Relevant bibliographies by topics / Flexible Spacecraft Control

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
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Academic literature on the topic 'Flexible Spacecraft Control'

Author: Grafiati
Published: 4 June 2021
Last updated: 6 September 2023

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Journal articles on the topic "Flexible Spacecraft Control"

1

Yu, Ya Nan, Xiu Yun Meng, and Li Chao Ma. "PSO-Based State Feedback Control of Flexible Spacecraft for Attitude Tracking and Vibration Suppression." Applied Mechanics and Materials 229-231 (November 2012): 2161–65. http://dx.doi.org/10.4028/www.scientific.net/amm.229-231.2161.

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PD state-feedback controller has been adopted in many spacecraft for attitude tracking and presents good performance. For flexible spacecraft, the controller can be designed with a term which takes into account the flexible dynamics. However, duo to nonlinearity and coupling, how to determine state-feedback control parameters which ensure fast attitude tracking and significant vibration suppression must be considered. In this paper, the dynamics model of spacecraft with flexible appendages is derived with the hybrid coordinate method and the full state feedback controller originated from the P
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Wang, Guan Yu, Wei Ping Ge, Guang Wei Yang, and Sheng Chao Wang. "CSVS Method for Spacecraft with Two Flexible Appendages during Attitude Maneuver." Advanced Materials Research 1049-1050 (October 2014): 939–44. http://dx.doi.org/10.4028/www.scientific.net/amr.1049-1050.939.

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An angle maneuver control strategy of spacecraft with two flexible appendages based on component synthesis vibration suppression (CSVS) method is put forward. Unwanted flexible vibration modes can be eliminated while desired rigid motion can be achieved by this method. Jet device and Momentum wheel system are used as the actuator of the spacecraft’s angle maneuver. Several time-fuel control strategies are designed for spacecraft with flexible appendages. Simulation results validate the feasibility of the CSVS method. The DC motor control method is researched in order to combine momentum wheel
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Kwatny, H. G., M. J. Baek, W. H. Bennett, and G. L. Blankenship. "Attitude Control of Articulated, Flexible Spacecraft." IFAC Proceedings Volumes 25, no. 13 (1992): 463–69. http://dx.doi.org/10.1016/s1474-6670(17)52325-3.

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Zhang, Shuo, Yukang Zhou, and Suting Cai. "Fractional-Order PD Attitude Control for a Type of Spacecraft with Flexible Appendages." Fractal and Fractional 6, no. 10 (2022): 601. http://dx.doi.org/10.3390/fractalfract6100601.

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As large-sized spacecraft have been developed, they have been equipped with flexible appendages, such as solar cell plates and mechanical flexible arms. The attitude control of spacecraft with flexible appendages has become more complex, with higher requirements. In this paper, a fractional-order PD attitude control method for a type of spacecraft with flexible appendages is presented. Firstly, a lumped parameter model of a spacecraft with flexible appendages is constructed, which provides the transfer function of the attitude angle and external moment. Then, a design method for the fractional
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Nadafi, Reza, Mansour Kabganian, Ali Kamali, and Mahboobeh Hossein Nejad. "Super-twisting sliding mode control design based on Lyapunov criteria for attitude tracking control and vibration suppression of a flexible spacecraft." Measurement and Control 52, no. 7-8 (2019): 814–31. http://dx.doi.org/10.1177/0020294019847696.

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The three-axis attitude tracking manoeuvre and vibration suppression of a flexible spacecraft in the presence of external disturbances are investigated in this paper. The spacecraft consists of a rigid hub and two flexible appendages. The Euler–Bernoulli beam theory is used to model the flexible parts. The attitude dynamic equations of motion are derived using the law of conservation of angular momentum, and the flexural equations are derived. The attitude of the spacecraft is represented using the quaternion parameters. The controller is designed based on the super-twisting sliding mode contr
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He, Guiqin, and Dengqing Cao. "Dynamic Modeling and Attitude–Vibration Cooperative Control for a Large-Scale Flexible Spacecraft." Actuators 12, no. 4 (2023): 167. http://dx.doi.org/10.3390/act12040167.

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Modern spacecraft usually have larger and more flexible appendages whose vibration becomes more and more prominent, and it has a great influence on the precision of spacecraft attitude. Therefore, the cooperative control of attitude maneuvering and structural vibration of the system has become a significant issue in the spacecraft design process. We developed a low-dimensional and high-precision mathematical model for a large-scale flexible spacecraft (LSFS) equipped with a pair of hinged solar arrays in this paper. The analytic global modes are used to obtain the rigid–flexible coupling discr
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Huang, Wenke, Linfeng Li, Wenye Dong, Liwen He, Taoming Feng, and Jun Xiao. "Finite element dynamic modeling and attitude control for a slender flexible spacecraft." Journal of Physics: Conference Series 2472, no. 1 (2023): 012034. http://dx.doi.org/10.1088/1742-6596/2472/1/012034.

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Abstract This paper aims to study the dynamic modeling and attitude control of a kind of slender flexible spacecraft. The basic structure of this kind of spacecraft is different from the traditional structure of a center rigid body with flexible appendages, but rigid bodies at both ends, which are connected by a flexible truss structure. Firstly, the finite element modeling method is adopted to establish the dynamic model of this kind of spacecraft, and the vibration frequency and damping of the flexible structure are obtained. The unconstrained modes of the flexible spacecraft are obtained th
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Bennett, W. H., C. LaVigna, H. G. Kwatny, and G. Blankenship. "Nonlinear and Adaptive Control of Flexible Space Structures." Journal of Dynamic Systems, Measurement, and Control 115, no. 1 (1993): 86–94. http://dx.doi.org/10.1115/1.2897412.

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This paper addresses design of nonlinear control systems for rapid, large angle multiaxis, slewing and LOS pointing of realistic flexible space structures. The application of methods based on adaptive feedback linearization for nonlinear control design for flexible space structures is presented. A comprehensive approach to modeling the nonlinear dynamics and attitude control of multibody systems with structural flexure is considered. Adaptive feedback linearizing control laws are described based on Lagrangian dynamical system model for the spacecraft. Simulation results for attitude slewing an
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Joshi, S. M., and P. G. Maghami. "Robust dissipative compensators for flexible spacecraft control." IEEE Transactions on Aerospace and Electronic Systems 28, no. 3 (1992): 768–74. http://dx.doi.org/10.1109/7.256297.

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Ye, Dong, and Zhaowei Sun. "Variable structure tracking control for flexible spacecraft." Aircraft Engineering and Aerospace Technology 88, no. 4 (2016): 508–14. http://dx.doi.org/10.1108/aeat-04-2014-0038.

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Dissertations / Theses on the topic "Flexible Spacecraft Control"

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Watkins, R. Joseph. "The attitude control of flexible spacecraft." Thesis, Monterey, California. Naval Postgraduate School, 1991. http://hdl.handle.net/10945/26896.

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Approved for public release; distribution is unlimited<br>This thesis details the design of the Naval Postgraduate School's Flexible Spacecraft Simulator and the first attempts at simulation and control of the model. The effect of flexible structures on the attitude control spacecraft has been a topic of research for many years. Only recently has the technology to actually test models and theory on the ground been available. At the Naval Postgraduate School, an experimental testbed for research into this area has been contracted. This facility has a model of a satellite with a flexible arm flo
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Quinn, Roger D. "Maneuver and control of flexible spacecraft." Diss., Virginia Polytechnic Institute and State University, 1985. http://hdl.handle.net/10919/53895.

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This dissertation is concerned with the problem of slewing large flexible structures in space and simultaneously suppressing any vibrations. The equations of motion for a three-dimensional spacecraft undergoing large rigid-body maneuvers are derived. The elastic motions are assumed to remain in the linear range. A method of substructure synthesis is presented which spatially discretizes the equations of motion. A perturbation approach is used to solve the equations of motion. The zero-order equations describing the rigid-body maneuver are independent of the first-order vibration problem which
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Dodds, S. J. "Gas jet attitude control of flexible spacecraft." Thesis, University of Surrey, 1986. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.372009.

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Wood, Timothy David. "Modelling and control of large flexible spacecraft." Thesis, University of Bath, 1986. https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.376345.

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Strong, Ronald E. "Control of flexible spacecraft structures using H-infinity wave absorbing control." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1994. http://handle.dtic.mil/100.2/ADA293141.

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Humphries, T. T. "The dynamics and control of large flexible asymmetric spacecraft." Thesis, Cranfield University, 1991. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.305281.

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Sharony, Yaakov. "Control of flexible spacecraft during a minimum-time maneuver." Diss., Virginia Polytechnic Institute and State University, 1988. http://hdl.handle.net/10919/77834.

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The problem of simultaneous maneuver and vibration control of a flexible spacecraft can be solved by means of a perturbation approach whereby the slewing of the spacecraft regarded as rigid represents the zero-order problem and the control of elastic vibration, as well as of elastic perturbations from the rigid-body maneuver, represents the first-order problem. The zero-order control is to be carried out in minimum time, which implies on-off control. On the other hand, the perturbed model is described by a high-order set of linear time-varying ordinary differential equations subjected to persi
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Kwak, Moon Kyu. "Dynamics and control of spacecraft with retargeting flexible antennas." Diss., Virginia Polytechnic Institute and State University, 1989. http://hdl.handle.net/10919/54227.

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This dissertation is concerned with the dynamics and control of spacecraft consisting of a rigid platform and a given number of retargeting flexible antennas. The mission consists of maneuvering the antennas so as to coincide with preselected lines of sight while stabilizing the platform in an inertial space and suppressing the elastic vibration of the antennas. The dissertation contains the derivation of the equations of motion by a Lagrangian approach using quasi-coordinates, as well as a procedure for designing the feedback controls. Assuming that antennas are flexible, distributed paramete
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Giuliano, Francesco. "Robust attitude control of a spacecraft with flexible dynamics." Thesis, KTH, Skolan för elektroteknik och datavetenskap (EECS), 2019. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-254418.

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The employment of Electrical Propulsion, to reduce the cost of satellites, has also increasedthe use of large solar arrays. Such solar panels are associated with low-frequency resonantmodes, and to ensure fine pointing of the satellite, the attitude control should not excitethese modes. This is a difficult task in such complex systems, whose exact a prioriknowledge is largely unavailable during the early design phase.The primary scope of this thesis is to synthesize a robust algorithm for attitude controlthat deals with modeling errors.The first part is dedicated to understanding the principal
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Hailey, Jeffrey A. "Experimental verification attitude control techniques for flexible spacecraft slew maneuvers." Thesis, Monterey, California. Naval Postgraduate School, 1992. http://hdl.handle.net/10945/23670.

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Approved for public release; distribution is unliminted<br>The experimental verification of attitude control designs for flexible spacecraft is essential for reliable operation in space. The Flexible Spacecraft Simulator (FSS) at the Naval Postgraduate School is designed to test a variety of control designs. The experimental setup simulates pitch axis motion of a flexible spacecraft consisting of a rigid central body and a flexible appendage connecting a reflector. The primary actuators are a reaction wheel and thrusters. Angular position information is obtained with a rotary variable di
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Books on the topic "Flexible Spacecraft Control"

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Mazzini, Leonardo. Flexible Spacecraft Dynamics, Control and Guidance. Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-25540-8.

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Watkins, R. Joseph. The attitude control of flexible spacecraft. Naval Postgraduate School, 1991.

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Onoda, Junjiro. Simultaneous structure/control optimization of large flexible spacecraft. American Institute of Aeronautics and Astronautics, 1987.

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Silverberg, Larry M. A control system design approach for flexible spacecraft. National Aeronautics and Space Administration, Langley Research Center, 1986.

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Center, Langley Research, ed. A control system design approach for flexible spacecraft. National Aeronautics and Space Administration, Langley Research Center, 1986.

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Baxter, Bruce. Feedback control of a flexible spacecraft with robustness improvement. Brunel University, 1991.

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Suhada, Jayasuriya, Texas A & M University., and Lyndon B. Johnson Space Center., eds. Active vibration control techniques for flexible space structures. Texas A&M University, 1990.

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Wang, Jie, and Dong-Xu Li. Rigid-Flexible Coupling Dynamics and Control of Flexible Spacecraft with Time-Varying Parameters. Springer Singapore, 2022. http://dx.doi.org/10.1007/978-981-16-5097-0.

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Chun, Hon M. Large-angle slewing maneuvers for flexible spacecraft. Langley Research Center, 1988.

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Taylor, Lawrence W. 4th NASA Workshop on Computational Control of Flexible Aerospace Systems: Proceedings of a workshop sponsored by the National Aeronautics and Space Administration and held at the Kingsmill Resort, Williamsburg, Virginia, July 11, 1990. Langley Reseearch Center, 1991.

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Book chapters on the topic "Flexible Spacecraft Control"

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Mazzini, Leonardo. "Spacecraft Propulsion." In Flexible Spacecraft Dynamics, Control and Guidance. Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-25540-8_8.

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Mazzini, Leonardo. "Attitude Control Methods." In Flexible Spacecraft Dynamics, Control and Guidance. Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-25540-8_6.

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Wang, Jie, and Dong-Xu Li. "Rigid-Flexible Coupling Control Method for Flexible Spacecraft." In Rigid-Flexible Coupling Dynamics and Control of Flexible Spacecraft with Time-Varying Parameters. Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-16-5097-0_6.

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Mazzini, Leonardo. "The Optimal Control Theory." In Flexible Spacecraft Dynamics, Control and Guidance. Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-25540-8_5.

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Mazzini, Leonardo. "The Kinematics of the Flexible Satellite." In Flexible Spacecraft Dynamics, Control and Guidance. Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-25540-8_2.

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Mazzini, Leonardo. "The Dynamics of the Flexible Satellite." In Flexible Spacecraft Dynamics, Control and Guidance. Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-25540-8_3.

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Wang, Jie, and Dong-Xu Li. "Rigid-Flexible Coupling Dynamic Analysis of Flexible Spacecraft." In Rigid-Flexible Coupling Dynamics and Control of Flexible Spacecraft with Time-Varying Parameters. Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-16-5097-0_3.

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Wang, Jie, and Dong-Xu Li. "Rigid-Flexible Coupling Dynamic Modeling of Flexible Spacecraft." In Rigid-Flexible Coupling Dynamics and Control of Flexible Spacecraft with Time-Varying Parameters. Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-16-5097-0_2.

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Mazzini, Leonardo. "Introduction." In Flexible Spacecraft Dynamics, Control and Guidance. Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-25540-8_1.

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Mazzini, Leonardo. "The AOCS Functions." In Flexible Spacecraft Dynamics, Control and Guidance. Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-25540-8_4.

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Conference papers on the topic "Flexible Spacecraft Control"

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Li, Guang-xing, Jun Zhou, and Feng-qi Zhou. "Variable Structure Control for Flexible Spacecraft." In 2006 Chinese Control Conference. IEEE, 2006. http://dx.doi.org/10.1109/chicc.2006.280813.

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Joshi, S. M., and P. G. Maghami. "Dissipative Compensators for Flexible Spacecraft Control." In 1990 American Control Conference. IEEE, 1990. http://dx.doi.org/10.23919/acc.1990.4791069.

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Williams, Trevor. "Transmission Zeros of Flexible Spinning Spacecraft." In 1991 American Control Conference. IEEE, 1991. http://dx.doi.org/10.23919/acc.1991.4791849.

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Di Gennaro, S. "Active vibration suppression for flexible spacecraft." In 1997 European Control Conference (ECC). IEEE, 1997. http://dx.doi.org/10.23919/ecc.1997.7082671.

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Ben-Asher, Joseph, John Burns, and Eugene Cliff. "Time optimal slewing of flexible spacecraft." In 26th IEEE Conference on Decision and Control. IEEE, 1987. http://dx.doi.org/10.1109/cdc.1987.272896.

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Lucibello, Pasquale. "Steering a flexible spacecraft between equilibrium points." In 1992 American Control Conference. IEEE, 1992. http://dx.doi.org/10.23919/acc.1992.4792476.

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Joshi, S. M. "Failure-Accommodating Control of Large Flexible Spacecraft." In 1986 American Control Conference. IEEE, 1986. http://dx.doi.org/10.23919/acc.1986.4788929.

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Dwyer, Thomas A. W. "Automatic Decoupling of Flexible Spacecraft Slewing Maneuvers." In 1986 American Control Conference. IEEE, 1986. http://dx.doi.org/10.23919/acc.1986.4789168.

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BOSSI, J. "A laboratory simulation of flexible spacecraft control." In Guidance, Navigation and Control Conference. American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-2325.

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Malekzadeh, Maryam, Abolghasem Naghash, and Ali Talebi. "Flexible Spacecraft Control Using Robust Feedback Linearization." In AIAA Guidance, Navigation, and Control Conference. American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-8295.

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Reports on the topic "Flexible Spacecraft Control"

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Junkins, John L. Optimization of Closed Loop Eigenvalues: Maneuvering, Vibration Control, and Structure/Control Design Iteration for Flexible Spacecraft. Defense Technical Information Center, 1986. http://dx.doi.org/10.21236/ada172716.

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