Airbus Helicopters

Jean-Philippe Evrard

Alban Corpron

Cyril Passemard

A method of optimizing the performance of a rotary wing aircraft having at least one turbine engine with a gas generator and a turbine assembly comprising at least one turbine. In a definition step (STP), first and second performance levels are defined for the aircraft. During a health check step (STP), a first power margin is determined as a function of a speed of rotation of said gas generator and a second power margin is determined as a function of a temperature in said turbine assembly. During an evaluation step (STP), each power margin is compared with a first threshold in order to determine whether a target performance level is equal to the first performance level or to the second performance level. During a display step (STP), the target performance level is displayed.

Method of optimizing the performance of an aircraft, a device, and an aircraft

A method of providing a volume-mass law for determination of a fuel flow rate of an engine, particularly providing a fuel flow rate to a helicopter turbine, comprising the steps of: determining a sample type of fuel and a start density &#x3c1;of said sample type of fuel in said fuel tank using an equation &#x3c1;=aT+b, with a and bbeing known for said sample type of fuel and calculating real time offset parameters bfrom an algorithm to determine real time densities &#x3c1; of the fuel.

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Marseilles, France

Jean-Philippe Evrard