AIRCRAFT WITH AUTOMATIC FENCING IN RESPONSE TO ENGINE FAILURE DETECTION

Abstract

The aircraft (100) comprises: - two engines (104A, 104B); - two propellers (106A, 106B) respectively driven by the engines (104A, 104B) to propel the aircraft (100), each propeller (106A, 106B) having variable pitch blades; and - for each engine (104A, 104B), a computer (116A, 116B) designed to regulate the engine (104A, 104B) in question; monitoring of each motor (104A, 104B) being implemented, this monitoring includes: - detecting a failure of the motor (104A, 104B) in question and, - in the event of detection of a failure of the motor (104A, 104B) in question, commanding a feathering of the propeller blades (106A, 106B) and commanding the computer (116A, 116B) of the other motor (104A, 104B) to activate an operating mode of the other motor (104A, 104B) adapted to the detected failure of the motor (104A, 104B) in question.Each computer (116A, 116B) is dual-channel, presenting two channels, and designed so that one channel, called the control channel, regulates the associated motor (104A, 104B), while the other channel, called the standby channel, monitors the associated motor (104A, 104B). See Figure 1 for abbreviations.

Description

Title of the invention: AIRCRAFT WITH AUTOMATIC FEARING IN RESPONSE TO ENGINE FAILURE DETECTION Technical field of the invention

[0001] The present invention relates to an aircraft with automatic feathering in response to engine failure detection. Technological background

[0002] An aircraft comprising: is known from the prior art - two engines; - two propellers respectively driven by the engines to propel the aircraft; - for each propeller, a blade pitch control system for the propeller in question; and - for each engine, a computer designed to regulate the engine considered ; monitoring of each engine being implemented, this monitoring includes: - detecting a failure of the engine in question and, - in the event of detection of a failure of the engine in question, to command the stalling system associated with this engine in question to feather the propeller blades and to command the computer of the other engine to activate an operating mode of the other engine adapted to the detected failure of the engine in question.

[0003] It is known that monitoring is performed by a specific computer, separate from the engine control computers. The monitoring function therefore requires an additional computer, in addition to the aircraft's other computers. However, reliability decreases with the number of computers.

[0004] It may therefore be desirable to provide an aircraft which makes it possible to overcome at least some of the aforementioned problems and constraints. Summary of the invention

[0005] An aircraft comprising: is therefore proposed. - two engines; - two propellers respectively driven by the engines to propel the aircraft; - for each propeller, a blade pitch control system for the propeller in question; and - for each engine, a computer designed to regulate the engine considered ; monitoring of each engine being implemented, this monitoring includes: - detecting a failure of the engine in question and, - in the event of detection of a failure of the engine in question, to command the stalling system associated with this engine in question to feather the propeller blades and to command the computer of the other engine to activate an operating mode of the other engine adapted to the detected failure of the engine in question; characterized in that each computer is dual-channel so as to present two channels, and designed so that one of the channels, called the control channel, regulates the associated motor, while the other of the channels, called the standby channel, implements the monitoring of the associated motor.

[0006] Thanks to the invention, a specific computer for the monitoring function can be avoided.

[0007] The invention may further include one or more of the following optional features, according to any technically possible combination.

[0008] Optionally, the aircraft may also include: - for each motor, sensors designed to measure operating parameters of the motor in question; and / or - avionics; and in which each waiting channel implements monitoring from measurements of the sensors of the associated engine and / or information received from the avionics.

[0009] Optionally, the detected fault may also be one of the following: - a shutdown of the associated engine; - a loss of power in the associated engine; and - a power difference between the associated engine and the other engine greater than a threshold.

[0010] Optionally, the flagging also includes one of the following: - the transmission of a discrete analog signal to a propeller timing system; - the transmission of a discrete digital signal to the propeller timing system; and - a direct activation of a flagging device independent of the stabilization system.

[0011] Optionally, the control of the other computer may also include one of the following: - the transmission of a discrete analog signal to the other computer; and - the transmission of a discrete digital signal through a link digital communication between computers.

[0012] Optionally, the aircraft also includes a device designed to detect a failure of each standby channel and, if such a failure is detected in one of the standby channels: - to warn an aircraft pilot of the unavailability of the automatic feathering activation; and / or - to control the computer of the other engine to activate an operating mode of the other engine adapted to the detected failure of the engine in question.

[0013] Optionally, each engine also includes a turbomachine.

[0014] Optionally, the computer is also designed to alternate the lane in control and the waiting lane. Brief description of the figures

[0015] The invention will be better understood with the aid of the following description, given solely by way of example and made with reference to the accompanying drawings in which: - [Fig.1] is a simplified top view of an aircraft according to the invention. Detailed description of the invention

[0016] With reference to [Fig.1], an example of aircraft 100 according to the invention will now be described.

[0017] The aircraft 100 is for example an airplane and includes first of all a fixed wing 102 and two engines 104A, 104B, such as turbomachines, carried by the fixed wing 102. The aircraft 100 also includes two propellers 106A, 106B respectively driven by the engines 104A, 104B to propel the aircraft 100.

[0018] Each propeller 106A, 106B has adjustable-pitch blades. Thus, the aircraft 100 further comprises, for each propeller 106A, 106B, a blade pitch control system 108A, 108B for the propeller 106A, 106B in question. The aircraft 100 may also comprise, for each propeller 106A, 106B, a feathering device 109A, 109B independent of the pitch control system 108A, 108B, such as, for example, a servo valve.

[0019] The aircraft 100 further comprises, for each engine 104A, 104B, a sensor 110A, respectively 110B, designed to measure operating parameters of the engine 104A, respectively 104B, considered.

[0020] The aircraft 100 further comprises avionics 112 and an information presentation device 114 (for example, visually and / or audibly) to a pilot of the aircraft 100.

[0021] The aircraft 100 further comprises, for each engine 104A, 104B, a computer 116A, respectively 116B.

[0022] Each computer 116A, 116B is dual-channel so as to present two channels. One of the channels, hereafter referred to as the control channel, regulates the motor 104A, 104B associated, while the other of the tracks, subsequently called the standby track, monitors this 104A, 104B motor.

[0023] More specifically, the standby channel is designed to detect a failure of the associated 104A, 104B motor.

[0024] For example, the standby channel implements this monitoring based on measurements from sensors 110A, 110B of the associated engine 104A, 104B and / or information received from the avionics 112. Also, for example, the standby channel is designed to detect at least one of the following failures: a shutdown of the associated engine 104A, 104B, a loss of power of the associated engine 104A, 104B significant enough to be considered an in-flight shutdown (IFSD), a loss of power of the associated engine 104A, 104B significant enough to be considered a loss of power control (LOPC), and a power difference between the associated engine 104A, 104B and the other engine 104A, 104B exceeding a predefined threshold acceptable to the aircraft.

[0025] The standby track is further designed, in the event of detection of a failure of the associated motor 104A, 104B, to feather the blades of the propeller 108A, 108B.

[0026] For example, feathering includes one of: a transmission of a discrete analog signal to the propeller trim system 108A, 108B; a transmission of a discrete digital signal to the propeller trim system through a digital communication link 118A, 118B of the aircraft 100 linking the computer 116A, 116B to the trim system 108A, 108B; and a direct activation of the feathering device 109A, 109B, i.e. without going through the trim system 108A, 108B.

[0027] The standby channel is further designed, in the event of detection of a failure of the associated engine 104A, 104B, to command the computer 110A, 110B of the other engine 104A, 104B to activate an operating mode of the other engine 104A, 104B adapted to the detected failure of the engine 104A, 104B considered, generally called OEI mode, from the English "One Engine Inoperative".

[0028] The control of the other computer 104A, 104B includes for example one of: a transmission of a discrete analog signal to the other computer 104A, 104B; and a transmission of a discrete digital signal through a digital communication link 120 between the computers 116A, 116B.

[0029] Preferably, each computer 116A, 116B is designed to alternate between the control channel and the standby channel. This alternation is performed, for example, each time the aircraft 100 is started.

[0030] Furthermore, avionics 112 may be designed to detect a failure in the monitoring channel. For example, avionics 112 is designed to detect a failure of each of the computers 116A, 116B. The avionics 112 is then designed, for example, in the event of detection of such a failure, to warn the pilot of the aircraft of the unavailability of the automatic feathering triggering through the information presentation device 114. The avionics 112 can also be designed, in the event of detection of such a failure, to command the computer 116A, 116B of the other engine 104A, 104B to activate the OEI mode.

[0031] In conclusion, it should be noted that the invention is not limited to the embodiments described above. It will indeed be apparent to those skilled in the art that various modifications can be made to the embodiments described above, in light of the information just disclosed to them.

[0032] In the detailed presentation of the invention given above, the terms used shall not be interpreted as limiting the invention to the embodiments set forth in this description, but shall be interpreted as including all equivalents which can be foreseen by a person skilled in the art by applying their general knowledge to the implementation of the teaching which has just been disclosed to them.

Claims

Demands

1. Aircraft (100) comprising: - two engines (104A, 104B); - two propellers (106A, 106B) respectively driven by the engines (104A, 104B) to propel the aircraft (100), each propeller (106A, 106B) having variable pitch blades; and - for each engine (104A, 104B), a computer (116A, 116B) designed to regulate the engine (104A, 104B) in question; monitoring of each engine (104A, 104B) being implemented, this monitoring including: - detecting a failure of the engine (104A, 104B) considered and, - in the event of detection of a failure of the engine (104A, 104B) considered, commanding a feathering of the propeller blades (106A, 106B) and commanding the computer (116A, 116B) of the other engine (104A, 104B) to activate an operating mode of the other engine (104A, 104B) adapted to the detected failure of the engine (104A, 104B) considered;characterized in that each computer (116A, 116B) is dual-channel so as to present two channels, and designed so that one of the channels, called the control channel, regulates the associated motor (104A, 104B), while the other of the channels, called the standby channel, implements the monitoring of the associated motor (104A, 104B).

2. Aircraft (100) according to claim 1, further comprising: - for each engine (104A, 104B), sensors (110A, 110B) designed to measure operating parameters of the engine (104A, 104B) considered; and / or - avionics (112); and wherein each standby channel implements monitoring from the measurements of the sensors (110A, 110B) of the associated engine (104A, 104B) and / or information received from the avionics (112).

3. Aircraft (100) according to claim 1 or 2, wherein the detected defect is one of: a shutdown of the associated motor (104A, 104B); - a loss of power of the associated motor (104A, 104B); and - a power difference between the associated motor (104A, 104B) and the other motor (104A, 104B) greater than a threshold.

4. Aircraft (100) according to any one of claims 1 to 3, wherein the feathering comprises one of: - a transmission of a discrete analog signal to a propeller trim system (108A, 108B); - a transmission of a discrete digital signal to the propeller trim system (108A, 108B); and - a direct activation of a feathering device (109A, 109B) independent of the trim system (108A, 108B).

5. Aircraft (100) according to any one of claims 1 to 4, wherein the control of the other computer (116A, 116B) comprises one of: - a transmission of a discrete analog signal to the other computer (116A, 116B); and - a transmission of a discrete digital signal through a digital communication link (120) between the computers (116A, 116B).

6. Aircraft (100) according to any one of claims 1 to 5, further comprising a device (112) designed to detect a failure of each standby channel and, in the event of detection of such a failure of one of the standby channels: - to warn a pilot of the aircraft (100) of the unavailability of the automatic feathering trigger; and / or - to command the computer (116A, 116B) of the other engine (104A, 104B) to activate an operating mode of the other engine (104A, 104B) adapted to the detected failure of the engine (104A, 104B) concerned.

7. Aircraft (100) according to any one of claims 1 to 6, wherein each engine (104A, 104B) comprises a turbomachine.

8. Aircraft (100) according to any one of claims 1 to 7, wherein the computer (116A, 116B) is designed to alternate between the control lane and the standby lane.

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