Granted Patent B2

US 12,735,176 · App. 18/966,672 · Granted Sep 15, 2026

Inventors: Mario Hamers (Donauwörth, DE); Rene Nater (Asbach-Bäumenheim, DE)

Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH

B64C27/00G09B9/46

Abstract

Claims (30)

1 . A rotorcraft with at least one main rotor and at least one engine for powering the at least one main rotor in a normal flight mode, comprising an autorotation training mode control system that is activatable for switching rotorcraft operation between the normal flight mode and an autorotation training mode configured to enable training of autorotation, wherein the autorotation training mode control system comprises at least one main control element that is manually operable for activating the autorotation training mode control system and switching the rotorcraft operation from the normal flight mode to the autorotation training mode to engage the autorotation training mode;

wherein the autorotation training mode control system comprises a data processing unit configured to control execution of the autorotation training mode;

wherein the data processing unit enables execution of the autorotation training mode only if predetermined execution conditions are fulfilled; and

wherein the at least one engine is monitored by a Full Authority Digital Engine Control, and wherein the predetermined execution conditions are fulfilled if: no failure levels are detected on the Full Authority Digital Engine Control, no One Engine Inoperative training mode is engaged, and engine torque of the at least one engine is below a predetermined threshold.

2 . The rotorcraft of claim 1 , wherein the autorotation training mode control system is configured for disengaging the autorotation training mode if one or more predetermined disengagement conditions are fulfilled.

3 . The rotorcraft of claim 2 , comprising at least one of a main instrument panel, a slant console, and a middle console, wherein the at least one main control element is arranged on one of the main instrument panel, the slant console, or the middle console, wherein the at least one main control element is a switch or a button.

4 . The rotorcraft of claim 2 , wherein the at least one main control element is further manually operable for deactivating the autorotation training mode control system and disengaging the autorotation training mode for switching the rotorcraft operation from the autorotation training mode to the normal flight mode.

5 . The rotorcraft of claim 2 , further comprising, at least one auxiliary control element that is manually operable for activating the autorotation training mode control system and switching the rotorcraft operation from the normal flight mode to the autorotation training mode to engage the autorotation training mode, and/or for deactivating the autorotation training mode control system and disengaging the autorotation training mode for switching the rotorcraft operation from the autorotation training mode to the normal flight mode.

6 . The rotorcraft of claim 5 , comprising at least one of a collective stick, a pilot cyclic stick, and a co-pilot cyclic stick, wherein the at least one auxiliary control element is arranged on one of the collective stick, the pilot cyclic stick, and/or the co-pilot cyclic stick.

7 . The rotorcraft of claim 2 , wherein the data processing unit monitors rotorcraft operating parameters for determining whether one or more predetermined disengagement conditions are fulfilled; and

wherein the one or more predetermined disengagement conditions are fulfilled if: an actual engine free turbine speed value is below a predetermined engine free turbine speed autorotation reference value, a torque demand increases for a predefined duration above a predetermined torque threshold, and/or a predetermined duration after engagement of the autorotation training mode expires without rotor desynchronization.

8 . A rotorcraft with a main rotor and an engine for powering the main rotor in a normal flight mode, comprising an autorotation training mode control system activatable for switching rotorcraft operation between the normal flight mode and an autorotation training mode configured to enable training of autorotation, wherein the autorotation training mode control system comprises a main control element manually operable to switch the rotorcraft operation from the normal flight mode to the autorotation training mode to engage the autorotation training mode mode;

wherein the autorotation training mode control system comprises a data processer configured to control execution of the autorotation training mode;

wherein the autorotation training mode control system is configured to disengage the autorotation training mode if a predetermined disengagement condition is fulfilled

wherein the data processer monitors rotorcraft operating parameters to determine whether the predetermined disengagement condition is fulfilled; and

wherein the predetermined disengagement condition is fulfilled if: an actual engine free turbine speed value is below a predetermined engine free turbine speed autorotation reference value, a torque demand increases for a predefined duration above a predetermined torque threshold, and/or a predetermined duration after engagement of the autorotation training mode expires without rotor desynchronization.

9 . A rotorcraft with at least one main rotor and at least one engine for powering the at least one main rotor in a normal flight mode, comprising an autorotation training mode control system that is activatable for switching rotorcraft operation between the normal flight mode and an autorotation training mode configured to enable training of autorotation, wherein the autorotation training mode control system comprises at least one main control element that is manually operable for activating the autorotation training mode control system and switching the rotorcraft operation from the normal flight mode to the autorotation training mode to engage the autorotation training mode;

wherein the autorotation training mode control system comprises a data processing unit configured to control execution of the autorotation training mode;

wherein the autorotation training mode control system is configured for disengaging the autorotation training mode if one or more predetermined disengagement conditions are fulfilled;

wherein the data processing unit monitors rotorcraft operating parameters for determining whether the one or more predetermined disengagement conditions are fulfilled; and

wherein the one or more predetermined disengagement conditions are fulfilled if: an actual engine free turbine speed value is below a predetermined engine free turbine speed autorotation reference value, a torque demand increases for a predefined duration above a predetermined torque threshold, and/or a predetermined duration after engagement of the autorotation training mode expires without rotor desynchronization.

10 . The rotorcraft of claim 9 , comprising at least one of a main instrument panel, a slant console, and a middle console, wherein the at least one main control element is arranged on one of the main instrument panel, the slant console, or the middle console.

11 . The rotorcraft of claim 9 , wherein the at least one main control element is a switch or a button.

12 . The rotorcraft of claim 9 , wherein the at least one main control element is further manually operable for deactivating the autorotation training mode control system and disengaging the autorotation training mode for switching the rotorcraft operation from the autorotation training mode to the normal flight mode.

13 . The rotorcraft of claim 9 , further comprising, at least one auxiliary control element that is manually operable for activating the autorotation training mode control system and switching the rotorcraft operation from the normal flight mode to the autorotation training mode to engage the autorotation training mode, and/or for deactivating the autorotation training mode control system and disengaging the autorotation training mode for switching the rotorcraft operation from the autorotation training mode to the normal flight mode.

14 . The rotorcraft of claim 13 , comprising at least one of a collective stick, a pilot cyclic stick, and a co-pilot cyclic stick, wherein the at least one auxiliary control element is arranged on one of the collective stick, the pilot cyclic stick, and/or the co-pilot cyclic stick.

15 . The rotorcraft of claim 13 , wherein the at least one auxiliary control element is a switch or a button.

16 . The rotorcraft of claim 9 , wherein the data processing unit enables execution of the autorotation training mode only if predetermined execution conditions are fulfilled.

17 . The rotorcraft of claim 9 , wherein the data processing unit decreases a predetermined engine free turbine speed datum by a predetermined reduction rate during execution of the autorotation training mode.

18 . The rotorcraft of claim 9 , wherein the autorotation training mode control system comprises a display indicator for visualizing engagement of the autorotation training mode.

Assignments (1)

Priority Claims (1)

Continuity (1)

References Cited (14)