Methods and systems for operating aircraft landing gears

• US 7,093,795 B2
• Filed: 11/30/2004
• Issued: 08/22/2006
• Est. Priority Date: 02/09/2004
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Lindahl, Gary M., Trotter, Steven J.
• Primary Examiner(s): Swiatek, Robert P.
• Application Number:
  US11/000,167
• Publication Number:
  US 20060027706A1
• Time in Patent Office: 630 Days
• Field of Search: 244/81, 244/100.R, 244/102.R, 244/102.A, 244/102.SL, 244/190
• US Class Current: 244/102.00R
• CPC Class Codes: B64C 25/16 Fairings movable in conjunction with undercarriage elements
• CPC Class Codes: B64C 25/18 Operating mechanisms
• CPC Class Codes: B64C 25/22 fluid
• CPC Class Codes: B64C 25/28 with indicating or warning devices

Abstract

Methods and systems for performing landing gear operations. In one embodiment, a method for retracting a landing gear is useable with an aircraft having a gear door that at least partially covers a gear well when the landing gear is extended. The method can include receiving a first signal during movement of the aircraft down a runway for takeoff. The first signal can correspond to at least a first aspect of motion of the aircraft, such as upward rotation of the aircraft for liftoff. The gear door can be opened in response to receiving the first signal. The method can further include receiving a second signal after the aircraft has lifted off of the runway. The second signal can correspond to a second aspect of motion of the aircraft, such as the aircraft achieving a positive rate of climb. In response to receiving the second signal, the landing gear can be retracted into the gear well.

Claims

1. An aircraft system comprising:

landing gear movable between an extended position and a retracted position, wherein the landing gear is at least partially stowed in a gear well when the landing gear is in the retracted position;

a landing gear door movable between an open position and a closed position, wherein the landing gear door at least partially covers the gear well when the landing gear door is in the closed position;

at least a first actuator operably coupled to the landing gear and configured to move the landing gear between the extended position and the retracted position;

at least a second actuator operably coupled to the landing gear door and configured to move the landing gear door between the open position and the closed position; and

a controller operably coupled to the first and second actuators, wherein the controller causes the second actuator to open the gear door in response to a first signal, and wherein the controller further causes the first actuator to retract the landing gear in response to a second signal different from the first signal.

2. The aircraft system of claim 1 wherein the controller causes the second actuator to open the gear door in response to an automatically generated signal, and wherein the controller further to causes the first actuator to retract the landing gear in response to a manually generated signal.

3. The aircraft system of claim 1 wherein the controller causes the second actuator to open the gear door in response to a signal that is automatically generated by an aspect of aircraft motion, and wherein the controller further causes the first actuator to retract the landing gear in response to a signal that is manually generated.

4. The aircraft system of claim 1 wherein the controller causes the second actuator to open the gear door in response to a signal that is automatically generated by aircraft rotation, and wherein the controller is further the first actuator to retract the landing gear in response to a signal that is manually generated when the aircraft achieves a positive rate of climb.

5. The aircraft system of claim 1 wherein the first and second actuators are hydraulic actuators, wherein the aircraft system further comprises a hydraulic system operably coupled to the first and second actuators, and wherein the controller is operably coupled to the hydraulic system, the controller causing the hydraulic system to move the second actuator and open the gear door in response to a first signal, the controller further causing the hydraulic system to move the first actuator and retract the landing gear in response to a second signal different from the first signal.

6. The aircraft system of claim 5 wherein the controller level-loads the hydraulic system during retraction of the landing gear and closure of the gear door such that the flow of hydraulic fluid is maintained at or below an at least approximately constant level.

7. An aircraft comprising:

a fuselage;

a passenger cabin positioned in the fuselage;

a wing extending outwardly from the fuselage;

a landing gear attached to the wing, the landing gear being movable between an extended position and a retracted position, wherein the landing gear is at least partially stowed in a gear well when the landing gear is in the retracted position;

a landing gear door movable between an open position and a closed position, wherein the landing gear door at least partially covers the gear well when the landing gear door is in the closed position;

at least a first actuator operably coupled to the landing gear and configured to move the landing gear between the extended position and the retracted position;

at least a second actuator operably coupled to the landing gear door and configured to move the landing gear door between the open position and the closed position; and

a controller operably coupled to the first and second actuators, wherein the controller causes the second actuator to open the gear door in response to an automatically generated signal, and wherein the controller further causes the first actuator to retract the landing gear in response to a manually generated signal.

8. The aircraft system of claim 7 wherein the controller causes the second actuator to open the gear door in response to a signal that is automatically generated by an aspect of aircraft motion.

9. The aircraft system of claim 7 wherein the controller causes the second actuator to open the gear door in response to a signal that is automatically generated by aircraft rotation.

10. The aircraft system of claim 7 wherein the controller causes the second actuator to open the gear door in response to a signal that is automatically generated when weight is lifted off of the landing gear.

11. The aircraft system of claim 7 wherein the controller causes the first actuator to retract the landing gear in response to a signal that is manually generated when the aircraft achieves a positive rate of climb.

12. The aircraft system of claim 7 wherein the first and second actuators are hydraulic actuators, wherein the aircraft system further comprises a hydraulic system operably coupled to the first and second actuators, and wherein the controller is operably coupled to the hydraulic system, the controller causing the hydraulic system to move the second actuator and open the gear door in response to a first signal, the controller further causing the hydraulic system to move the first actuator and retract the landing gear in response to a second signal different from the first signal.

13. The aircraft system of claim 12 wherein the controller level-loads the hydraulic system during retraction of the landing gear and closure of the gear door such that the flow of hydraulic fluid is maintained at or below an at least approximately constant level.