Hybrid propulsion system and method for controlling such a system
AssigneeSafran Helicopter Engines
InventorsThomas KLONOWSKI, Lois Pierre Denis VIVE, Camel SERGHINE
Life of this patent
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Abstract
A hybrid propulsion system for a multi-rotor rotary-wing aircraft, including: an internal combustion engine, an electric machine coupled to the internal combustion engine, a rectifier connected to the electric machine, a converter, an electric network connecting the rectifier to the converter, electric motors connected to the converter, rotary-blade assemblies coupled to the electric motors, wherein the system includes: a detector configured to detect a reduction in a demand for electrical power within the system to below a predetermined value, a bypass circuit configured to bypass the electric machine when the detector detects a reduction in the demand for electrical power.
Claims10
A hybrid propulsion system for a multi-rotor rotary wing aircraft, comprising:
- an internal combustion engine,
- at least one electric machine coupled to the internal combustion engine so that in operation the internal combustion engine drives the electric machine,
- a rectifier connected to the electric machine and configured to convert an alternative current delivered from the electric machine into a direct current,
- means for converting direct current into alternative current,
- an electrical network connecting the rectifier to the conversion means,
- electric motors connected to the conversion means so that in operation the conversion means supply the electric motors with alternative current,
- propellers coupled to the electric motors so that in operation the electric motors drive the propellers,
- wherein the system comprises:
- detection means configured to detect a reduction in a demand for electrical power within the system below a predetermined value,
- short-circuit means configured to short-circuit the electric machine when the detection means detects a reduction in the demand for electrical power.
Dependencies are inferred from the claim text.