Aircraft control surface drive system and associated methods

• US 7,506,842 B2
• Filed: 10/05/2004
• Issued: 03/24/2009
• Est. Priority Date: 11/24/2003
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Jones, Kelly T.
• Primary Examiner(s): DINH, TIEN QUANG
• Application Number:
  US10/959,629
• Publication Number:
  US 20050109876A1
• Time in Patent Office: 1,631 Days
• Field of Search: 244/78.1, 244/226, 244211-213
• US Class Current: 244/226
• CPC Class Codes: B64C 13/42 having duplication or stand-by provisions
• CPC Class Codes: B64D 2045/001 for indicating symmetry of flaps deflection
• CPC Class Codes: B64D 45/0005 Devices specially adapted to indicate the position of a movable element of the aircraft, e.g. landing gear
• CPC Class Codes: Y02T 50/40 Weight reduction
• CPC Class Codes: Y10T 137/87161 With common valve operator
• CPC Class Codes: Y10T 29/4933 Fluid coupling device

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)).

Claims

1. An actuator control system for an aircraft, comprising:

first and second aircraft control portions;

a source of fluid on the aircraft;

first and second supply lines and a return line coupleable to the source of fluid;

a fluid-driven actuator connected to at least one of the first and second control portions, the fluid-driven actuator in fluid communication with the first and second supply lines;

a flow control assembly connected to the first supply line and to the return line and configured to control the flow of fluid in one direction from the first supply line to the fluid-driven actuators and to control the flow of fluid in another direction from the fluid-driven actuator to the return line;

a bypass line connected to the first and second supply lines and positioned to provide fluid from the second supply line into the first supply line at a position intermediate the source and the flow control assembly, the bypass line being configured to allow local recycling of the fluid from the second supply line to the first supply line at the position intermediate the source and the flow control assembly to drive the actuator;

a primary power system operatively coupled to the fluid-driven actuator; and

a dedicated alternate power system coupled to the fluid-driven actuator with the alternate power system being provided for dedicated operation of the fluid-driven actuator.

2. The system of claim 1, further comprising a flow controller connected to the first and second supply lines and being movable from a first position that allows movement of the fluid-driven actuator and a second position that restricts movement of the fluid-driven actuator.

3. The system of claim 2 wherein flow controller is a blocking valve and the first position is an open position and the second position is a closed position.

4. The system of claim 1 wherein the fluid-driven actuator is a hydraulic actuator.

5. The system of claim 1, further comprising a power system having a fluid line connected to at least one of the first and second supply lines, and a pump connected to the fluid line and configured to pump fluid to the fluid-driven actuator.

6. The system of claim 1 wherein the fluid-driven actuator is movable between extended and retracted positions, the first supply line being configured to provide the fluid to move the fluid-driven actuator toward the extended position and the second supply line being configured to provide the fluid to move the fluid-driven actuator toward the retracted position.

7. The system of claim 1 wherein the flow control assembly includes a valve movable between a first position that controls a flow of fluid through the first supply line, a second position that controls a flow of fluid through the return line, and a third position that restricts flow through the first supply line and through the return line.