Patent ID: 7636054

Claim:
A flight control indicator for an aircraft, intended to provide a power parameter pertaining to at least one turboprop of said aircraft, said turboprop comprising a gas turbine driving the rotation of at least one propeller, said flight control indicator ( 1 ) comprising: data sources ( 2 ) which determine at least the values of parameters relating to the aircraft; data processing means ( 3 ) for processing the data received from said data sources ( 2 ); and display means ( 5 ) capable of displaying, on at least one display screen ( 7 ), data from said processing means ( 3 ), and at least one characteristic sign ( 11 ) illustrating said power parameter, wherein: said data sources ( 2 ) additionally determine the values of parameters relating to the propeller and to the turbine of the turboprop; said processing means ( 3 ) calculate, from the values determined by said data sources ( 2 ), a power parameter that takes account of the ratio between the current power of the turboprop and the maximum power obtained without air bleed at sea level in a standard atmosphere; and said processing means ( 3 ) calculate said power parameter PIT using the following expression: PIT= 100. A. ( TQc.NPc−PWRr )/( PWR max− PWR r) in which: A corresponds to the sign of β-β 0 , β representing the current measured angle of incidence of the blades of the propeller of the turboprop, and β 0 representing the angle of incidence of said blades on the ground at idle; TQc represents the current torque on the shaft of the free turbine; NPc represents the current measured speed of the propeller of the turboprop, the product TQc.NPC forming said current power; PWRmax represents said maximum power; and PWRr represents a predetermined reference power.