Power margin indicator device for a rotorcraft, an associated rotorcraft, and a corresponding method

Patent metadata

Field	Value
Publication number	US-10329028-B2
Application number	US-201715635426-A
Country	US
Kind code	B2
Filing date	Jun 28, 2017
Priority date	Jul 1, 2016
Publication date	Jun 25, 2019
Grant date	Jun 25, 2019

Abstract

The present invention relates to A power margin indicator device constituting a first limitation indicator for a rotorcraft, for providing a pilot of said rotorcraft with information about a power margin available on at least one engine and a main power transmission gearbox of said rotorcraft as a function of flying conditions, said device comprising:
input means for collecting input data corresponding various operating parameters of said at least one engine and of said MGB; calculation means connected to said input means, said calculation means serving to determine a collective pitch margin for the blades of a rotor of said rotorcraft; and display means presenting said collective pitch margin.

First claim

What is claimed is:

1. A power margin indicator device constituting a first limitation indicator for a rotorcraft, for providing a pilot of the rotorcraft with information about a power margin available on at least one engine and a main power transmission gearbox of the rotorcraft as a function of flying conditions, the device comprising:
input means for collecting input data corresponding to at least two distinct operating parameters of the at least one engine and of the main power transmission gearbox;
calculation means connected to the input means, the calculation means serving:
to calculate at least two power margins as a function firstly of respective values of the at least two operating parameters, and secondly of limitation values for at least one of the utilization ratings corresponding to a maximum takeoff power, a maximum continuous power, a maximum transient power, a thirty second one engine inoperative supercontingency power, a two minute one engine inoperative contingency power, and a one engine inoperative continuous contingency power for the at least one engine;
to compare the at least two power margins in order to identify a limiting power margin as being the smallest of the at least two power margins; and
to convert the limiting power margin into a collective pitch margin for the blades of a rotor of the rotorcraft; and

display means presenting on a display screen the collective pitch margin represented on a scale graduated in collective pitch equivalents in a window of the display screen and an index representative of a current collective pitch of the blades of the rotor;
wherein:
the calculation means are configured to determine the following simultaneously for at least one of the utilization ratings corresponding to the maximum takeoff power, the maximum continuous power, the maximum transient power, the thirty second one engine inoperative supercontingency power, the two minute one engine inoperative contingency power, and the one engine inoperative continuous contingency power for the at least one engine:
initially, a plurality of results corresponding to the collective pitch margin for the blades of the rotor for a plurality of values of the speed of rotation of the rotor, the plurality of values of the speed of rotation of the rotor forming a predetermined range of values for the speed of rotation of the rotor; and
subsequently, a plurality of collective pitch limits obtained by summing the current collective pitch of the blades of the rotor with each of the results of the plurality of results; and

the display means present at least one planar curve corresponding to the at least one of the utilization ratings corresponding to the maximum takeoff power, the maximum continuous power, the maximum transient power, the thirty second one engine inoperative supercontingency power, the two minute one engine inoperative contingency power, and the one engine inoperative continuous contingency power for the at least one engine, the at least one planar curve being representative of the plurality of collective pitch limits over the predetermined range of values for the speed of rotation of the rotor, the at least one planar curve being formed by a set of points presenting as abscissa value the speed of rotation of the rotor and as ordinate value a corresponding collective pitch limit, each of the at least one planar curves being capable of moving at least along an ordinate axis Y relative to the scale graduated in collective pitch equivalents and/or relative to the index representative of a current collective pitch of the blades of the rotor.

2. The device according to claim 1 , wherein the at least two distinct operating parameters are selected from the group comprising at least: a speed of rotation of a gas generator of the engine; a first torque measured at the engine; a second torque measured at an inlet of the main power transmission gearbox; and a gas ejection temperature T4 measured at the inlet of a free turbine of the engine.

3. The device according to claim 1 , wherein the predetermined range of values for the speed of rotation is expressed as a percentage of a nominal value for the speed of rotation.

4. The device according to claim 3 , wherein the predetermined range of values for the speed of rotation extends from a minimum speed corresponding to 70% of the nominal value for the speed of rotation, to a maximum speed corresponding to 130% of the nominal value of the speed of rotation.

5. The device according to claim 1 , wherein the index representative of the current collective pitch is capable of moving along an abscissa axis X relative to the scale graduated in collective pitch equivalents, and/or relative to the at least one planar curve.

6. The device according to claim 1 , wherein each of the at least one planar curve is capable of moving both along the ordinate axis Y and an abscissa axis X relative to the scale graduated in collective pitch equivalents, and/or relative to the index representative of the current collective pitch of the blades of the rotor.

7. The device according to claim 1 , wherein the at least one planar curve is representative of an increasing function.

8. The device according to claim 1 , wherein the display means present at least two planar curves corresponding to two of the utilization ratings corresponding to the maximum takeoff power, the maximum continuous power, the maximum transient power, the thirty second one engine inoperative supercontingency power, the two minute one engine inoperative contingency power, and the one engine inoperative continuous contingency power for the at least one engine; the at least two planar curves being representative of at least two different pluralities of collective pitch limits over the predetermined range of values for the speed of rotation of the rotor, the at least two planar curves being parallel to each other.

9. A rotorcraft including at least one engine and a main power transmission gearbox for driving rotation of at least one main rotor, wherein the rotorcraft includes a power margin indicator according to claim 1 .

10. A method for providing a pilot of a rotorcraft with information about a power margin available on at least one engine and a main power transmission gearbox of the rotorcraft as a function of flying conditions, the method comprising:
a collection step for collecting input data corresponding to at least two distinct operating parameters of the at least one engine and the main power transmission gearbox;
a calculation step for calculating at least two power margins as a function firstly of respective values of the at least two operating parameters, and secondly of limitation values for at least one of the utilization ratings corresponding to a maximum takeoff power (TOP), a maximum continuous power, a maximum transient power, a thirty second one engine inoperative supercontingency power, a two minute one engine inoperative contingency power, and a one engine inoperative continuous contingency power for the at least one engine;
a comparison step for comparing the at least two power margins and identifying a limiting power margin as being the smallest of the at least two power margins;
a conversion step for converting the limiting power margin into a collective pitch margin for the blades of a rotor of the rotorcraft; and
a display step for presenting on a display screen the collective pitch margin represented on a scale graduated in collective pitch equivalents in a window of the display screen and an index representative of a current collective pitch of the blades of the rotor;
wherein:
the calculation, comparison, and conversion steps serve to determine the following simultaneously for at least one o

Assignees

• Airbus Helicopters

Inventors

• Abbas Gregory
• Gavios Damien

Classifications

• B64C27/04

  Helicopters · CPC title

• B64C27/006

  Safety devices · CPC title

• B64D43/00 Primary

  Arrangements or adaptations of instruments · CPC title

• G01M15/044

  by monitoring power, e.g. by operating the engine with one of the ignitions interrupted; by using acceleration tests · CPC title