The invention is in the field of controlling an aircraft. In particular, the invention pertains, according to some embodiments, to control of engines of an aircraft.
In a conventional multi-engine aircraft, a pilot controls a plurality of levers, wherein a position of each lever indicates a desired thrust (or power) for each one of the plurality of engines.
There is now a need to provide new systems and methods for controlling engines of a multi-engine aircraft.
In accordance with certain aspects of the presently disclosed subject matter, there is provided a system for controlling a plurality of engines of an aircraft, wherein said plurality of engines comprises at least one first engine of the aircraft and at least one second engine of the aircraft, the system comprising a common controlling unit configured to convert data representative of a thrust command transmitted by an actuating element controllable by a pilot or by an auto-throttle of the aircraft, into:
In addition to the above features, the system according to this aspect of the presently disclosed subject matter can optionally comprise one or more of features (i) to (x) below, in any technically possible combination or permutation:
According to another aspect of the presently disclosed subject matter there is provided a system for controlling a plurality of engines of an aircraft, wherein said plurality of engines comprises at least one right engine and at least one left engine, the system comprising an interface operable by a pilot to provide a command representative of a curvature of a trajectory of the aircraft on the ground, and a common controlling unit configured to generate at least one first command usable by at least one controller of said at least one right engine for controlling thrust of said at least one right engine based at least on said first command, and generate at least one second command usable by at least one controller of said at least one left engine for controlling thrust of said at least one left engine based at least on said at least one second command, wherein said first command and said second command are selected such that thrust of said at least one right engine and thrust of said at least one left engine allow the aircraft to follow a curved trajectory representative of said command provided on said interface.
In addition to the above features, the system according to this aspect of the presently disclosed subject matter can optionally comprise one or more of features (i) to (x) above, in any technically possible combination or permutation.
According to another aspect of the presently disclosed subject matter, there is provided a method of controlling a plurality of engines of an aircraft, wherein said plurality of engines comprises at least one first engine of the aircraft and at least one second engine of the aircraft, the method comprising:
wherein said conversion is performed based at least on data representative of a level of operability of each engine, thereby making each engine to either comply with said thrust command or to operate differently from said thrust command, based at least on its level of operability.
In addition to the above features, the method according to this aspect of the presently disclosed subject matter can optionally comprise one or more of features (xi) to (xx) below, in any technically possible combination or permutation:
According to another aspect of the presently disclosed subject matter there is provided a method of controlling a plurality of engines of an aircraft, wherein said plurality of engines comprises at least one right engine and at least one left engine, the method comprising:
wherein said first command and said second command are selected such that thrust of said at least one right engine and thrust of said at least one left engine allow the aircraft to follow a curved trajectory representative of said command.
In addition to the above features, the method according to this aspect of the presently disclosed subject matter can optionally comprise one or more of features (xi) to (xx) above, in any technically possible combination or permutation:
According to another aspect of the presently disclosed subject matter there is provided a non-transitory storage device readable by a machine, tangibly embodying a program of instructions executable by the machine to perform a method controlling a plurality of engines of an aircraft, wherein said plurality of engines comprises at least one first engine of the aircraft and at least one second engine of the aircraft, the method comprising:
wherein said conversion is performed based at least on data representative of a level of operability of each engine, thereby making each engine to either comply with said thrust command or to operate differently from said thrust command, based at least on its level of operability.
In addition to the above features, the non-transitory storage device according to this aspect of the presently disclosed subject matter can optionally perform a method comprising one or more of features (xi) to (xx) above, in any technically possible combination or permutation.
According to another aspect of the presently disclosed subject matter there is provided a non-transitory storage device readable by a machine, tangibly embodying a program of instructions executable by the machine to perform a method of controlling a plurality of engines of an aircraft, wherein said plurality of engines comprises at least one right engine and at least one left engine, the method comprising:
wherein said first command and said second command are selected such that thrust of said at least one right engine and thrust of said at least one left engine allow the aircraft to follow a curved trajectory representative of said command.
In addition to the above features, the non-transitory storage device according to this aspect of the presently disclosed subject matter can optionally perform a method comprising one or more of features (xi) to (xx) above, in any technically possible combination or permutation.
According to some embodiments, the proposed solution improves efficiency and quality of control of engines of an aircraft.
According to some embodiments, the proposed solution provides simplification of control of an aircraft for a pilot. As a consequence, pilot's fatigue is reduced.
According to some embodiments, the proposed solution provides a better and safer handling of aircraft flight incidents, such as fire in engines, failure of engines, etc.
According to some embodiments, the proposed solution reduces the complexity of the intervention expected from a pilot during flight incidents.
According to some embodiments, the proposed solution increases automation of handling flight incidents which involve malfunction of one or more engines.
According to some embodiments, the proposed solution improves safety of flights.
According to some embodiments, the proposed solution improves control of aircraft whilst on the ground.
According to some embodiments, the proposed solution improves safety of aircraft during ground operations.
According to some embodiments, the proposed solution facilitates starting engines of the aircraft whilst on the ground.
In order to better understand the subject matter that is disclosed herein and to exemplify how it may be carried out in practice, embodiments will now be described, by way of non-limiting example only, with reference to the accompanying drawings, in which:
In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the invention. However, it will be understood by those skilled in the art that the presently disclosed subject matter may be practiced without these specific details. In other instances, well-known methods have not been described in detail so as not to obscure the presently disclosed subject matter.
Unless specifically stated otherwise, as apparent from the following discussions, it is appreciated that throughout the specification discussions utilizing terms such as “generating”, “converting”, “determining”, “instructing”, or the like, refer to the action(s) and/or process(es) of a processing unit that manipulates and/or transforms data into other data, said data represented as physical, such as electronic, quantities and/or said data representing the physical objects.
The term “processing unit” as disclosed herein should be broadly construed to include any kind of electronic device with data processing circuitry, which includes for example a computer processing device operatively connected to a computer memory (e.g. digital signal processor (DSP), a microcontroller, a field programmable gate array (FPGA), and an application specific integrated circuit (ASIC), etc.) capable of executing various data processing operations.
It can encompass a single processor or multiple processors, which may be located in the same geographical zone or may, at least partially, be located in different zones and may be able to communicate together.
The term “memory” as used herein should be expansively construed to cover any volatile or non-volatile computer memory suitable to the presently disclosed subject matter.
Embodiments of the presently disclosed subject matter are not described with reference to any particular programming language. It will be appreciated that a variety of programming languages may be used to implement the teachings of the presently disclosed subject matter as described herein.
The invention contemplates a computer program being readable by a computer for executing one or more methods of the invention. The invention further contemplates a machine-readable memory tangibly embodying a program of instructions executable by the machine for executing one or more methods of the invention.
Attention is drawn to
An engine can comprise e.g. a propeller, a turbo-propeller, a turbo-fan, a variable pitch propeller, an electrical engine, etc. This list is not limitative.
As shown, the aircraft comprises a plurality of engines 101 Pi, with i from 1 to N and N≥2.
According to some embodiments, the aircraft comprises at least one right engine (or a plurality of right engines) and at least one left engine (or a plurality of left engines). Right side and left side are generally defined with respect to a main axis of a body of the aircraft. This is not limitative and according to some embodiments, at least some of (or all) the engines are located on the axis of the body of the aircraft, or in the vicinity of this axis, or in any adapted location.
System 100 can comprise (or can be operatively connected to) an actuating element, such as a throttle or lever 110 controllable in particular by a pilot of the aircraft. In the following, it will be referred to a lever, but this is not limitative and other kinds of actuating elements controllable by a pilot can be used (different examples will be provided).
Depending on commands provided by the pilot on this lever 110, and/or by thrust commands provided by an auto-throttle and/or auto-pilot of the aircraft, thrust of the plurality of engines can be controlled. In other words, the pilot indicates, using this lever 110, a level of thrust desired for the engines of the aircraft.
Therefore, based on commands provided e.g. by the pilot, data representative of a thrust command is generated by the lever 110. It has to be noted that data representative of a thrust command are also representative of a power command, since thrust and power of an engine are directly correlated.
Similarly, the auto-throttle can generate data representative of a thrust command based e.g. on inputs of a pilot (e.g. the pilot sets a desired speed, or thrust, if necessary with some additional parameters such as altitude, and the auto-throttle generates data representative of a thrust command which corresponds to the pilot's input). In some embodiments, the auto-throttle can modify a physical position of the lever 110 in accordance with the thrust command.
According to some embodiments, lever 110 can control the thrust of all engines of the aircraft.
According to some embodiments, the system comprises a single lever 110 for controlling the positive thrust of all engines of the aircraft. In other words, the pilot provides a single thrust command (using this single lever) and controls positive thrust of all engines of the aircraft.
According to some embodiments, the system comprises a single lever 110 for controlling the positive thrust and the negative thrust of all engines of the aircraft. In other words, the pilot provides a single positive or negative thrust command (using this single lever) and controls positive or negative thrust of all engines of the aircraft. For example, when the pilot moves forward the lever, this will create a positive thrust command, and when the pilot moves backwards the lever, this will create a negative thrust command. This is however not limitative.
According to some embodiments, the system comprises a single lever 110 for controlling the positive thrust of all engines of the aircraft. In addition, a single sub-component of this single lever 110 (this can be e.g. a moving element present on the lever 110, or when a negative thrust has to be created on ground, this can correspond to element 150 described hereinafter) can be used for controlling the negative thrust of all engines of the aircraft.
In other words, the pilot can provide a single positive thrust command using single lever 110 which controls positive thrust of all engines of the aircraft, and the pilot can provide a single negative thrust command using the above-mentioned sub-component which controls negative thrust of all engines of the aircraft.
According to some embodiments, the system comprises a single lever 110 for controlling the positive thrust of all engines of the aircraft, and another single lever (which can be distinct from the first lever) for controlling the negative thrust of all engines of the aircraft. In other words, the pilot can provide a single positive thrust command using a first single lever which controls positive thrust of all engines of the aircraft, and the pilot can provide a single negative thrust command using a second single lever which controls negative thrust of all engines of the aircraft.
According to some embodiments, data representative of a single thrust command is generated by the lever (or by a processing unit connected to the lever and suitable for translating the position of the lever into a thrust command), and based on this single thrust command, the thrust of all engines can be controlled.
According to some embodiments, and as shown in
In other words, it is possible to control the thrust of the plurality of engines of the aircraft (in particular of all engines of the aircraft) with a single movable element 150.
As already mentioned above, a lever is only a possible example of an actuating element which can be present in the aircraft for providing a thrust command. Other examples include a joystick, a graphical interface, a keyboard, an electronic button, an interface controllable by voice (etc.) with which the pilot can indicate a thrust level for the engines—in particular, according to some embodiments, a single thrust level can be indicated for all engines by the pilot using this actuating element (in some embodiments, a single actuating element controls positive and negative thrust of all engines, and in other embodiments, a single first actuating element controls positive thrust of all engines and a single second actuating element controls negative thrust of all engines).
As shown in
The common controlling unit 130 is operable on a processing unit and can comprise in some embodiments data circuitry and a memory. In some embodiments, the common controlling unit 130 can include an embedded system (or unit) with one or more lanes. It can include an analog or digital input/output (I/O) interface. According to some embodiments, the common controlling unit 130 comprises complex hardware (e.g. FPGA, ASIC) or computer hardware (e.g. CPU, RAM, ROM).
As explained hereinafter in the specification, the common controlling unit 130 can receive other commands from the pilot and/or the auto-pilot of the aircraft, such as a command representative of a curvature of the trajectory of the aircraft on ground.
As shown in
In particular, the common controlling unit 130 can generate, based on data representative of a thrust command:
For example, assume the aircraft comprises a right engine P1, controlled by a controller C1 and a left engine P2 controller by a controller C2.
The common controlling unit 130 can receive data representative of a thrust command from the lever 110 and can generate a first command for the controller C1 and a second command for the controller C2.
As explained hereinafter in the specification, the first command and the second command are generally also each representative of a thrust command.
The controller 140 of an engine is for example a FADEC (Full Authority Digital Engine), an “electronic engine controller” (EEC) or an “engine control unit” (ECU). This is however not limitative. A FADEC generally receives a position of the lever which represents a thrust level.
According to some embodiments, a single common controlling unit 130 can generate commands for all controllers of all engines of the aircraft.
According to some embodiments, the controller 140 (e.g. FADEC) converts a command received from the common controlling unit 130 into at least one command pertaining to engine operating parameters such as fuel flow, stator vane position, air bleed valve position, rotation speed of the fan, etc. In other words, the controller 140 can translate data representative of a thrust command received from the common controlling unit 130 into a command for the engine which ensures that the engine complies with the thrust command.
According to some embodiments, the controller 140 of an engine also controls and monitors engine starting and relighting.
According to some embodiments, the first command and the second command can be thrust commands generated by the common controlling unit 130 (based on the thrust command provided by the lever 110 or the auto-throttle).
The first command is transmitted to a first controller which converts it into a command pertaining to engine operating parameters for a first engine. The conversion can depend on various parameters, such as operability of the engines, parameters of the flight, etc.
Engine operating parameters of the first engine are selected such that resulting thrust/power of the first engine controlled by said first controller matches the first command (which is e.g. a thrust command). For example, appropriate rotation speed of the turbine, angle of attack of the blades, etc. are selected to match the thrust command (first command).
Similarly, the second command is transmitted to a second controller which converts it into a command pertaining to engine operating parameters for a second engine.
Engine operating parameters of the second engine are selected such that thrust/power of the second engine controlled by said second controller matches the second command (which is e.g. a thrust command).
According to some embodiments, a given controller can comprise multi-channels, in order to control multiple engines. In this case, each channel is dedicated to control engine operating parameters of a different engine. For example, a given controller can be assigned to control engine operating parameters of a plurality of engines located on the right side of the aircraft. In this case, the given controller will apply the command generated by the common controlling unit to the plurality of engines that it controls. This is however not limitative.
According to some embodiments, the common controlling unit 130 can communicate with various other systems 160 and exchange data with them. These systems 160 include at least one of:
The common controlling unit 130 can generate commands for the controllers 140 of the engines 101 based also on one or more of the data received from one or more of the systems 160 mentioned above. Various examples will be provided hereinafter.
According to some embodiments, the common controlling unit 130 stores in at least one memory one or more predefined operations to be applied for each of a plurality of predefined flight/ground scenarios (e.g. malfunction/failure of an engine, etc.). For each scenario, the common controlling unit 130 can execute these instructions in order to appropriately convert the commands communicated by the pilot via the lever 110, or transmitted by the auto-throttle, into commands to be sent to the controllers 140 of the engines 101.
According to some embodiments, the lever 110 comprises a rotating member. Therefore, a pilot of the aircraft can rotate this rotating member to control motion of the aircraft. As explained hereinafter in the specification, this rotating member can be used to control, in an efficient way, the aircraft on the ground along a non-linear trajectory, such as a curved trajectory, based on the rotation of this rotating member.
A non-limitative example is illustrated in
This rotating member 190 can be rotated around an axis parallel to the main axis of the lever 110. A command representative of the rotation of the rotating member 190 can be generated by the lever 110 and transmitted to the common controlling unit 130.
This example is not limitative and other configurations can be used for the rotating member.
In some embodiments, the pilot can provide a command representative of a curvature of the trajectory of the aircraft using another interface (such as a screen, a joystick, a voice command, etc.).
Attention is now drawn to
According to some embodiments, system 100 can comprise, or can be connected to an additional interface 180. This additional interface 180 can comprise:
According to some embodiments, the additional interface 180 can rotate. Depending on the angular position of the additional interface 180, the corresponding action is activated (for example, when the interface 180 is rotated so that a predefined indicator of the interface is located at the “start” position 182, the engine is started).
According to some embodiments, for each engine, there is such an additional interface 180. Embodiments of methods which rely on this additional interface 180 will be described hereinafter.
Attention is now drawn to
The method can comprise (operation 200) obtaining a command from an actuating element controllable by a pilot, such as lever 110, or from the auto-throttle system of the aircraft. This command transmitted by the lever can be generated e.g. by the lever, or a by a processing unit in communication with the lever, based e.g. on a level of displacement of the lever by the pilot.
This command can be transmitted to the common controlling unit 130.
This command can be representative of a thrust level desired by the pilot or auto-throttle for the engines 101.
As mentioned, in some embodiments, a single thrust command is obtained based on a single input of the pilot, for all engines. The same can apply to the command of the auto-throttle, which can be a single thrust command for all engines of the aircraft.
The method can comprise converting (operation 210), by the common controlling unit 130, the received command into at least one first command and at least one second command. As explained hereinafter in the specification, the common controlling unit 130 can take into account various data in order to perform this conversion, such as:
Assume the aircraft has two engines (right engine and left engine), or more. The first command can be computed so as to be received by a first controller 140 (e.g. FADEC) of the right engine, and the second command can be computed so as to be received by a second controller 140 (e.g. FADEC) of the left engine.
The first command can be e.g. a command representative of a thrust required for the right engine. Similarly, the second command can be e.g. a command representative of a thrust required for the left engine.
This can be applied for more than two engines. Depending on the number N of controllers 140 for this plurality of N′ engines 101 (with N>2, N′>2), more than two commands can be generated for the controllers of these engines. Generally. N=N′ and therefore the common controlling unit 130 generates N=N′ commands. This is however not mandatory, and in some embodiments, N<N′, and therefore the common controlling unit can generate N commands for N controllers controlling N′ engines.
According to some embodiments, the first command and the second command are equal and substantially correspond to the thrust command provided by the lever 110 or the auto-throttle.
According to some embodiments, the first command and the second command can be different. Examples will be provided hereinafter, in which an asymmetric thrust is set for the engines 101, although the pilot or the auto-throttle may have only provided a single thrust command for all engines.
According to some embodiments, the first command and/or the second command can be different from the command generated by the lever 110 based on the pilot input, or from the auto-throttle command. Examples will be provided hereinafter, in which the common controlling unit 130 generates a first and/or second command which is new and differs from the command 120 based on other data that it receives, such as level of operability of an engine, status of the aircraft, etc.
As already explained with respect to
Engine operating parameters such as fuel flow, stator vane position, air bleed valve position, rotation speed of the turbine, etc. can be controlled by the controller of each engine to reflect the thrust command it has received from the common controlling unit 130.
During operation of the aircraft (e.g. on the ground and/or in flight) operations 200 and 210 can be repeated, depending e.g. on the actions of the pilot on the actuator of the system, on flight conditions, on possible malfunction of the engines, etc.
Attention is now drawn to
Operations depicted in
Assume the aircraft comprises engines P1 to PN, with N≥2.
The method can comprise obtaining (operation 300) a command (data representative of a thrust command) from lever 110 controllable by a pilot, or from an auto-throttle. Operation 300 is similar to operation 200 above. This command can be transmitted to the common controlling unit 130. In particular, a single thrust command can be transmitted to the common controlling unit 130 based on the pilot's input on lever 110, or based on the instructions of the auto-throttle.
The method can comprise obtaining (operation 301), by the common controlling unit 130, data representative of a malfunction and/or failure of at least one engine Pj (with j a value between 1 and N). This data can be transmitted e.g. by the controller of the faulty engine Pj, or by at least one sensor of the aircraft, or by a central processing unit of the aircraft, or by any other adapted system.
According to some embodiments, malfunction/failure of an engine can be classified into at least three categories:
Other classifications can be used.
As mentioned above, in the presented situation, the pilot provides a single thrust command (using the lever 110) while at least one engine is faulty. The same can apply to the auto-throttle, which can send a common thrust command for all engines.
According to some embodiments, the common controlling unit 130 can generate command(s) usable by the respective controller(s) 140 of each engine Pi, with i from 1 to N being different from j.
In other words, the thrust command transmitted by the lever 110 or by the auto-throttle is converted into corresponding thrust commands for only the controllers 140 which control the non-faulty engines Pi (i different from j).
According to some embodiments, assume the thrust command generated received by the common controlling unit 130 is equal to X, then the common controlling unit 130 can generate a thrust command substantially equal to X for only each of the controllers of the non-faulty engines. As a consequence, the non-faulty engines will have thrust which is substantially equal to the thrust command inputted by the pilot or sent by the auto-throttle.
Concerning the faulty engine Pj, the common controlling unit 130 can generate (see operation 303) a thrust command to the controller of engine Pj to instruct it e.g. to set a thrust of engine Pj at a reduced level (which is lower than the thrust level requested by the pilot using the lever, or requested by the auto-throttle). A possible embodiment of such control will be described with reference to
Therefore, although the pilot (or the auto-throttle) may provide a single thrust command, the common controlling unit 130 generates different thrust commands for the respective controllers of the engines, depending on the operability of the respective engines.
As shown in
According to some embodiments, an auto-pilot system of the aircraft can generate a yaw command for controlling position of a yaw actuator 420 of the aircraft, to compensate for the yaw drift caused by this failure.
According to some embodiments, the common controlling unit 130 (or another system of the aircraft, such as the auto-pilot) can generate (operation 304) a yaw command for controlling position of a yaw actuator 420 of the aircraft, to compensate for the yaw drift caused by this failure. The yaw actuator 420 is for example a rudder of the aircraft, as depicted in
Yaw drift 410 is compensated for by displacement 430 of yaw actuator 420.
According to some embodiments, the yaw command is computed, such as yaw drift is zero or below a threshold (which can be static, or dynamic).
According to some embodiments, a filter, such as a Kalman filter, present in the common controlling unit 130 can be used to determine the yaw command. The filter can receive data representative of the current yaw of the aircraft, data representative of the failure of the engine, and other flight data, in order to generate an appropriate yaw command.
According to some embodiments, the common controlling unit 130 can reduce the yaw drift by determining appropriate thrust commands for the non-faulty engines which compensate for this drift.
Assume the aircraft comprises N/2 right engines and N/2 left engines.
Assume one right engine is faulty. As a consequence, the propulsion provided by the left engines is higher than the propulsion provided by the right engines, thereby creating a yaw drift.
Assume the pilot (or the auto-throttle) has provided a thrust command which has a value of Y for the engines. The common controlling unit 130 can generate a thrust command equal to Y for the controllers of the right engines which are not faulty, and a thrust command equal to Y′, with Y′<Y, for the controllers of the left engines which are not faulty, in order to reduce the asymmetric propulsion. Value of Y′ is limited to the minimum thrust needed for the aircraft to fly in a safe manner.
This control can be performed in conjunction with the yaw command provided by the common controlling unit 130, or independently from it.
With the method of
Attention is now drawn to
Operations depicted in
Operation 450 comprises obtaining a command (such as a thrust or power command) from an actuating element (such as lever 110) controllable by a pilot, or from an auto-throttle of the aircraft. Operation 450 is similar to operation 300 of
Operation 455 comprises obtaining data representative of a failure of at least one engine Pj. When this data do not meet a safety threshold, this indicates that the failure exceeds a predetermined level, which requires taking a safety action.
For example, data representative of the fact that a temperature of the engine does not meet a safety threshold can be received (e.g. temperature can be higher than acceptable temperature, or can be lower than operating temperatures, etc.), thereby indicating that a failure is present in the engine.
In some embodiments, an alert can be received from the controller of the engine indicating that operating parameters of the engine do not meet a safety threshold and therefore are indicative of a possible failure of the engine.
Operation 460 can comprise generating by the common controlling unit 130 a thrust command for the controller of the faulty engine Pj which is different from the thrust command inputted by the pilot or by the auto-throttle at operation 450.
In particular, the common controlling unit 130 can instruct a controller of the faulty engine to reduce thrust of the faulty engine Pj at a value which is lower than the thrust command provided by the pilot or the auto-throttle.
According to some embodiments, the common controlling unit 130 can instruct a controller of the faulty engine Pj to set the faulty engine Pj in an “IDLE” state, in which the thrust is reduced, but in which the engine Pj is not yet shutdown.
This can be performed in order to avoid further deterioration of the engine's functioning, which could result in serious damage to the engine and/or to the aircraft.
According to some embodiments, operation 460 can be performed automatically by the common controlling unit 130, with, or without requiring intervention of the pilot.
Once the thrust of the faulty engine Pj is set at a reduced value, according to some embodiments, the method can comprise a waiting during a certain waiting period, such that thrust of the faulty engine Pj stabilizes at this value (operation 465).
According to some embodiments, the method can comprise (operation 470) raising an alert for the pilot (such as a “Cres-Alerting system” alert—CAS alert). This alert can be raised e.g. to indicate to the pilot that one of the engines has encountered a failure.
Indeed, as mentioned above, operations 455, 460 and 465 can be in some embodiments performed without intervention of the pilot, and therefore the pilot needs to receive an alert that an engine is faulty (and that the thrust of this engine has been set at a reduced level), so that he is made aware of the situation.
According to some embodiments, the common controlling unit 130 can trigger such an alert, by sending a command to an alerting system (e.g. a display, a sound speaker, etc.) of the aircraft to raise a visual and/or audio alert. In other embodiments, another processing unit of the aircraft can trigger this alert, by sending a command to an alerting system of the aircraft to raise a visual and/or audio alert.
At this stage, if the pilot or the auto-throttle modifies the desired thrust for the engines, the common controlling unit 130 generates a corresponding command to the respective controllers of the non-faulty engines in order to obtain the thrust desired by the pilot or the auto-throttle, and sends a command to the controller of the faulty engine in order to maintain a reduced value for the thrust of this faulty engine.
At operation 475, it can be checked whether failure of engine Pj is still present. This verification can be performed e.g. after a certain waiting period, once thrust of the engine Pj has stabilized at its reduced value.
According to some embodiments, this verification can be performed e.g. by checking if an alert indicative of a failure of the engine Pj is still present.
According to some embodiments, this verification can be performed by checking if data representative of the engine Pj still do not match a safety threshold.
If it is apparent that the failure has ceased, the method can comprise maintaining the engine at its reduced thrust value. Indeed, even if it is apparent that the failure has ceased, it cannot be assumed that the engine has returned to an operational state, and overcoming of the failure could be due to the fact that the thrust of the engine has been reduced. Therefore, for security reasons, thrust of the engine is maintained at a reduced value.
The method can further comprise operation 490, in which it can be determined whether another engine has encountered a failure which requires taking safety actions. At least some of operations 460 to 485 can be repeated for this other engine. This process can be repeated several times, for each engine which is detected as faulty.
If the failure is still present, the method can comprise (operation 480) raising a second alert (such as a “Crew-Alerting system” alert—CAS alert) to the pilot. This alert can be indicative of the fact that the failure of engine Pj is still present.
According to some embodiments, the common controlling unit 130 can trigger this second alert, by sending a command to an alerting system of the aircraft for raising a visual and/or audio alert. In other embodiments, another processing unit of the aircraft can trigger this second alert, by sending a command to an alerting system of the aircraft for raising a visual and/or audio alert.
The method can comprise (operation 485) performing a supervised shut-down of the faulty engine Pj. Indeed, since the failure is still present, this can indicate that there is a risk that the engine may explode, cause internal damage to the engine, or cause damage to the aircraft. For safety reasons, it can be decided to shut down the engine, as explained hereinafter.
In operation 485, upon instructions of the pilot, the faulty engine Pj is shut down. According to some embodiments, the pilot can activate a shut-down interface of the faulty engine Pj (such as a shut-down button specific to this engine) which sends a command to the controller of the engine for shutting down the engine. For example, the pilot can activate the “cut” position 183 present in the additional interface 180.
According to some embodiments, a shut-down instruction of the engine is provided by the pilot and transmitted to the common controlling unit 130 which transfers this command to the controller of the faulty engine Pj.
According to some embodiments, in order to avoid that the pilot inputs a shut-down instruction of an engine which is not faulty, the method can comprise verifying (e.g. by the common controlling unit 130) that the shut-down instruction of an engine matches with the engine which is faulty. If there is a match, the method can comprise transferring the shut-down instruction (e.g. by the common controlling unit 130), and if there is not a match, the method can comprise providing feedback to the pilot that his instruction does not comply with the current state of the engine, and ignoring the shut-down instruction of the pilot.
The method can further comprise operation 490, in which it can be checked whether another engine has encountered a failure which requires taking safety actions. At least some of operations 460 to 485 can be repeated for this other engine. This process can be repeated several times, for each engine which is detected as faulty.
According to some embodiments, if at least one engine is detected as faulty and therefore its thrust is reduced (or in some cases its thrust is set to zero), an operation can be performed to avoid a yaw drift of the aircraft due to its asymmetric propulsion, as explained with respect to operation 304 in
Attention is now drawn to
When the aircraft is on the ground, e.g. before take-off, the pilot generally needs to start each of the engines of the aircraft. In conventional aircraft, this process is performed by starting a first engine, setting its thrust to an IDLE state, and then to a higher thrust which is adapted to take-off. These operations are repeated for each engine, until all engines are operating at a thrust which is sufficient for take-off.
According to some embodiments, the method can comprise operation 491, in which a command is obtained which represents an instruction that engine Pj has to be switched on. This command can be generated following an instruction of the pilot using an interface such as a switching button present in the aircraft and associated to this engine Pj. For example, the “start” position 182 of the additional interface 180 can be activated.
This command can be obtained e.g. by the common controlling unit 130.
As mentioned above, according to some embodiments (see e.g.
At operation 492, following the instructions of the pilot to start engine Pj, the common controlling unit 130 can generate a command for the controller of engine Pj in order to increase thrust of the engine Pj at a first thrust value (e.g. this can correspond to an IDLE mode).
In some embodiments, this first thrust value can be different from the thrust command provided by the lever. In particular, in some embodiments, the first thrust value can be lower than the thrust command provided by the lever.
This can be due to the fact that the pilot has already switched on another engine in preparation for take-off, and therefore had to increase, using the lever, thrust of this engine to a higher value than that of IDLE mode. In other words, although the single lever may have provided a thrust command which is not adapted for starting engine Pj, the common controlling unit generates a different thrust command for the controller of engine Pj, which is adapted for starting gradually engine Pj.
After a stabilization period (see 493), the method can comprise verifying if the engine has managed to reach the first thrust value. If this is the case, the method can comprise moving to operation 494. If the engine did not manage to reach the first thrust value (e.g. because the engine is faulty), the method can comprise reverting back to operation 491, in which an instruction to start another engine can be obtained.
In operation 494, the common controlling unit 130 can instruct the controller of engine Pj to set thrust of engine Pj at a second thrust value which corresponds substantially to the thrust command of the lever. In other words, after the engine has been switched on and has stabilized at a first reduced thrust, the thrust of the engine is then increased to match with the thrust command provided by the actuator.
If all (non-faulty) engines run and have a thrust which matches with the thrust command provided by the lever, the method can stop operating. If at least one (non-faulty) engine has not yet been switched on, the method can revert back to operation 491, in order to repeat the process for another engine Pk, with k being different from j. Operations which follow operation 491 can be repeated similarly for engine PL.
These operations can be repeated until all (non-faulty) engines run and have a thrust which corresponds to the thrust command of the actuator.
In the embodiments above, examples have been described in which the common controlling unit 130 can generate a different thrust command than the one received from the pilot or auto-throttle. In some embodiments, the common controlling unit 130 can generate a thrust command which is higher than the thrust command provided by the single lever or by the auto-throttle. For example, the pilot can provide a reduced thrust command X during take-off of the aircraft (e.g. for reducing consumption of the engine, wherein X is less than the maximal thrust of the engine), and the common controlling unit 130 will generate a higher thrust command X′>X (for example if the engine is detected as faulty, and therefore, a higher thrust command should be provided to compensate for this malfunction).
Attention is now drawn to
When the aircraft is on the ground (in “taxi” mode), it is sometimes necessary to make the aircraft follow a non-linear trajectory, such as a curved or bent trajectory.
In some embodiments, the lever 110 controllable by the pilot comprises an interface allowing the pilot to provide a command representative of a level of curvature of the trajectory which is desired by the pilot for the aircraft.
According to some embodiments, this interface corresponds to a rotating member of the lever 110 (as explained e.g. with reference to
According to some embodiments, the interface can communicate data with the common controlling unit 130 but is not necessarily physically located on lever 110, and can be located in another place in the cockpit.
When the pilot rotates this rotating member (or uses another interface allowing inputting a command representative of the curvature of the trajectory of the aircraft), the lever 110 or the interface itself can generate a command (hereinafter “curvature command”) correlated to the level of rotation, and which represents the level of curvature of the trajectory of the aircraft which is desired by the pilot.
The method can comprise obtaining (operation 500), by the common controlling unit 130, the curvature command. In some embodiments, this curvature command can be provided by the auto-pilot of the aircraft.
In some embodiments, a single interface (e.g. single rotating member) is present and provides a single curvature command. Based on this single curvature command, the system is able to provide a plurality of thrust commands adapted for each controller of each engine for matching this curvature command.
The method can comprise (operation 510) generating, based on this curvature command, at least one first command usable by a controller of at least one right engine for controlling thrust of the right engine based at least on this first command, and at least one second command usable by a controller of at least one left engine for controlling thrust of the left engine based at least on this second command.
In particular, first command and second command can be selected to obtain thrust of the right engine and thrust of the left engine which cause the aircraft to follow a curved trajectory which matches the curvature command of the pilot (e.g. according to some matching criteria which indicates that the difference is below a predetermined threshold).
For example, assume the pilot has rotated the rotating member as shown in position 600 of
For example, the common controlling unit 130 can generate a first thrust command for a controller of a right engine, and a second thrust command for a controller of a left engine, wherein the second thrust command is higher than the first thrust command, thereby making the aircraft bend its trajectory as desired by the pilot.
In particular, the difference between the first thrust command and the second thrust command can be determined in order to reflect the level of curvature required by the pilot (which depends e.g. on the level of rotation of the rotating member, or more generally on the curvature command).
If the pilot inputs a curvature command which corresponds to a straight trajectory (no curvature), then the common controlling unit 130 can transfer the thrust command of the lever 110 to each of the controllers of the engines so that their thrust will match the thrust command.
In some embodiments, assume the right engine and the left engine currently operate at the same thrust X, which is equal to the thrust command inputted by the pilot through lever 110. Assume a curvature command is provided by the pilot in order to make the aircraft bend its trajectory.
The method can comprise making the thrust of the right and left engines vary around power X, in order to match the curvature command. For example, assume the curvature command indicates a left turn. Thrust of the right engine can be increased to X+ε and/or thrust of the left engine can be decreased to X−ε, wherein ε is calibrated to comply with the curvature command.
According to some embodiments, if one engine has been detected as faulty (see above various embodiments for detecting this faulty state), the common controlling unit 130 can take into account this information in order to compute the thrust required for the other engines to produce the desired curved trajectory.
For example, assume the pilot inputted a command to bend left, and that one of the right engines is faulty.
If the right engine was not faulty, it would be enough to maintain thrust of all left engines to X and to set thrust of all right engines to X+ε. However, since one of the right engines is faulty, this can be insufficient to obtain the desired curvature. Therefore, the common controlling unit 130 can generate a command so that thrust of all right engines is set to X+α, with α>>ε, in order to comply with the curvature command while a right engine is faulty.
This example is not limitative and other tuning of the thrust of the engines can be performed to match the level of curvature desired by the pilot.
This also applies to cases wherein the pilot inputs a command to follow a straight trajectory (no curvature) and one engine is detected as faulty. According to some embodiments, the common controlling unit 130 transmits a thrust command to each of the controllers of the non-faulty engines in order to compensate for the fact that at least one engine is faulty. For example, assume thrust command of the lever is X, that one right engine is faulty, and that the pilot desires a straight trajectory. According to some examples, thrust of left engines can be maintained to X, but thrust of the non-faulty remaining right engines can be increased to X+ε, in order to compensate for the presence of at least one faulty right engine.
In some embodiments, the lever 110 can provide both:
In this case, the commands generated by the common controlling unit 130 for the controllers of the engines can be tuned to reflect, as much as possible, both the command representative of the level of curvature desired by the pilot and the command representative of the thrust desired by the pilot or the auto-throttle for the engines.
For example, assume the pilot inputs a thrust command of X, which is transmitted by the common controlling unit 130 to the non-faulty engines.
Assume that the pilot also inputs a command reflecting a given level of curvature for the trajectory of the aircraft, then the common controlling unit 130 can create an asymmetric power of the engines around thrust command X (e.g. X+ε for at least some of the engines in order to match the desired level of curvature), thereby reflecting both the thrust command and the command pertaining to the curvature of the trajectory of the aircraft.
In some embodiments, the common controlling unit 130 can provide a thrust command which corresponds to a negative forward thrust, for one or more engines of the aircraft (in this case, E can be selected such as that X+ε is negative).
Attention is now drawn to
Operations depicted in
Assume the aircraft comprises engines P1 to PN, with N≥2.
The method can comprise obtaining (operation 700), by the common controlling unit 130, data representative of a fire of at least one engine Pj. Although the method is described with respect to the presence of a fire, the method can be applied similarly to other failures that request a security action to be taken. Examples of failure include low oil pressure, presence of significant vibrations, etc.
This data can be sent e.g. by at least one controller of the engine Pj, or by at least one sensor of the aircraft, or by at least one sensor operatively connected with the engine, or by a central processing unit of the aircraft, or by any other adapted system.
According to some embodiments, the common controlling unit 130 can instruct (operation 701) a controller of the faulty engine Pj to set the faulty engine Pj in an “IDLE” state, in which the thrust is reduced, but in which the engine Pj is not yet totally turned off. This can be performed automatically, without intervention of the pilot.
Since the common controlling unit 130 independently sends an appropriate command to the correct controller controlling this specific engine under fire, error by the pilot is avoided (such as deactivation by the pilot of an operational engine, instead of a faulty engine).
The common controlling unit 130 can monitor the failure (e.g. fire) present in the engine, and, if after a predetermined duration, the failure is still present, it can trigger an alarm to the pilot. According to some embodiments, a visual alarm and/or an audio alarm can be triggered. According to some embodiments, triggering of the alarm is not performed by the common controlling unit 130, and can be performed by another system of the aircraft. At this stage, the fire is still being monitored and has not yet been handled.
If the fire has ceased after the predetermined duration, the method can end (operation 708). The fact that the fire has ceased can be known e.g. by receiving new data from the system which detected the fire (this new data can be received e.g. by the common controlling unit 130), which indicates that the fire has ceased, or in some cases, by a visual inspection of the team crew.
If the fire has not ceased after the predetermined duration, the pilot can activate (operation 702) the “fire” (or more generally “emergency”) position 184 of the interface 180, which cuts off additional elements of the engine Pj or in communication with the engine Pj (such as fuel and hydraulic supply, etc.—this corresponds to an emergency shutdown). In some embodiments, the common controlling unit 130 can control that the pilot has deactivated the correct engine Pj, and if the pilot deactivates another engine, the common controlling unit 130 can ignore this command, to avoid an error. A corresponding alarm can be raised for the pilot.
In some embodiments, the common controlling unit 130 can activate by itself the “fire” (or more generally “emergency”) position 184.
In addition, the pilot can activate the discharge position 185 of the interface 180 for triggering a security action.
As a consequence of activation of the discharge position 185 of the interface 180, a security action can be triggered for handling the fire. For example, a firefighting agent (e.g. a powder) can be thrown from a firefighting device located in the vicinity of the engine, in order to extinguish the fire.
In some embodiments, the common controlling unit 130 can control that the pilot has ordered a security action for the correct engine Pj, and if the pilot has ordered this security action for another engine, the common controlling unit 130 can ignore this command, to avoid an error. A corresponding alarm can be raised for the pilot.
As shown in
For example, even if an alarm pertaining to a fire has been received by the common controlling unit 130, the pilot can still provide thrust commands using the lever 110 (the same applies to the auto-throttle).
The common controlling unit 130 can convert this command into commands which are adapted for each controller of each engine, as explained in the various embodiments above (operation 706).
In particular, the common controlling unit 130 can generate thrust commands which comply with the pilot input or the auto-throttle input for the non-faulty engines, and can generate a command which reduces the thrust of the faulty engine as explained in operation 701.
According to some embodiments, if the aircraft is on the ground, and data representative of a fire has been received for a given engine, the system can behave, with respect to commands pertaining to the curved trajectory of the aircraft on the ground, as explained in the embodiment described with reference to
It is to be noted that the various features described in the various embodiments may be combined according to all possible technical combinations.
It is to be understood that the invention is not limited in its application to the details set forth in the description contained herein or illustrated in the drawings. The invention is capable of other embodiments and of being practiced and carried out in various ways. Hence, it is to be understood that the phraseology and terminology employed herein are for the purpose of description and should not be regarded as limiting. As such, those skilled in the art will appreciate that the conception upon which this disclosure is based may readily be utilized as a basis for designing other structures, methods, and systems for carrying out the several purposes of the presently disclosed subject matter.
Those skilled in the art will readily appreciate that various modifications and changes can be applied to the embodiments of the invention as hereinbefore described without departing from its scope, defined in and by the appended claims.
Number | Date | Country | Kind |
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262426 | Oct 2018 | IL | national |
Filing Document | Filing Date | Country | Kind |
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PCT/IL2019/051065 | 9/26/2019 | WO | 00 |