| タイトル | Real-Time Adaptive Control Allocation Applied to a High Performance Aircraft |
| 本文（外部サイト） | http://hdl.handle.net/2060/20040086083 |
| 著者（英） | Davidson, John B.; Lallman, Frederick J.; Bundick, W. Thomas |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 2001-01-01 |
| 言語 | eng |
| 内容記述 | Abstract This paper presents the development and application of one approach to the control of aircraft with large numbers of control effectors. This approach, referred to as real-time adaptive control allocation, combines a nonlinear method for control allocation with actuator failure detection and isolation. The control allocator maps moment (or angular acceleration) commands into physical control effector commands as functions of individual control effectiveness and availability. The actuator failure detection and isolation algorithm is a model-based approach that uses models of the actuators to predict actuator behavior and an adaptive decision threshold to achieve acceptable false alarm/missed detection rates. This integrated approach provides control reconfiguration when an aircraft is subjected to actuator failure, thereby improving maneuverability and survivability of the degraded aircraft. This method is demonstrated on a next generation military aircraft Lockheed-Martin Innovative Control Effector) simulation that has been modified to include a novel nonlinear fluid flow control control effector based on passive porosity. Desktop and real-time piloted simulation results demonstrate the performance of this integrated adaptive control allocation approach. |
| NASA分類 | Aircraft Stability and Control |
| 権利 | Copyright, Distribution under U.S. Government purpose rights |
