A method for providing adaptive control to a fly-by-wire aircraft includes measuring via at least one first sensor a characteristic of at least one component of the aircraft and measuring via at least one second sensor a state of the aircraft. Using the characteristic of at least one component and the state of the aircraft, a determination of at least one of an actual damage and remaining life of the at least one component is made. The operational envelope of the aircraft is adapted based on the at least one of actual damage and remaining life of the at least one component. Adapting the operational envelope includes adjusting an outer boundary thereof to prohibit operation exceeding a safe operation threshold and generating an intermediate boundary of the operational envelope. Operation of the aircraft within the intermediate boundaries minimizes further damage accrual of the at least one component.
ADAPTIVE CONTROL OF AIRCRAFT USING STRUCTURAL HEALTH MONITORING
2020-04-02
Patent
Electronic Resource
English
IPC: | G05D SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES , Systeme zum Steuern oder Regeln nichtelektrischer veränderlicher Größen / B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen |
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