AIRCRAFT DRIVE SYSTEM

The present invention includes an aircraft drive system (200) comprising a main rotor gearbox (214) comprising a first and a second input; a first drive system comprising a first engine reduction gearbox (216a) connecting a first engine to the first input of the main rotor gearbox (214) at a reduced...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	POSTER, Scott David, RILEY, Walter, COPE, Gary, SPELLER JR, Charles Hubert
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AEROPLANES AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION BLASTING COSMONAUTICS ENGINEERING ELEMENTS AND UNITS EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS GEARING GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS HEATING HELICOPTERS LIGHTING MECHANICAL ENGINEERING PARACHUTES PERFORMING OPERATIONS THERMAL INSULATION IN GENERAL TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	The present invention includes an aircraft drive system (200) comprising a main rotor gearbox (214) comprising a first and a second input; a first drive system comprising a first engine reduction gearbox (216a) connecting a first engine to the first input of the main rotor gearbox (214) at a reduced shaft speed; and a second drive system independent from and redundant with the first drive system, the second drive system comprising a second engine reduction gearbox (216b) connecting a second engine to the second input of the main rotor gearbox (214) at the reduced shaft speed.