METHOD AND DESIGN OF OPTIMIZED POWER TRANSMISSION BETWEEN AUXILIARY POWER ENGINE AND BASIC HELICOPTER ENGINES

摘要

1. A method for optimized energy transfer between an auxiliary engine (8) and the main engines (1, 1 ') of a helicopter containing main engines designed to provide traction energy, and an auxiliary engine designed to provide non-traction energy, characterized in that it consists on some flight steps, in addition to the power generated by the auxiliary engine (8), to the power created by the main engines (1, 1 ') by connecting the drive shaft (82) of the auxiliary engine (8) with at least at least one drive shaft (25, 25 ') and / or power transmission shaft (31, 31') of at least one main engine (1, 1 ') through at least one power matching (83, 84 , 11) .2. The method of energy transfer according to claim 1, wherein the connection of the drive shaft (82) of the auxiliary engine (8) with at least one main engine (1, 1 ') is performed on one of the shafts of this main engine selected from the drive shaft of the structure an engine with a connected turbine, a drive shaft (25, 25 ') of the gas generator (81) and / or a power transmission shaft (31, 31') of the engine design with a free turbine. 3. The method of energy transfer according to claim 1, wherein the power supply from the auxiliary engine (8) is regulated between the main engines (1, 1 ') so as to strive for equilibrium of power between these engines (1, 1'), by compensating for the asymmetric operation of these engines (1, 1 ') in the case when this asymmetry is caused unintentionally due to a partial malfunction of one of the engines, and by approaching a loaded engine in the case of intentional asymmetry, depending on the stages of the helicopter's flight mission. 4. The method of energy transfer according to any one of paragraphs. 1-3, in which mechanical