System for controlling an aircraft thrust reversal means

1. A system for controlling an aircraft thrust reverser, comprising a reverse idle control, a first detection means configured to detect, when the reverse idle control is active, a condition for activation of the thrust reverser, an actuation means configured to activate the thrust reverser when the first detection means detects a condition for activation of the thrust reverser, and a second detection means configured to detect a condition for activation of the reverse idle control, the reverse idle control being configured to activate when the second detection means detects a condition for activating the reverse idle control.

2. The system according to claim 1 , wherein the second detection means is capable of detecting at least one parameter selected from a speed of the aircraft, an altitude of the aircraft, a rate of variation of the altitude of the aircraft, and an angle of descent of the aircraft.

3. The system according to claim 1 , wherein a necessary condition for the second detection means to detect a condition for activation of the reverse idle control is that an aircraft engine power control is comprised between 0% and 5% of the maximum power.

4. The system according to claim 1 , further comprising an arming module able to be activated by a user during a step of preparing the landing of the aircraft and/or a step of preparing the take-off of the aircraft, the second detection means being configured to detect a condition for activation of the reverse idle control only if the arming module is activated.

5. The system according to claim 4 , wherein the arming module comprises means for arming an auto brake system of the aircraft, the arming module being configured to be activated when a user actuates the arming means.

6. The system according to claim 1 , wherein the control means comprises a controller and a control lever for at least one engine of the aircraft, the control lever being capable of activating a reverse idle control.

7. The system according to claim 6 , comprising a motorised actuator in communication of information with the controller, the controller being able to control the motorised actuator so as to change a position of the control lever between a position wherein the control lever controls a forward operation of the engine of the aircraft and a position wherein the control lever activates a reverse idle control.

8. The system according to claim 6 , further comprising means for displaying the position of the control lever.

9. The system according to claim 6 , comprising means for displaying the activation of the reverse idle control, the controller being capable of directly activating the reverse idle control.

10. A method for controlling a thrust reverser system connected to at least one engine of an aircraft, wherein the thrust reverser system comprises a detector, a speed detector, a radio altimeter, a position sensor, and levers comprising:

detecting a condition for activation of a reverse idle control by:

collecting speed detected by the speed detector,

collecting an altitude emitted by the radio altimeter,

determining a position of the levers, and

determining the angle of descent or climb of the aircraft,

activating the reverse idle control,

detecting a condition for activation of the thrust reverser by:

determining if the weight of the aircraft rests on wheels of landing gear; and

when the weight of the aircraft rests on the wheels of the landing gear, activating the thrust reverser, and

detecting a condition for activation of the reverse idle control.

11. The method of claim 10 , wherein the condition for activation of the reverse idle control is a detection of a situation at a start of a flare before landing the aircraft.

12. The method of claim 10 , wherein the condition for activation of the reverse idle control is a detection of a situation of triggering an aborted take-off.

13. The method of claim 10 , further comprising:

activating an arming module when preparing the landing of the aircraft; and

detecting a condition for activation of the reverse idle control.

14. The method of claim 10 , further comprising:

displaying the activation of the reverse idle control.

15. The method of claim 10 , further comprising:

pulling the levers to increase power supplied by the one of more engines; and

increasing a braking effect supplied by the thrust reversers.

16. The method of claim 10 , wherein the condition for activation of the thrust reverser is selected from the altitude above ground being less than 50 feet, the airspeed being within a tolerance of 5% around a reference speed for the landing, the position of the levers being in a forward range and between 0% and 5% of the maximum power that can be supplied by the at least one engine wherein a vertical speed is negative, or the position of the levers being between −5% and +5% around a forward idle position.

17. The method of claim 16 , further comprising:

displaying the position of the reverse idle control.