2 edition of Evaluation of potential changes to the Space Shuttle Orbiter"s Flight Control System to increase directional control during post landing rollout found in the catalog.
by Naval Postgraduate School, Available from National Technical Information Service in Monterey, Calif, Springfield, Va
Written in English
Space Shuttle Orbiter landings indicate both long term directional instability and the potential for pilot induced oscillations during landing and rollout before nosewheel touchdown. The Orbiter"s Flight Control System requires improvements to increase directional control in the two points stance (after main gear touchdown with the nose in the air). A number of modifications are proposed to improve directional control. This thesis describes the control deficiency, potential improvements to the Flight Control System (FCS), and evaluates a number of these improvements. The evaluation was performed by modeling the Orbiter"s postlanding lateral/directional control laws using a commercially available engineering software package known as MATLAB 5.0. Directional control of the Orbiter was evaluated with and without the proposed modification to obtain a comparison of control response. Initial evaluation of future Orbiter FCS modifications could be performed using commercially available engineering software packages such as MATLAB; rather than costly full-up Orbiter simulators. A low cost initial evaluation of changes may save NASA resources.
|Statement||Linda J. Ham|
|Contributions||Naval Postgraduate School (U.S.)|
|The Physical Object|
|Pagination||xvi, 113 p. ;|
|Number of Pages||113|
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