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Relevant bibliographies by topics / Flexible Spacecraft Control / Dissertations / Theses

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Dissertations / Theses on the topic 'Flexible Spacecraft Control'

Author: Grafiati

Published: 4 June 2021

Last updated: 6 September 2023

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1

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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2

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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3

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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4

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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5

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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6

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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7

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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8

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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9

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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10

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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11

France, Martin E. B. "Discrete-time control of a spacecraft with retargetable flexible antennas." Diss., Virginia Polytechnic Institute and State University, 1989. http://hdl.handle.net/10919/54528.

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This dissertation considers the discrete-time control of a spacecraft consisting of a rigid-platform with retargetable flexible antennas. The mission consists of independent minimum-time maneuvers of each antenna to coincide with pre-determined lines of sight, while the platform is stabilized in an inertial space and elastic vibration of the antennas is suppressed. The system is governed by a set of linearized, time-varying equations of motion. A discrete-time approach permits consideration of the time-varying nature of the system in designing the control law. Both global and decentralized c

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12

Akbulut, Burak. "Attitude Control Of Multiple Rigid Body Spacecraft With Flexible Hinge Joints." Master's thesis, METU, 2009. http://etd.lib.metu.edu.tr/upload/2/12611079/index.pdf.

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Control algorithm is developed for a satellite with flexible appendages to achieve a good pointing performance. Detailed modeling activity was carried out that consists of sensor and actuator models, disturbances and system dynamics. Common hardware found in the spacecraft such as reaction wheels, gyroscopes, star trackers etc. were included in the model. Furthermore, the Newton-Euler method is employed for the derivation of multi-body equations of motion. Evaluation of the pointing accuracy with proper pointing performance metrics such as accuracy, jitter and stability during slew maneuvers a

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13

Mosquera, Alonso Andrea. "State- and Parameter Estimation for Spacecraft with Flexible Appendages using Unscented Kalman Filters." Thesis, Luleå tekniska universitet, Institutionen för system- och rymdteknik, 2019. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-76320.

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The problem of system identification for dynamic effects on spacecraft has become increasingly relevant with the surge of agile spacecraft, which must perform large amplitude maneuvers at high rates. Precise knowledge of the state of the spacecraft, as well as of the parameters characterizing its motion, is vital for the design of control algorithms enabling stabilization and pointing accuracy. Traditional rigid body models and estimation methods are no longer sufficient to provide this knowledge. This thesis focuses on estimation of flexibility effects and spacecraft parameters through method

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14

Fulton, Joseph M. "LQG/LTR optimal attitude control of small flexible spacecraft using free-free boundary conditions." Diss., Connect to online resource, 2006. http://gateway.proquest.com/openurl?url_ver=Z39.88-2004&rft_val_fmt=info:ofi/fmt:kev:mtx:dissertation&res_dat=xri:pqdiss&rft_dat=xri:pqdiss:3219032.

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15

Jones, Evan S. "Development of an active damping system to aid in the attitude control of flexible spacecraft." Thesis, Monterey, California. Naval Postgraduate School, 1991. http://hdl.handle.net/10945/26471.

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16

Mattei, Giovanni. "Robust nonlinear control : from continuous time to sampled-data with aerospace applications." Thesis, Paris 11, 2015. http://www.theses.fr/2015PA112025/document.

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La thèse porte sur le développement des techniques non linéaires robustes de stabilisation et commande des systèmes avec perturbations de model. D’abord, on introduit les concepts de base de stabilité et stabilisabilité robuste dans le contexte des systèmes non linéaires. Ensuite, on présente une méthodologie de stabilisation par retour d’état en présence d’incertitudes qui ne sont pas dans l’image de la commande («unmatched»). L’approche récursive du «backstepping» permet de compenser les perturbations «unmatched» et de construire une fonction de Lyapunov contrôlée robuste, utilisable pour le

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17

Stellini, Julian. "Magnetic Attitude Control For Spacecraft with Flexible Appendages." Thesis, 2012. http://hdl.handle.net/1807/33545.

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The design of an attitude control system for a flexible spacecraft using magnetic actuation is considered. The nonlinear, linear, and modal equations of motion are developed for a general flexible body. Magnetic control is shown to be instantaneously underactuated, and is only controllable in the time-varying sense. A PD-like control scheme is proposed to address the attitude control problem for the linear system. Control gain limitations are shown to exist for the purely magnetic control. A hybrid control scheme is also proposed that relaxes these restrictions by adding a minimum control effo

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18

Lin, Gern-Liang, and 林耕良. "NONLINEAR ATTITUDE CONTROL OF RIGID SPACECRAFT WITH FLEXIBLE STRUCTURE." Thesis, 2000. http://ndltd.ncl.edu.tw/handle/64511678074665389524.

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博士<br>國立成功大學<br>航空太空工程學系<br>88<br>Two methods of adaptive damping and variable structure control incorporating the stable vibration control are applied in this dissertation for the simultaneous multi-axis reorientation of a rigid spacecraft with flexible structures. Uniqueness of the methods are that only three attitude torque actuators in the hub are required for the designed control law. Modeling of the dynamic system gives a set of coupled ordinary and partial differential equations, which includes the a

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19

Muneer, Khan Mohd. "Dynamics and control of flexible spacecraft : a case study." Thesis, 1992. http://hdl.handle.net/2429/1123.

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The First Milestone Configuration (FMC) of the proposed Space Station Freedom is considered for investigating the dynamics and control aspects of a space based orbiting flexible structure. The system dynamics is governed by an extremely lengthy (even in the matrix form), highly nonlinear, nonautonomous and coupled set of equations amenable only to a numerical solution. Two distinctly different discretization procedures, using the system modes and the component modes, are applied to the design as well as the Lagrange orientations of the FMC. The system is found to be inherently unstable suggest

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20

Joseph, Thomas K. "Dynamic Response Of A Satellite With Flexible Appendages And Its Passive Control." Thesis, 2009. https://etd.iisc.ac.in/handle/2005/943.

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Most present day spacecrafts have large interconnected solar panels. The dynamic behavior of the spacecraft in orbit can be modeled as a free rigid mass with flexible elements attached to it. The natural frequencies of such spacecrafts with deployed solar panels are very low. The low values of the natural frequencies pose difficulties for maneuvering the spacecraft. The control torque required to maneuver the spacecraft is influenced by the flexibility of the solar arrays. The control torque sets up transient oscillations in the flexible solar panels which in turn induces disturbances in the r

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21

Joseph, Thomas K. "Dynamic Response Of A Satellite With Flexible Appendages And Its Passive Control." Thesis, 2009. http://hdl.handle.net/2005/943.

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Most present day spacecrafts have large interconnected solar panels. The dynamic behavior of the spacecraft in orbit can be modeled as a free rigid mass with flexible elements attached to it. The natural frequencies of such spacecrafts with deployed solar panels are very low. The low values of the natural frequencies pose difficulties for maneuvering the spacecraft. The control torque required to maneuver the spacecraft is influenced by the flexibility of the solar arrays. The control torque sets up transient oscillations in the flexible solar panels which in turn induces disturbances in the r

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22

Forbes, James Richard. "Extensions of Input-output Stability Theory and the Control of Aerospace Systems." Thesis, 2011. http://hdl.handle.net/1807/31751.

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This thesis is concerned with input-output stability theory. Within this framework, it is of interest how inputs map to outputs through an operator that represents a system to be controlled or the controller itself. The Small Gain, Passivity, and Conic Sector Stability Theorems can be used to assess the stability of a negative feedback interconnection involving two systems that each have specific input-output properties. Our first contribution concerns characterization of the input-output properties of linear time-varying (LTV) systems. We present various theorems that ensure that a LTV sys

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