本篇論文中,探討以離散化的模型來模擬美國國加太空總署(NASA) 所提出的heliogyro 式太陽風帆飛行器。先前針對此種極輕、極長，且薄的葉片之研究已經可以由動態方程式看出相當可觀的非線性。本論文旨於兩個方面。第一，展示一種合適的系統識別方法以解釋非耦合性heliogyro 葉片的動態行為並且運用識別所得知之系統模型設計控制器。研究方法為利用非線性旋轉薄膜模型，以及其線性化模型來產生模擬資料，再利用時域以及頻域的系統識別技術來識別出系統模型。我們使用principal gain 的方法捕捉非線性所產生的不確定性，進而針對這不確定性區域進行控制器設計。結果顯示隨著系統的非線性程度提高，加上控制器後的系統所能夠達到的阻尼係數會下降。第二，在假設太陽光固定角度照射的情況下，探討太陽光壓對於實際飛行體的影響。透過推倒薄膜風帆的平面運動以及扭轉運動的耦合方程式，及完全耦合的運動方程式，我們發現耦合現象會經由太陽光壓產生耦合。

Initial studies of a heliogyro membrane blade have revealed significant nonlinearities in the equations of motion. This thesis, presents a discrete modeling approach for the NASA heligogyro concept design and the objectives of this thesis are two-fold. First, this thesis aims to offer a system identification method applicable for describing the dynamic behavior of an uncoupled heliogyro membrane blade and for control design. The approach is to use simulation data generated from linear and nonlinear models of a spinning membrane to identify linear models using time and frequency domain techniques. A controller design is introduced and its stability robustness is described. Results from the implementation of the controller reveal that the achievable level of damping is diminished by the system nonlinearities. Second, this thesis discusses the effects of solar pressure on the spacecraft blade in flight . Equations of motion for a coupled in-plane and twisting motion, and fully coupled motion with bending deformation are derived. A coupling on the twisting and in-plane motion is observed when solar radiation pressure is included.

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