AIRCRAFT ACTUATOR HYDRAULIC SYSTEM

PROBLEM TO BE SOLVED: To drive a control surface by a single actuator even when a loss or degradation in a function of an airframe side hydraulic power source and miniaturize a high output power actuator at low cost to install the actuator inside a thin wing.SOLUTION: A first actuator 14a drives the...

Ausführliche Beschreibung

Gespeichert in:

Bibliographische Detailangaben
Hauptverfasser:	FUKUI ATSUSHI, TAKAGI NORIMASA
Format:	Patent
Sprache:	eng
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
Online-Zugang:	Volltext bestellen
Tags:	Tag hinzufügen Keine Tags, Fügen Sie den ersten Tag hinzu!

Beschreibung
Zusammenfassung:	PROBLEM TO BE SOLVED: To drive a control surface by a single actuator even when a loss or degradation in a function of an airframe side hydraulic power source and miniaturize a high output power actuator at low cost to install the actuator inside a thin wing.SOLUTION: A first actuator 14a drives the control surface 103a by being operated by supply of pressure oil from a first airframe side hydraulic pump 104a of a first airframe side hydraulic power source 104. A second actuator 14b drives the control surface 103a by being operated by supply of pressure oil from a second airframe side hydraulic pump 105a of a second airframe side hydraulic power source 105. A backup hydraulic pump 18 is installed inside the wing 102a of an aircraft 100 and is provided so as to be able to supply pressure oil to the first actuator 14a when a loss or degradation in a function of at least one of the first airframe side hydraulic power source 104 and the second airframe side hydraulic power source 105 occurs. A maximum discharge pressure of the backup hydraulic pump 18 is set to be greater than maximum discharge pressures of the first airframe side hydraulic pump 104a and the second airframe side hydraulic pump 105a.