A method (400) for an aircraft (100) is provided in one example embodiment and may include determining (402) a transition from an airplane mode to a helicopter mode for a propulsion system (110, 112) of the aircraft (100), wherein the propulsion system (110, 112) comprises a plurality of rotor blades (121, 131); determining (404) whether a descent rate condition is satisfied, wherein the descent rate condition is associated with a maximum allowable descent rate for the aircraft (100); and controlling (406) a collective pitch angle for the plurality of rotor blades (121, 131) based on the descent rate condition.
SYSTEM AND METHOD TO PROVIDE DESCENT RATE LIMITING FOR AN AIRCRAFT
SYSTEM UND VERFAHREN ZUR BEREITSTELLUNG EINER SINKGESCHWINDIGKEITSBEGRENZUNG FÜR EIN FLUGZEUG
SYSTÈME ET PROCÉDÉ POUR FOURNIR UNE LIMITATION DE TAUX DE DESCENTE POUR UN AÉRONEF
2022-03-02
Patent
Electronic Resource
English
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