Control system and method for landing gear extension/retraction

Patent metadata

Field	Value
Publication number	US-11136114-B2
Application number	US-201916556651-A
Country	US
Kind code	B2
Filing date	Aug 30, 2019
Priority date	Mar 2, 2017
Publication date	Oct 5, 2021
Grant date	Oct 5, 2021

Abstract

A control system has first and second processing modules for controlling retraction and extension of an aircraft landing gear assembly. The processing modules operate independently providing redundancy. Each processing module is configured to perform a first sequence of steps for retracting the landing gear assembly and a second sequence of steps for extending the landing gear assembly. A step of switching control from one processing module to the other (e.g. an avionics side changeover step) is performed (a) as part of the first sequence of steps, but only after the landing gear assembly has been retracted, or (b) as part of the second sequence of steps. By ensuring that the step of switching control is performed at such times, and not for example between initiation of the first sequence of steps and the retraction of the landing gear assembly, the landing gear assembly may be retracted sooner after such initiation.

First claim

The invention claimed is:

1. A control system for retracting and extending a landing gear assembly in an aircraft, comprising:
a first one or more processor and a second one or more processor, each of the first and second processors being configured to control retraction and extension of the landing gear assembly independently, thus, providing redundancy;
each of the first and second processors being further configured to perform a first sequence of steps for retracting the landing gear assembly and a second sequence of steps for extending the landing gear assembly; and
at least one of the first sequence of steps and the second sequence of steps comprising a step of switching control between the first one or more processors and the second one or more processors, and wherein
the step of switching control is performed
(a) as part of the first sequence of steps for retracting the landing gear assembly, but only after the landing gear assembly has been retracted, or
(b) as part of the second sequence of steps for extending the landing gear assembly.

2. The control system according to claim 1 , wherein each of the first and second processors is configured such that the first sequence of steps for retracting the landing gear assembly does not include a step of switching control before the landing gear assembly has been retracted.

3. The control system according to claim 1 , wherein each of the first and second processors is configured such that the step of switching control is performed as part of the second sequence of steps for extending the landing gear assembly and is performed before the landing gear assembly starts moving from its retracted position to its extended position.

4. The control system according to claim 3 , wherein:
each of the first and second processors is configured to perform, during the second sequence of steps but before the landing gear assembly starts moving from its retracted position to its extended position, a step of issuing a control signal that causes one or more landing gear bay doors to open; and
each of the first and second processors is configured such that the step of switching control is performed before the step of issuing the control signal that causes the landing gear bay door(s) to open.

5. The control system according to claim 4 , wherein:
each of the first and second processors is configured to perform, during the second sequence of steps but before step of issuing the control signal that causes the landing gear bay door(s) to open, a step of issuing a control signal that causes unlocking of the landing gear bay door(s); and
each of the first and second processors is configured such that the step of switching control is performed before the step of issuing the control signal that causes unlocking of the landing gear bay door(s).

6. The control system according to claim 3 , wherein:
each of the first and second processors is configured such that the step of switching control is performed immediately after receipt of a control signal or other input that initiates the second sequence of steps for extending the landing gear assembly.

7. The control system according to claim 1 , wherein each of the first and second processors is configured to perform, during the first sequence of steps but after the landing gear assembly has been retracted, a step of issuing a control signal that causes one or more landing gear bay doors to close, and
each of the first and second processors is configured such that the step of switching control is performed as part of the first sequence of steps for retracting the landing gear assembly, but after the step of issuing the control signal that causes landing gear bay door(s) to close.

8. The control system according to claim 7 , wherein:
each of the first and second processors is configured to perform, during the first sequence of steps but after the step of issuing the control signal that causes the landing gear bay door(s) to close, a step of causing and/or detecting locking of the landing gear bay door(s), and
each of the first and second processors is configured such that the step of switching control is performed after the step of causing and/or detecting locking of the landing gear bay door(s).

9. The control system according to claim 1 , wherein each of the first and second processors is configured such that the step of switching control is performed as part of the second sequence of steps for extending the landing gear assembly, but only after the landing gear assembly has been extended.

10. The control system according to claim 9 , wherein each of the first and second processors is configured to perform, during the second sequence of steps but after the landing gear assembly has been extended, a step of issuing a control signal that causes one or more landing gear bay doors to close, and
wherein each of the first and second processors is configured such that the step of switching control is performed after the step of issuing the control signal that causes landing gear bay door(s) to close.

11. The control system according to claim 10 , wherein:
each of the first and second processors is configured to perform, during the second sequence of steps but after the step of issuing the control signal that causes the landing gear bay door(s) to close, a step of causing and/or detecting locking of the landing gear bay door(s), and
each of the first and second processors is configured such that the step of switching control is performed after the step of causing and/or detecting locking of the landing gear bay door(s).

12. An aircraft comprising a control system according to claim 1 , and a retractable landing gear assembly.

13. A method of switching control of landing gear extension/retraction between a first avionics control system and a second avionics control system, wherein the method comprises:
using a control system for retracting and extending a landing gear assembly in an aircraft, the control system comprising:
a first one or more processors and a second one or more processors, each of the first and second processors being configured to control retraction and extension of the landing gear assembly independently thus providing redundancy;
each of the first one or more processors and the second one or more processors being further configured to perform a first sequence of steps for retracting the landing gear assembly and a second sequence of steps for extending the landing gear assembly; and
at least one of the first sequence of steps and the second sequence of steps comprising a step of switching control between the first one or more processors and the second one or more processors, and wherein
the step of switching control is performed
(a) as part of the first sequence of steps for retracting the landing gear assembly, but only after the landing gear assembly has been retracted, or
(b) as part of the second sequence of steps for extending the landing gear assembly; and

wherein the first one or more processors forms a part of the first avionics control system and the second one or more processors forms a part of the second avionics control system.

14. A processing module programmed with a non-transitory computer program to perform steps comprising:
using a control system for retracting and extending a landing gear assembly in an aircraft, the control system comprising:
a first one or more processors and a second one or more processors, each of the first and second one or more processors being configured to control retraction and extension of the landing gear assembly independently thus providing redundancy;
each of the processors bein

Assignees

• Airbus Operations Ltd

Inventors

• Rowlands Martin Griffith
• Jones Maxwell William
• King Graham
• Brighton Trevor Anthony
• Gadd Matthew

Classifications

• B64C25/26 Primary

  Control or locking systems therefor · CPC title

• B64C25/16

  Fairings movable in conjunction with undercarriage elements · CPC title