US 6,799,739 B1Granted

Aircraft control surface drive system and associated methods

AssigneeThe Boeing Company

InventorKelly T. Jones

Life of this patent

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Abstract

A control surface drive system having a plurality of actuator assemblies are coupled to first and second supply lines and to a return line. The first and second supply lines are connected to a source of hydraulic fluid. At least one of the actuator assemblies has a hydraulic actuator movably connectable to an aircraft control surface. A flow control assembly is connected to the return line and to at least one of the first and second supply lines. A bypass line is in fluid communication with the first and second supply lines and positioned to recycle the hydraulic fluid from one of the first and second supply lines back into the other one of the first and second supply lines when the hydraulic actuator moves toward the first position. A computer controller operatively interconnects the plurality of actuator assemblies and the flow control assembly. It is emphasized that this abstract is provided to comply with the rules requiring an abstract. It is submitted with the understanding that it will not be used to interpret or limit the scope or meaning of the claims (37 C.F.R.§1.72(b)).

Claims36

Dependent claims

A control surface drive system for moving an aircraft control surface, the system being coupleable to a source of hydraulic fluid, comprising:

first and second supply lines and a return line coupleable to the source of hydraulic fluid;
a plurality of actuator assemblies coupled to the first and second supply lines and to the return line, at least one of the actuator assemblies having:
a hydraulic actuator connectable to the aircraft control surface and being movable between first and second positions, the hydraulic actuator configured to receive hydraulic fluid from the first supply line when the hydraulic actuator moves toward the first position, and configured to receive hydraulic fluid from the second supply line when the hydraulic actuator moves toward the second position;
a flow blocking member coupled to the first and second supply lines and being movable between an open position and a closed position, with the flow blocking member in the closed position preventing movement of the hydraulic fluid to and from the hydraulic actuator;
a flow control assembly connected to the return line and to at least one of the first and second supply lines;
a bypass line in fluid communication with the first and second supply lines and positioned to direct hydraulic fluid from one of the first and second supply lines into the other one of the first and second supply lines at a position intermediate the source and the hydraulic actuator when the hydraulic actuator moves toward the first position to recycle the hydraulic fluid back into the other one of the first and second supply lines;
and
a computer controller operatively interconnecting the plurality of actuator assemblies and the flow control assembly.

5 more elements

An aircraft system, comprising:

first and second control surfaces;
a source of hydraulic fluid;
a first control system coupled to the first control surface and a second control system coupled to the second control surface, each of the first and second control systems comprising:
first and second supply lines coupled to the source of hydraulic fluid;
a return line coupled to the source of hydraulic fluid;
a hydraulic actuator connected to at least one of the first and second aircraft control surfaces, the hydraulic actuator being movable between first and second positions, the hydraulic actuator configured to receive hydraulic fluid from the first supply line when the hydraulic actuator moves toward the first position, and configured to receive hydraulic fluid from the second supply line when the hydraulic actuator moves toward the second position;
a flow blocking member coupled to the first and second supply lines and being movable between an open position and a closed position, the flow blocking member in the closed position prevents movement of the hydraulic fluid to and from the hydraulic actuator;
a flow control assembly connected to the return line and to at least one of the first and second supply lines;
a bypass line in fluid communication with the first and second supply lines and positioned to direct hydraulic fluid from one of the first and second supply lines into the other one of the first and second supply lines upstream of the hydraulic actuator when the hydraulic actuator moves toward the first position to recycle the hydraulic fluid back into the other one of the first and second supply lines;
and
a computer controller operatively interconnecting the first and second control systems.

8 more elements

An aircraft system, comprising:

first and second aircraft control surfaces;
a source of hydraulic fluid;
a first control system coupled to the first aircraft control surface and a second control system coupled to the second aircraft control surface, each of the first and second control systems comprising:
first and second supply lines coupled to the source of hydraulic fluid;
a return line coupled to the source of hydraulic fluid;
a hydraulic actuator connected to at least one of the first and second aircraft control surfaces, the hydraulic actuator having a first port in fluid communication with the first supply line and a second port isolated from the first port and in fluid communication with the second supply line;
a first flow controller coupled to the first and second supply lines and movable between a first position that allows hydraulic fluid to move to and from the hydraulic actuator and a second position that prevents movement of the hydraulic fluid to and from the hydraulic actuator to retain the hydraulic actuator in a fixed position;
a second flow controller coupled to at least the first and second supply lines and configured to control the flow of hydraulic fluid to and from at least one of the first and second ports;
a flow control assembly connected to the first supply line and to the return line, the flow control assembly being configured to control the flow of hydraulic fluid in one direction from the first supply line to at least one of the hydraulic actuators and to control the flow of hydraulic fluid in another direction from the hydraulic actuator to the return line;
and
a bypass line in fluid communication with the first and second supply lines in a position intermediate the source and the hydraulic actuator and positioned to provide hydraulic fluid from the second supply line into the first supply line upstream of the hydraulic actuator;
and
a flight control computer operatively interconnecting the first and second control systems.

10 more elements

Dependencies are inferred from the claim text.

Facts

Application: 10/720,786Filed 24 Nov 2003
Granted: 5 Oct 2004
Term ends: Not estimatedThe source records don’t support an estimate.

Classification10 codes

B64D 45/0005
Aircraft indicators or protectors not otherwise provided for: devices specially adapted to indicate the position of a movable element of the…
B64C 13/42
Using fluid pressure: having duplication or stand-by provisions
B64D 2045/001
Devices specially adapted to indicate the position of a movable element of the aircraft, e.g. landing gear: for indicating symmetry of flaps…
Y02T 50/40
Aeronautics or air transport: weight reduction