| 摘要 |
<p>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.</p> |
