The invention aims to optimise all of the engine power available on a helicopter provided with an auxiliary engine by allowing that auxiliary engine to provide non-propulsive and/or propulsive energy during flight. For this purpose, this auxiliary engine is coupled in such a way as to be able to directly contribute to the supply of propulsive mechanical or electrical energy and non-propulsive electrical energy of the aircraft. An example configuration architecture comprises an onboard electrical network (2), two main engines (5a, 5b) and an energy conversion system for converting mechanical/electrical energy (6, 6a, 6b, 7) between a main gearbox BTP (40) transferring power to the propulsion members (4, 41) and means for receiving electrical energy comprising the onboard network (2) and a power electronics system (9) linked with starters (8) of the main engines (5a, 5b). The configuration also comprises an auxiliary power engine (3) supplying electrical energy to the means for receiving electrical energy (2, 9) via the energy conversion system (6, 6a, 6b, 7) and mechanical coupling means (8a, 11a to 11d) between the auxiliary engine (3, 0, 30) and at least one propulsion means (4, 41).


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    Title :

    Method and configuration for an auxiliary power engine to deliver propulsive and/or non-propulsive energy in a helicopter architecture


    Contributors:

    Publication date :

    2015-04-01


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / B64C AEROPLANES , Flugzeuge



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