Global ETD Search
Search theses and dissertations gathered from participating repositories worldwide. Every result links back to the library that holds it. No account is needed.
Results
Showing 1 to 13 of 13 for “"Flexible Spacecraft"”.
-
Maneuver and control of flexible spacecraft
… 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. …
-
Time optimal slewing of flexible spacecraft
The time optimal slewing problem for flexible spacecraft is considered. We study single-axis rotational maneuvers for a simple flexible system, consisting of a rigid hub with an elastic appendage. The equations of motions are derived by Hamilton’s Principle, and a discrete nonlinear model is …
-
Large-angle slewing maneuvers for flexible spacecraft
Thesis (Ph. D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1986.
-
Online Estimation of Unknown Parameters for Flexible Spacecraft
<p>Attitude controls methods of highly flexible spacecraft have seen increased interest over the last decades thanks to the technological development of flexible solar panels and deploy-ables, which improves the capabilities of small satellites. However, a high-fidelity model of the flexible mode …
-
Modeling and Slew-Maneuver Control of a Flexible Spacecraft
<p>Slew-maneuver control problem is studied for a flexible spacecraft consisting of a rigid main body to which a long flexible appendage is attached. Nonlinear dynamical system models are developed using both distributed parameter modeling and discrete parameter modeling; these models are shown to …
-
Dynamics and control of flexible spacecraft : a case study
… 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 …
-
Control of flexible spacecraft during a minimum-time maneuver
… 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 …
-
Gravity and laboratory suspension effects on the dynamics of controlled flexible spacecraft
Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1993.
-
Adaptive Control for Spacecraft with Flexible Appendages with Unknown Parameters
<p>Flexible spacecraft pose several challenges in control design due to the uncertain dynamical model and the underactuated nature of these systems. Adaptive and robust controllers are the common choice for these systems to either meet operational requirements like attitude pointing or to suppress …
-
A perturbation approach to control of rotational/translational maneuvers of flexible space vehicles
An open loop control law is applied to a flexible spacecraft that admits translational, as well as rotational and flexural motion. The translational degrees of freedom are coupled to the rotation and deformation through the active controls applied to the structure. The objective of any maneuver is …
-
Design and control of a space based two link manipulator with Lyapunov based control laws
The Flexible Spacecraft Simulator (FSS) at the Naval Postgraduate School was modified by replacing the flexible appendage with a two link robotic manipulator. This experimental setup was designed to simulate motion of a spacecraft about the pitch axis. The spacecraft consists of a main body, a two …
-
A Novel Magnetorheological Fluid Damper for a Small Spacecraft with Flexible Appendages
… electrical power may be the adoption of larger, flexible solar arrays. However, spacecraft with flexible appendages have historically presented attitude control challenges relating to platform stability given the dynamic response of the flexible components to applied torques. These challenges may …
-
Development and experimental validation of direct controller tuning for spaceborne telescopes
… to the successful controllers from predecessor spacecraft. Two principal tools are developed: an analysis algorithm that quantifies each sensor/actuator combination's effectiveness for control, and a design engine which tunes a baseline controller to improve performance and/or stability …