An aircraft propulsion system comprises a propulsor, a motor and a reduction gearbox coupled to a prime mover at an input side, and the propulsor at an output side. The reduction gearbox is configured to provide a reduction ratio between the input and output. The reduction gearbox is configured such that the input side rotates in an opposite direction to the output side, and the prime mover, motor, propulsor and reduction gearbox are configured such that gyroscopic forces of the propulsor, motor, prime mover and reduction gearbox generated during aircraft manoeuvres and/or propulsion system failures are substantially cancelled.
Aircraft propulsion system configured to substantially cancel component gyroscopic forces
05.09.2023
Patent
Elektronische Ressource
Englisch
IPC: | F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS |
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