chauncey, Robert L. Forward, and Robert P. Hoyt. "The ‘Terminator Tether’: An Efficient Mechanism for End-of-Life Deorbit of Constellation Spacecraft." In Mission Design & Implementation of Satellite Constellations. Springer Netherlands, 1998. http://dx.doi.org/10.1007/978-94-011-5088-0_31.

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Conference papers on the topic "Tethered satellites"

1

Schutte, Aaron, and Brian Dooley. "Constrained Motion of Tethered Satellites." In ASME 2005 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2005. http://dx.doi.org/10.1115/detc2005-84042.

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The orbital motion of tethered satellites is a highly complex nonlinear problem. This investigation sets out to formulate a new method that significantly simplifies the dynamic analysis of tethered satellite systems. This is accomplished using the fundamental equation for constrained dynamic systems, which was formulated by Udwadia and Kalaba. As a result of this new method, a study of the periodicity of tethered satellite motion is conducted and an extension to formation flying satellites is made. With varying fixed tether lengths, the system motion seems to transition from periodic to quasi-

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2

Karl, Robert R., Henry G. Horak, David J. McComas, Thomas D. Wilkerson, and Harlan E. Spence. "A Bistatic LIDAR for Mapping of Ionospheric Species and A Precise Locating LIDAR for the Tethered Satellite System." In Optical Remote Sensing. Optica Publishing Group, 1985. http://dx.doi.org/10.1364/ors.1985.tuc22.

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A new ionospheric measurement concept using a bistatic lidar is described for the Tethered Satellite System (TSS) and the Space Shuttle as first suggested by McComas and Spence.1 This technique will utilize low power lasers in the Shuttle bay. Lightweight photometers with small electrical consumption will be placed on the sub-satellite to be deployed on a tether towards the earth. Ranges will be from 20 to 100 kilometers from the Shuttle with a minimum sustainable altitude of approximately 130 km. The long duration of this mission offers unique opportunities for a global mapping of trace speci

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3

HAYNES, M., and D. BODEN. "Out of plane maneuvering with tethered satellites." In Astrodynamics Conference. American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-4282.

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Pradeep, S. "Tension control for retrieval of tethered satellites." In AIAA/AAS Astrodynamics Specialist Conference and Exhibit. American Institute of Aeronautics and Astronautics, 1998. http://dx.doi.org/10.2514/6.1998-4475.

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Liaw, Der-Cherng, and Eyad H. Abed. "On Nonlinear Station-Keeping Control of Tethered Satellites." In 1990 American Control Conference. IEEE, 1990. http://dx.doi.org/10.23919/acc.1990.4791165.

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VADALI, S. "Feedback control of tethered satellites using Liapunov stability theory." In Dynamics Specialists Conference. American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-1197.

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Williams, Paul, and Pavel Trivailo. "On the Optimal Deployment and Retrieval of Tethered Satellites." In 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. American Institute of Aeronautics and Astronautics, 2005. http://dx.doi.org/10.2514/6.2005-4291.

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WEBSTER, JR., WILLIAM. "Applications of tethered satellites to some problems of terrestrial physics." In 26th Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-689.

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9

Valmorbida, Andrea, Lorenzo Olivieri, Giulia Sarego, et al. "Experimental Validation of a Deployment Mechanism for Tape-tethered Satellites." In 2021 IEEE 8th International Workshop on Metrology for AeroSpace (MetroAeroSpace). IEEE, 2021. http://dx.doi.org/10.1109/metroaerospace51421.2021.9511684.

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French, David, and Andre Mazzoleni. "Assessment of Micrometeoroid Threat to Tethered Satellites in Interplanetary Space." In AIAA SPACE 2009 Conference & Exposition. American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-6663.

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Reports on the topic "Tethered satellites"

1

Liaw, Der-Cherng, and Eyad H. Abed. Stabilization of Tethered Satellites During Station-Keeping. Defense Technical Information Center, 1990. http://dx.doi.org/10.21236/ada454742.

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Liaw, D. C., and E. H. Abed. Tethered Satellite System Stability. Defense Technical Information Center, 1989. http://dx.doi.org/10.21236/ada454743.

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Cicci, David A., John E. Cochran, and Jr. Identification and Motion Prediction of Tethered Satellite Systems. Defense Technical Information Center, 2001. http://dx.doi.org/10.21236/ada387974.

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Pernicka, Henry J. Design, Fabrication and Test of a Formation of Two Satellites Connected by a Tether. Defense Technical Information Center, 2007. http://dx.doi.org/10.21236/ada471603.

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