Method of simulating a failure on an aircraft

Patent metadata

Field	Value
Publication number	US-9240126-B2
Application number	US-201313741751-A
Country	US
Kind code	B2
Filing date	Jan 15, 2013
Priority date	Feb 6, 2012
Publication date	Jan 19, 2016
Grant date	Jan 19, 2016

Abstract

A method of failure simulation for an aircraft ( 7 ) having a power plant ( 10 ) with at least two turbine engines ( 11, 12 ), together the two engines develop an overall power, each engine ( 11, 12 ) being capable of delivering at least one contingency power in order to compensate for a total failure of other engines ( 11, 12 ). The device serves during a failure simulation to modify the overall power delivered by the power plant, with this modification being performed with the help of first adjustment means ( 20 ). Second adjustment means ( 30 ) serve to modify also the difference between the minimum power obtained during the simulated failure and the stabilized overall power, and also the time between said failure stabilizing on said overall power.

First claim

What is claimed is:

1. A method of simulating a failure for an aircraft having a power plant, the power plant having at least two turbine engines together developing an overall power, each engine being capable of delivering at least one contingency power level in order to compensate for a failure of at least one other engine, wherein a low value, selected from any of a plurality of values lying between a minimum value and a maximum value, for the overall power is set manually with the help of first adjustment means and the overall power is reduced to the low value in order to simulate the failure and display means is used to display at least one OEI (one engine inoperative) contingency rating corresponding to the low value of the overall power.

2. The method according to claim 1 , wherein at least one characteristic for the passage of the overall power to the low value is set with the help of second adjustment means prior to lowering the overall power.

3. The method according to claim 2 , wherein the low value for the overall power is reached, the overall power dropping down to a minimum power before increasing and stabilizing at the low value for the overall power, and the characteristics comprise a difference A between the minimum power and the low value for the overall power, and also a time T between the instant at which the failure is simulated and the instant at which the overall power stabilizes at the low level.

4. The method according to claim 1 , wherein verification means is used to verify that the low value for the overall power is not less than a first limit power below which safe flight for the aircraft is not assured.

5. The method according to claim 4 , wherein the verification means is used to verify that each power level from the engines constituting the low value for the overall power is not greater than a second limit power above which the power plant is liable to be degraded.

6. The method according to claim 1 , wherein the low value for the overall power is shared uniformly among all of the engines.

7. A failure simulator device for an aircraft, comprising:
a power plant having at least two turbine engines together developing an overall power, each engine being capable of delivering at least one contingency power in order to compensate for a failure of at least one other engine; and
one control unit for each engine, each control unit being connected to the corresponding engine and controlling its power;
wherein the device comprises first adjustment means suitable for controlling the control units and for setting a low value, selected from any one of a plurality of values lying between a minimum value and a maximum value, of the overall power when simulating the failure;
wherein the device further comprises display means to display at least one OEI (one engine inoperative) contingency rating corresponding to the low value of the overall power.

8. The device according to claim 7 , wherein the device comprises second adjustment means suitable for controlling the control units and for setting at least one characteristic for the passage of the overall power to the low value for the overall power.

9. The device according to claim 8 , wherein the low value for the overall power is reached, the overall power dropping down to a minimum power before increasing and stabilizing at the low value for the overall power, and the characteristics comprise a difference A between the minimum power and the low value for the overall power, and a time T between the instant of the simulated failure and the instant at which the overall power stabilizes at the low value.

10. The device according to claim 8 , wherein the control unit can modify the feeding of fuel to the engine to which it is connected in order to modify at least one of the characteristics.

11. The device according to claim 7 , wherein the device includes verification means for verifying that the low value of the overall power is not less than a first limit power below which safe flight of the aircraft is not ensured.

12. The device according to claim 11 , wherein the verification means serves to verify that each power level from the engines constituting the low value for the overall power is not greater than a second limit power above which the power plant is liable to be degraded.

13. The device according to claim 7 , wherein the low value for the overall power is shared uniformly among all the engines.

14. A method of simulating a failure for an aircraft having a power plant, the power plant having at least two turbine engines together developing an overall power, each engine being capable of delivering at least one contingency power level in order to compensate for a failure of at least one other engine, wherein a low value, selected from any of a plurality of values lying between a minimum value and a maximum value, for the overall power is set manually with the help of first adjustment means and the overall power is reduced to the low value in order to simulate the failure;
wherein at least one characteristic for the passage of the overall power to the low value is set with the help of second adjustment means prior to lowering the overall power;
wherein the low value for the overall power is reached, the overall power dropping down to a minimum power before increasing and stabilizing at the low value for the overall power, and the characteristics include a difference A between the minimum power and the low value for the overall power and a time T between the instant at which the failure is simulated and the instant at which the overall power stabilizes at the low level.

15. The method according to claim 14 , wherein verification means is used to verify that the low value for the overall power is not less than a first limit power below which safe flight for the aircraft is not assured.

16. The method according to claim 15 , wherein the verification means is used to verify that each power level from the engines constituting the low value for the overall power is not greater than a second limit power above which the power plant is liable to be degraded.

17. The method according to claim 14 , wherein the low value for the overall power is shared uniformly among all of the engines.

18. The method according to claim 14 , wherein display means is used to display at least one OEI (one engine inoperative) contingency rating corresponding to the low value of the overall power.

19. A failure simulator device for an aircraft, comprising:
a power plant having at least two turbine engines together developing an overall power, each engine being capable of delivering at least one contingency power in order to compensate for a failure of at least one other engine; and
one control unit for each engine, each control unit being connected to the corresponding engine and controlling its power;
wherein the device includes first adjustment means suitable for controlling the control units and for setting a low value, selected from any one of a plurality of values lying between a minimum value and a maximum value, of the overall power when simulating the failure;
wherein the device further includes second adjustment means suitable for controlling the control units and for setting at least one characteristic for the passage of the overall power to the low value for the overall power;
wherein the low value for the overall power is reached, the overall power dropping down to a minimum power before increasing and stabilizing at the low value for the overall power, and the characteristics include a differen

Assignees

• Airbus Helicopters

Inventors

• Beaud Southdary
• Camhi Emmanuel

Classifications

• G09B9/46

  the aircraft being a helicopter · CPC title

• G09B9/18 Primary

  Condition of engine or fuel supply · CPC title

• G09B5/00 Primary

  Electrically-operated educational appliances (working with questions and answers G09B7/00; simulators G09B9/00; advertising or displaying in general G09F) · CPC title