| タイトル | Output feedback non-linear decoupled control synthesis and observer design for manoeuvring aircraft |
| 著者（英） | Schy, A. A.; Singh, S. N. |
| 著者所属（英） | Santa Catarina Univ.|NASA Langley Research Center |
| 発行日 | 1980-04-01 |
| 言語 | eng |
| 内容記述 | A study of the applicability of nonlinear decoupling theory to the design of control systems using output feedback for maneuvering aircraft is presented. The response variables chosen for decoupled control were angular velocity components along roll, pitch, and yaw axes, angle of attack (p), and angle of sideslip, using aileron, rudder, and elevator controls. An observer design for a class of nonlinear systems was presented and this method was used to estimate angle of attack and sideslip; an approximate observer was obtained by neglecting derivatives of p and aileron deflection angles and it was used in a simulation study. A simulation study showed that precise rapid combined lateral and longitudinal maneuvers can be performed; it was also demonstrated that a bank-angle-command outer loop could be designed for precise bank angles changes and simultaneous large lift maneuvers. |
| NASA分類 | AIRCRAFT STABILITY AND CONTROL |
| レポートNO | 80A36645 |
| 権利 | Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/421648 |
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