Aircraft take-off system

Patent metadata

Field	Value
Publication number	US-12214866-B2
Application number	US-202017760940-A
Country	US
Kind code	B2
Filing date	Sep 16, 2020
Priority date	Sep 17, 2019
Publication date	Feb 4, 2025
Grant date	Feb 4, 2025

Abstract

An aircraft system ( 10 ) for an aircraft ( 1 ) including a controller ( 100 ) configured to receive at least one signal during a take-off procedure of the aircraft. The signal includes information representative of at least one parameter of the aircraft. The controller is configured to determine whether a current or future aircraft climb rate associated with the take-off procedure meets a criterion, on the basis of the at least one signal. The controller is configured to determine at least one remedial action to be taken, such as performance of at least a portion of a procedure to retract a landing gear of the aircraft, when the controller determines that the aircraft climb rate does not meet the criterion.

First claim

The invention claimed is:

1. An aircraft system for an aircraft, the aircraft system comprising a controller configured to:
receive at least one signal during a take-off procedure of the aircraft indicative of a fault or failure of an engine of the aircraft; and
on the basis of the at least one signal, causing at least one remedial action to be taken to increase a rate of climb of the aircraft, wherein the at least one remedial action includes performing a portion of a retraction procedure to retract a landing gear of the aircraft,
wherein the at least one signal indicates that an operating condition of the engine is beyond a predetermined range or a predetermined threshold.

2. The aircraft system according to claim 1 , further comprising one or more landing gear bay door actuators configured to move a landing gear bay door from a closed position to an open position to permit movement of the landing gear from an extended position to a retracted position;
wherein the portion of the retraction procedure comprises the one or more landing gear bay door actuators moving the landing gear bay door from the closed position to the open position.

3. The aircraft system according to claim 1 , further comprising one or more landing gear actuators configured to move the landing gear from an extended position to a retracted position;
wherein the controller is configured to determine when the aircraft leaves the ground, and
wherein the portion of the retraction procedure comprises the one or more landing gear actuators moving the landing gear from the extended position to the retracted position in response to the controller determining that the aircraft has left the ground.

4. The aircraft system according to claim 1 , further comprising a sensor system configured to sense a parameter of the aircraft relating to the engine and to send to the controller the at least one signal comprising information representative of the parameter.

5. The aircraft system according to claim 1 , further comprising:
a movable landing gear lever in a cockpit of the aircraft, and
a warning device in the cockpit;
wherein the controller is configured to cause the warning device to issue a warning in response to the controller determining that a current physical position of the landing gear conflicts with a current physical position of the landing gear lever.

6. An aircraft comprising the aircraft system according to claim 1 .

7. The aircraft system of claim 1 , wherein the portion of the retraction procedure includes an avionics side change over.

8. The aircraft system of claim 1 , further comprising an isolator configured to supply power to the landing gear, and
wherein the portion of the retraction procedure includes operation of the isolator to apply power to the landing gear.

9. The aircraft system of claim 1 , wherein the controller is further configured to:
receive at least one additional signal during the take-off procedure indicative of a climb rate of the aircraft;
determine if the climb rate meets a climb rate criterion,
confirm the performance of the at least the portion of the retraction procedure if the climb rate does not meet the criterion, and
inhibit the performance of the at least the portion of the retraction procedure if the climb rate meets the criterion.

10. A method of operating a controller of an aircraft system of an aircraft during a take-off procedure, the method comprising the controller automatically:
receiving a signal indicative of a fault or failure of an engine in the aircraft during the take-off procedure; and
causing a remedial action to be taken in response to the signal, wherein the remedial action includes performing at least a portion of a retraction procedure to retract a landing gear of the aircraft,
wherein the at least one signal indicates that an operating condition of the engine is beyond a predetermined range or a predetermined threshold.

11. The method according to claim 10 , wherein the at least one signal comprises engine parameter information representative of at least one of:
a temperature or pressure of engine oil in the engine;
a vibration of at least part of the engine;
a spool speed of the engine;
a temperature of exhaust gas from the engine; or
an engine pressure ratio of the engine.

12. The method of claim 10 , further comprising:
receiving at least one additional signal during the take-off procedure indicative of a climb rate of the aircraft;
determining if the climb rate meets a climb rate criterion,
performing the at least the portion of the retraction procedure if the climb rate does not meet the criterion, and
not performing the at least the portion of the retraction procedure if the climb rate meets the criterion.

13. An aircraft system for an aircraft, the aircraft system comprising:
a sensor system configured to sense an engine parameter of an engine of the aircraft during a take-off procedure of the aircraft, and to output information representative of the engine parameter;
a landing gear system configured to retract a landing gear of the aircraft; and
a control system configured to:
receive the information from the sensor system; and
determine, during the take-off procedure, if there is a fault or failure of the engine based on the information, and
cause the landing gear system to perform at least a portion of a retraction procedure to retract the landing gear of the aircraft, in response to the determination of the fault or the failure.

14. The aircraft system of claim 13 , wherein the controller is further configured to:
receive at least one additional signal during the take-off procedure indicative of a climb rate of the aircraft;
determine if the climb rate meets a climb rate criterion,
confirm the performance of the at least the portion of the retraction procedure if the climb rate does not meet the criterion, and
inhibit the performance of the at least the portion of the retraction procedure if the climb rate meets the criterion.

Assignees

• Airbus Operations Ltd

Inventors

• Kerr Sean
• Marles David

Classifications

• B64D31/09

  in response to power plant failure · CPC title

• B64C25/26 Primary

  Control or locking systems therefor · CPC title

• B64C13/16 Primary

  actuated automatically, e.g. responsive to gust detectors · CPC title

• B64C25/10

  retractable, foldable, or the like · CPC title

• G05D1/0088

  characterized by the autonomous decision making process, e.g. artificial intelligence, predefined behaviours (using knowledge based models G06N5/00) · CPC title