Controlling movement of landing gear or landing gear bay doors

Patent metadata

Field	Value
Publication number	US-12017755-B2
Application number	US-202017435355-A
Country	US
Kind code	B2
Filing date	Jun 23, 2020
Priority date	Jun 27, 2019
Publication date	Jun 25, 2024
Grant date	Jun 25, 2024

Abstract

A method of operating a landing gear controller for an aircraft, including: the landing gear controller receiving one or more signals from at least one position sensor. The one or more signals indicate a position of one of a landing gear bay door and a landing gear when the landing gear bay door or the landing gear, respectively, is part way through a range of travel between two limits of travel. The method may also include the landing gear controller controlling movement of the other of the landing gear bay door and the landing gear on the basis of the one or more signals.

First claim

The invention claimed is:

1. An aircraft system including:
a landing gear bay door,
a landing gear bay door movement system configured to move the landing gear bay door over a first range of travel between a closed position and an open position of the landing gear bay door, wherein the landing gear bay door at least partially covers a landing gear bay when in the closed position;
a landing gear, and
a landing gear movement system configured to move the landing gear over a second range of travel between an extended position and a retracted position of the landing gear, wherein the landing gear is at least partially positioned in the landing gear bay when in the retracted position;
a first position sensor configured to output a first signal indicating a first position of the landing gear bay door part way through the first range;
a second position sensor configured to output a second signal indicating a second position of a part of the landing gear part way through the second range, and
a landing gear controller communicably connected to the first position sensor and the second position sensor, and the landing gear controller operably connected to the landing gear bay door movement system and to the landing gear movement system, wherein the landing gear controller is configured, in use, to:
receive the first signal and the second signal, and
determine, based on the first signal and the second signal, a first relative position of the landing gear bay door relative to the landing gear or a second relative position of the landing gear relative to the landing gear bay door, and
actuate the landing gear movement system to control movement of the landing gear through the second range based on the first relative position or the second relative position, or
actuate the landing gear bay door movement system to control movement of the landing gear bay door through the first range based on the first relative position or the second relative position.

2. The aircraft system according to claim 1 , wherein, the landing gear controller is further configured to, based on the first signal or the second signal, vary a speed of movement of the landing gear bay door or a speed of movement of the landing gear by controlling operation of the landing gear bay door movement system or the landing gear movement system, respectively.

3. The aircraft system according to claim 2 , wherein the landing gear bay door movement system comprises one or more rate-controllable actuators operable to move the landing gear bay door through the first range, and the landing gear movement system comprises one or more rate-controllable actuators operable to move the landing gear through the second range;
wherein, based on the first signal or the second signal, the landing gear controller is configured to vary the speed of movement of the landing gear bay door or the speed of movement of the landing gear by controlling an actuation rate of the one or more rate-controllable actuators of the landing gear bay door movement system or the landing gear movement system, respectively.

4. The aircraft system according to claim 2 , wherein the landing gear controller is configured to vary the speed of movement of the landing gear bay door based on the speed of movement of the landing gear or the second relative position, or
vary the speed of movement of the landing gear based on the first relative position or the speed of movement of the landing gear bay door.

5. The aircraft system according to claim 1 , wherein:
the first position sensor continuously or repeatedly outputs the first signal as the first position sensor continuously or repeatedly senses the position of the landing gear bay door as the landing gear bay door is moving over the first range; and
the second position sensor continuously or repeatedly outputs the second signal as the second position sensor continuously or repeatedly senses the position of the part of the landing gear as the part of the landing gear is moving over the second range; and
wherein the landing gear controller is configured, in use, to receive the first signal and the updated second signal continuously or repeatedly output by the first position sensor and the second position sensor.

6. The aircraft system according to claim 1 , wherein:
the landing gear controller is configured to:
determine a landing gear bay door speed of movement through the first range or a landing gear speed of movement through the second range based on the first signal or the second signal which are continuously or repeatedly output by the at least one position sensor; and
control the movement of the landing gear bay door based on the landing gear bay door speed of movement, or the movement of the landing gear based on the landing gear speed of movement.

7. The aircraft system according to claim 1 , wherein, the landing gear controller is further configured to initiate movement of the landing gear bay door or the landing gear by controlling operation of the landing gear bay door movement system or the landing gear movement system, respectively based on the first signal or the second signal.

8. The aircraft system according to claim 1 , wherein the first position sensor or the second position sensor is configured to sense one or more of: an angular position, a linear position, and a curvilinear position of the landing gear bay door or the landing gear.

9. A method of operating a landing gear controller for an aircraft, the method comprising the landing gear controller:
receiving a first signal from at least one relative position sensor indicating a first relative position of a landing gear bay door relative to a landing gear or receiving a second signal from the relative position sensor indicating a second relative position of the landing gear relative to the landing gear bay door, wherein the at least one relative position sensor generates the first signal or the second signal as the landing gear bay door moves part way through a first range between a closed position and an open position and as the landing gear moves part way through a second range between a deployed position and a retracted position, and; and
actuate a landing gear movement system to control movement of the landing gear through the second range based on the first relative position or the second relative position, or
actuate a landing gear bay door movement system to control movement of the landing gear bay door through the first range based on the first relative position or the second relative position.

10. The method according to claim 9 , further comprising:
receiving one or more additional signals, and
controlling the movement of the landing gear bay door or the landing gear based on the one or more additional signals.

11. The method according to claim 10 , wherein the one or more additional signals are indicative of one or more of:
a pitch of a landing gear bogie,
a status of another landing gear or another landing gear bay door,
a status of one or more aircraft engines,
failure or a defect of an aircraft component or an aircraft system, and
an aircraft crab angle.

12. The method according to claim 9 , further comprising initiating the movement of the landing gear bay door through the first range while the landing gear is part way in the second range or initiating movement of the landing gear through the second range the while the landing gear bay door is part way in the first range.

13. A non-transitory computer-readable storage medium storing instructions that, if executed by a processor, of the landing gear controller to cause the processor to carry out the method according to claim 9 .

Assignees

• Airbus Operations Ltd

Inventors

• Kerr Sean
• Marles David

Classifications

• B64C25/26 Primary

  Control or locking systems therefor · CPC title

• B64C25/12 Primary

  sideways · CPC title

• B64C2025/125

  into the fuselage, e.g. main landing gear pivotally retracting into or extending out of the fuselage · CPC title

• B64C25/20

  mechanical · CPC title

• B64C25/16 Primary

  Fairings movable in conjunction with undercarriage elements · CPC title