Lim, Sang Seok.2009-03-202009-03-2019901990Source: Dissertation Abstracts International, Volume: 52-11, Section: B, page: 5943.9780315605381http://hdl.handle.net/10393/5822http://dx.doi.org/10.20381/ruor-14554In this thesis a preliminary formulation of large space structures and their stabilization is considered. The system consists of a (rigid) massive body and flexible configurations which consist of several beams, forming the space structure. The rigid body is located at the center of the space structure and may play the role of experimental modules. A complete dynamics of the system has been developed using Hamilton's principle. Euler-Bernoulli, Rayleigh and Timoshenko beam theories are utilized to derive the dynamic equations governing the vibration of the beams. The equations that govern the motion of the complete system consist of six ordinary differential equations and several partial differential equations together with appropriate boundary conditions. The partial differential equations govern the vibration of flexible components. The ordinary differential equations describe the rotational and translational motion of the central body. The dynamics indicate very strong interaction among rigid body translation, rigid body rotation and vibrations of flexible members through nonlinear couplings. Hence any rotation of the rigid body induces vibration in the beams and vice-versa. Also any disturbance in the orbit induces vibration in the beams and wobbles in the body rotation and vice-versa. This makes the system performance unsatisfactory for many practical applications. In this thesis stabilization of the above mentioned system subject to external disturbances is considered. The asymptotic stability of the perturbed system by applying several types of stabilizing controls such as proportional controls, deadzone controls or saturation controls is proved using Lyapunov's method. Numerical simulations are carried out in order to illustrate the impact of dynamic coupling or interaction among several members of the system and the effectiveness of the suggested feedback controls for stabilization. Stability of a spacecraft and a space station under the influence of slew maneuvering is numerically investigated.336 p.Engineering, Aerospace.Thesis