Verfahren, Vorrichtung zur Unterstützung der Steuerung eines Luftfahrzeugs, und Luftfahrzeug

Details

Veröffentlichungs-Nr.

EP2505502

Aktenzeichen

EP12001762

Anmeldetag

15. März 2012

Veröffentlichung

16. Oktober 2013

Erteilung

16. Oktober 2013

Rechtsraum

EP

IPC

B64D35/04B64D43/00G01D7/02G01D7/10

Abstract

The method involves displaying an index (63) pointing to current collective pitches of respective rotor blades (6, 8) in a diagram (60), by a computer (40). A limiting parameter corresponding to a monitoring parameter that is closest to its limit in a current operating rating of engines (2, 3), is determined. Available power margins for the engines are determined. A power limit curve (70) per power margin is determined, and displayed in the diagram to inform a pilot about first and second collective pitch margins that are available before reaching a limit for each of engine operating ratings. Each power margin corresponds to the power to be delivered for causing the limiting parameter to reach the limit associated with the corresponding rating. The ratings include a takeoff rating, a maximum continuous rating, a transient rating, and three emergency ratings. The monitoring parameter is chosen from rotating speed of gas generator of the engines, engine torque, and temperature of gas at an inlet to a free turbine of the engines, where the engines are free-turbine turboshaft engines. Independent claims are also included for the following: (1) a device for assisting the piloting of an aircraft (2) an aircraft.

Anmelder

Firmen

Airbus Helicopters
EUROCOPTER

Land

🇫🇷 Frankreich

Fachgebiete