Redundant tail rotor control system

A flight control system for a helicopter tail rotor having a semicircular quadrant 18 with bell cranks 36, 40 mounted on either end of the quadrant and flexible control cables 20, 22 connected to each bell crank. The bell cranks are spring loaded in opposition to cable tension, and a fixed abutment...

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Bibliographische Detailangaben
Hauptverfasser:	BRAMWELL, FRANK, MACLENNAN, RODERICK A
Format:	Patent
Sprache:	eng
Schlagworte:	AEROPLANES AIRCRAFT AVIATION COSMONAUTICS GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS HELICOPTERS PERFORMING OPERATIONS TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION TECHNICAL SUBJECTS COVERED BY FORMER USPC TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS TRANSPORTING
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Beschreibung
Zusammenfassung:	A flight control system for a helicopter tail rotor having a semicircular quadrant 18 with bell cranks 36, 40 mounted on either end of the quadrant and flexible control cables 20, 22 connected to each bell crank. The bell cranks are spring loaded in opposition to cable tension, and a fixed abutment 72 provides a reaction against the bell crank springs in the event of a cable severance. The quadrant works against the spring loading of one bell crank in the event of breakage of the opposite control cable and is centered by the spring loading of both bell cranks if both cables are broken.