A method of preserving rotor speed during a one engine inoperative operation of an rotorcraft, the method can include: detecting a failure of a first engine; monitoring an engine parameter associated with a second engine; using a computer processor to compare the engine parameter to an engine limit; and commanding a decrease collective pitch command when the engine parameter is within a predefined range of the engine limit.
System and method for maximizing aircraft safe landing capability during one engine inoperative operation
2017-02-14
Patent
Electronic Resource
English
European Patent Office | 2016
|OPERATING AIRCRAFT PROPULSION SYSTEM DURING ENGINE-INOPERATIVE EVENT
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