DISTRIBUTED TRAILING EDGE WING FLAP SYSTEMS

A wing flap system (300) for an aircraft, comprising four flaps (112,114,118,120) configured to be moved between respective deployed positions and respective retracted positions, the flaps being configured to be moved relative to fixed trailing edges (110,116) of the wings (102,104) of the aircraft,...

Ausführliche Beschreibung

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Bibliographische Detailangaben
1. Verfasser:	HUYNH, Neal V
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AEROPLANES AIRCRAFT AVIATION BLASTING COSMONAUTICS DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR FLUID-PRESSURE ACTUATORS FLUID-PRESSURE ACTUATORS, e.g. SERVO-MOTORS HEATING HELICOPTERS HYDRAULICS OR PNEUMATICS IN GENERAL LIGHTING MECHANICAL ENGINEERING PERFORMING OPERATIONS SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	A wing flap system (300) for an aircraft, comprising four flaps (112,114,118,120) configured to be moved between respective deployed positions and respective retracted positions, the flaps being configured to be moved relative to fixed trailing edges (110,116) of the wings (102,104) of the aircraft, eight actuators (302,304,306,308,310,312,314,316) configured to move the flaps relative to the fixed trailing edges, respective ones of the actuators being configured to be hydraulically driven via first pressurized hydraulic fluid to be supplied by a first hydraulic system (334) of the aircraft, respective ones of the actuators being configured to be hydraulically driven via second pressurized hydraulic fluid to be supplied by a second hydraulic system (338) of the aircraft; and four local power units, four of the actuators being configured to be independently hydraulically driven via pressurized hydraulic fluid to be supplied by the local power units.