Aircraft and method for modifying the installation configuration of an aircraft

Abstract

The invention relates to an aircraft (1) comprising an engine (10) housed in an engine compartment (22) and an engine control device (15) adapted to control at least one parameter of the engine (10), wherein the engine control device (15) is installed in the engine compartment (22), and a method for modifying the installation configuration of the aircraft (1).

Description

Technical Field

[0001] The present invention relates to an aircraft and a method for modifying the installation configuration of an aircraft. More particularly, the present invention relates to the installation of a device for sensing and controlling an engine in an aircraft. Background Art

[0002] Most commercial aircraft include an auxiliary power unit (APU), which is an engine mounted inside the aircraft's fuselage. This engine provides auxiliary power while on the ground or in the air.

[0003] To reduce aircraft fuel consumption and facilitate maintenance, APUs are being given more functionality. Consequently, additional sensing and control capabilities are required for these engines. However, adapting existing aircraft designs—whether already built or not—is not easy. Any new functionality requires new equipment, which in turn requires new cables, wiring harnesses, and other equipment. Therefore, introducing new functionality into existing aircraft is not always economically viable. Summary of the Invention

[0004] The object of the present invention is to provide an aircraft having new functionalities related to its internal engines.

[0005] The present invention is particularly intended to provide a retrofit solution for existing aircraft.

[0006] The object of the present invention is to provide a simple and effective method for providing new sensing and control functions of an engine (eg, an APU) for an aircraft.

[0007] The present invention aims to provide a simple method for modifying the configuration of an aircraft with minimal impact on all installed devices and cable harnesses.

[0008] The present invention provides an aircraft, comprising:

[0009] -engine,

[0010] - a compartment called the engine compartment, in which said engine is installed,

[0011] - an engine control device adapted to control at least one parameter of the engine,

[0012] Characterized in that the engine control device is installed in the engine compartment.

[0013] The engines may be mounted in compartments referred to as engine compartments, which are within fuselage sections referred to as engine sections. Throughout, features described in relation to engine compartments will apply equally to engine sections and vice versa.

[0014] The invention equally extends to an aircraft comprising:

[0015] -engine,

[0016] - a fuselage section, called the engine section, in which the engine is installed,

[0017] - an engine control device adapted to control at least one parameter of the engine,

[0018] The invention is characterized in that an engine control device is installed in the engine section.

[0019] The engine according to the present invention can be understood in a broad sense. Such an engine can be, for example, a gas turbine engine, an internal combustion engine, etc.

[0020] The invention also extends to a method of manufacturing an aircraft comprising an engine section adapted to accommodate an engine, the method comprising:

[0021] - Connect the jumper connectors to:

[0022] to the command cable, which is connected to the command device, and

[0023] to a first end of a transmission cable, the first end being adapted to transmit an electrical signal in the aircraft,

[0024] - Change the engine control unit to:

[0025] Installed in the engine section,

[0026] connected to the second end of the transmission cable, and

[0027] • Connects to a sensing cable which is connected to the sensor.

[0028] The aircraft may further comprise command means adapted to output commands to the engine control means.

[0029] The engine control device may be adapted to control at least one component of the engine, such as an injector. The engine control device receives a command signal from the command device and transmits a corresponding control signal to one or more components of the engine. The engine control device may be adapted to process the command signal and generate a control signal.

[0030] The command device may be activated by a person or a computer. The command device may be a computer. The command device may thus include a human-computer interface, such as a joystick or a microphone. The command device may also include a computer interface.

[0031] The output of the command device can be connected to the input of the engine control device.The command device and the engine control device are connected to each other via a power cable.

[0032] The aircraft may further comprise a jumper connector for electrically connecting at least one power cable connected to the command device to a power cable connected to the engine control device.

[0033] An electrical power cable, referred to as a command cable, connected to the command device may be adapted to transmit electrical command signals between the command device and the engine control device.

[0034] The aircraft may include a sensor cable connected to the sensor and adapted to transmit an electrical sensing signal. In particular, the aircraft may include at least one sensor cable between the sensor and an engine control unit. The sensor may be adapted to sense a parameter related to the engine or an engine compartment.

[0035] The command cable can be used to transmit information signals between the engine control unit and the command unit. The engine control unit can control the APU based on its own software and data received from the APU's sensor(s). The engine control unit can output command signals to one or more engine control units. In this embodiment, the engine control unit may only send status signals to the command unit, wherein the status signals contain status information based on one or more sensor data and / or one or more actuator states.

[0036] The aircraft may further comprise a transmission cable adapted to transmit electrical signals along one or more fuselage sections of the aircraft. The transmission cable may in particular have one end in an engine section or in a gap between an engine section and an adjacent fuselage section, so as to be able to transmit electrical signals to or from the engine section.

[0037] The jumper connector may be adapted to replace an existing engine control device.The jumper connector may be adapted to connect the command cable to the transmission cable.

[0038] Thus, in the previous configuration, the aircraft command and sensing lines between the command device and the engine may include, in the following order: a command device, one or more command cables, an engine control device, one or more transmission cables, one or more sensing cables, the sensing cables being connected to at least some of the transmission cables and one or more sensors; the aircraft according to the present invention and obtained by the method according to the present invention may include: a command device, one or more command cables, a jumper connector, one or more transmission cables, an engine control device, one or more sensing cables and one or more sensors.

[0039] Thus, an aircraft's engine control unit can be relocated from a fuselage section different from the engine section to the engine section. Furthermore, a new engine control unit with additional inputs can be installed in the engine section. The present invention allows for the addition of additional sensors to the engine or engine section and their connection to the new engine control unit without having to install additional transmission cables in the fuselage. In practice, adding transmission cables is a complex task, as the command unit is typically located in the nose section of the aircraft, while the engine section housing the APU is typically located in the tail section of the aircraft. Consequently, the transmission cables are particularly long, and replacing these cables or adding new ones would require significant work on the aircraft.

[0040] The present invention allows for simple implementation into aircraft production lines, or simple retrofitting of existing aircraft, while adding new functionality to engine sensing and control.

[0041] The engine compartments may be housed in fuselage sections known as engine sections.

[0042] In some embodiments of the invention, the engine section may form an engine compartment.

[0043] The command device may be installed in a fuselage section of the aircraft that is different from the engine section.

[0044] In particular, when the engine is installed in an engine compartment, the command device can still be installed in a fuselage section different from the engine section in which the engine compartment is installed.

[0045] The engine may include at least one sensor connected to the engine control unit.

[0046] The engine may include a plurality of sensors. Such sensors may be, for example, speed sensors, oil level sensors, temperature sensors, pressure sensors, etc.

[0047] An aircraft may include sensors located in an engine section and connected to an engine control unit. Such sensors may not sense parameters related to the engine, but rather parameters related to the engine section, such as the temperature in the engine section, the presence of smoke in the engine section, etc.

[0048] The engine may include one or more actuators. Such actuators may be, for example, valve actuators, intake actuators, etc.

[0049] An aircraft may include actuators, such as air intake actuators, located in an engine section and connected to engine controls.

[0050] The engine control unit may be adapted to receive a wireless signal from the at least one sensor.

[0051] Wireless sensors can be used to facilitate the installation of additional sensors or replacement of sensors.The proximity of the engine control devices placed in the engine section allows the use of low power, short range wireless technologies.

[0052] The engine compartment can be isolated from its surroundings by a fire wall.

[0053] The engine compartment may be enclosed in a fire wall. The fire wall may define the boundaries of the engine compartment. The engine compartment may be mounted within and thermally insulated from the surrounding engine section.

[0054] Alternatively or in combination, the engine section is separated from the adjacent fuselage section by a fire wall.

[0055] The engine control device according to the present invention is installed in the fire wall of the engine compartment.

[0056] The engine control unit according to the present invention can be fire-resistant. In particular, the engine control unit according to the present invention can include a dedicated fireproof housing. The engine control unit installed in the engine compartment is thus adapted to withstand fire conditions, allowing it to continue to function properly.

[0057] The engine control device may be adapted to transmit data to the command device.

[0058] The engine control device may be adapted to receive sensory data from one or more sensors adapted to sense at least one parameter associated with the engine or an engine section. The engine control device may be adapted to transmit such sensory data to another device, such as a command device. The engine control device may be adapted to process such sensory data and transmit a corresponding reporting signal to the other device.

[0059] The invention extends to a method for modifying the installation configuration of an aircraft comprising a compartment known as an engine compartment in which an engine is installed, in which method:

[0060] - disconnecting an engine control device connected to a command cable and a first end of a transmission cable, from both the command cable and the transmission cable, said command cable being adapted to be connected to a command device and the first end being adapted to transmit electrical signals in the aircraft,

[0061] - Connect the jumper connector between the command cable and the transmission cable instead of the engine control unit,

[0062] - Connecting the engine control unit to the second end of the transmission cable and to a sensing cable connected to the sensor.

[0063] The engine control device connected between the second end of the transmission cable and the sensing cable may be the same engine control device removed from its position between the command cable and the first end of the transmission cable, or may be another engine control device of, for example, a new generation.

[0064] This approach allows an aircraft to be modified to increase its capabilities. For example, it allows additional sensors to be added to an engine section without having to install new transmission cables along the aircraft fuselage.

[0065] Before the engine control unit is connected to the transmission cable and the sensing cable, the transmission cable may be disconnected from the sensing cable.

[0066] The engine control unit is located between the transmission cable and the sensing cable.

[0067] The method according to the invention may further comprise installing the engine control unit in the engine compartment.

[0068] The method according to the invention may further comprise adding at least one sensor in the engine section and connecting it to an input of the engine control unit.

[0069] As mentioned, such additional sensors may have cables or may be wireless. The installation of new engine control units allows for the installation of such additional sensors. Indeed, engine control units with more inputs than previously installed in remote locations within the aircraft may be conceived and installed in the engine section.

[0070] The invention also extends to other possible combinations of the features described in the above description and in the following description with reference to the accompanying drawings. In particular, the invention extends to an aircraft section comprising the features relating to an aircraft and / or a method for modifying an aircraft; the invention extends to an aircraft comprising the features relating to a method for modifying an aircraft; and the invention extends to a method for modifying an aircraft comprising the features described in relation to an aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0071] In the following description, certain exemplary embodiments and aspects of the present invention are described with reference to the accompanying drawings.

[0072] Figure 1 is a schematic representation of an aircraft according to an embodiment of the invention in a cross section along the longitudinal axis of the aircraft.

[0073] Figure 2 is a schematic representation of the control and sensing circuitry of an engine in an aircraft before application of the method according to the invention.

[0074] Figure 3is a schematic representation of the control and sensing circuitry for an engine in an aircraft according to the present invention.

[0075] Figure 4 is a schematic representation of the method according to the invention. DETAILED DESCRIPTION

[0076] exist Figure 1 In FIG, an aircraft 1 is schematically represented.

[0077] The aircraft comprises a fuselage 19 made from a plurality of fuselage sections. In particular, the aircraft comprises a nose section 20 located at the front of the aircraft.

[0078] The aircraft includes an engine 10 , such as an auxiliary power unit (APU). The engine 10 is housed in an engine compartment 22 .

[0079] The engine compartment 22 is located in a fuselage section called the engine section 11, which is located toward or at the rear of the aircraft. The engine section 11 is separated from the nose section 20 by one or more intermediate fuselage sections 21. The engine section is separated from the adjacent forward section by a wall 12. Wall 12 may be a pressure bulkhead or a fire wall.

[0080] The engine compartment 22 includes a firewall 23. The firewall limits the volume in the engine compartment 22 in which the APU 10 is installed.

[0081] The aircraft comprises an engine control unit 15 located in an engine compartment 22. The engine control unit 15 is connected to at least one controllable element 26 of the APU (e.g. an APU actuator) via a control cable 27. The engine control unit 15 is also connected to sensors 24 of the APU 10 via sensing cables 18.

[0082] In this embodiment, the engine control unit 15 is also connected to the wireless sensor 25 via a wireless connection. The engine control unit 15 thus includes a wireless communication port. The proximity of the engine control unit and the APU, both mounted within the engine compartment 22, allows for wireless communication between one or more sensors 25 in the engine or engine compartment without interfering with or being interfered with by other wireless communications. Furthermore, low-energy, short-range wireless communication protocols may be used. The engine control unit 15 may also be wirelessly connected to one or more controllable components of the APU 10.

[0083] The aircraft comprises a command device 13 located in the nose section. This command device 13 may be an onboard computer. The command device is adapted to output command signals to an engine control device 15. The engine control device is adapted to convert this command signal into a control signal for the controllable elements it controls.

[0084] The engine control unit is connected to the command unit 13 via one or more cables. Figure 1 In an embodiment of the present invention, the command device is connected to the engine control device in the following manner:

[0085] command cables 16 connected at a first end to the command device 13 and at a second end to the jumper connector 14 ,

[0086] - transmission cables 17 , which are connected at a first end to the jumper connector 14 and at a second end to the engine control unit 15 ,

[0087] A jumper connector 14 adapted to electrically connect the command cable 16 to the transmission cable 17 .

[0088] In this embodiment, the transmission cable 17 terminates at a connector across the wall 12. The engine control unit 15 is connected to this connector.

[0089] In this embodiment, the jumper connector 14 is located in one of the intermediate fuselage sections 21 .

[0090] According to the method of the present invention, jumper connector 14 can replace the engine control unit in its previous location, with the engine control unit installed in the engine compartment. Consequently, there is no need to modify or add to the aircraft's wiring, particularly command cables 16 or transmission cables 17. Engine control unit 15 can now take on additional functions, such as receiving signals from additional sensors, without requiring additional wiring in center fuselage section 21.

[0091] exist Figure 2 , the configuration of the aircraft before modification by the method according to the invention is shown, wherein the command device 13 is connected to the engine control device 15 via a command cable 16. The engine control device is connected to the sensors 26 and the controllable elements 24 of the APU 10 via sensing cables 27 or control cables 18, respectively, and transmission cables, both of which are connected to the transmission cables 17 at a connection interface on the wall 12 of the engine section 11.

[0092] exist Figure 3 In FIG. 1 , the configuration of the aircraft according to the invention is shown, which can be realized by applying the method according to the invention to Figure 2 In this configuration, similar to Figure 1 The configuration, Figure 2The original engine control unit 15 has been relocated to the engine section 11. The engine control unit 15 may have been replaced by a new engine control unit 15. The new engine control unit may thus include additional functionality, such as additional inputs for sensors and / or wireless communication. The new engine control unit may also be fireproof.

[0093] The engine control unit previously installed in the middle fuselage section is replaced by a jumper connector 14 to ensure continuity of signal transmission between the command cable 16 and the transmission cable 17 .

[0094] The engine control device 15 is connected to the transmission cable 17 at a connection interface of the wall 12 , while the sensing cable 27 and the control cable 18 are directly connected to the engine control device 15 .

[0095] Furthermore, in this embodiment, the APU has been equipped with additional wireless sensors 25 adapted to communicate with the new engine control device 15 installed in the engine section 11 .

[0096] The steps of the method according to the invention are schematically represented in Figure 4 The following steps can be performed in this order or in a different order.

[0097] In a first step 41, the intermediate fuselage section is mounted Figure 2 The engine control unit is shown disconnected from the command cable 16 and the transmission cable 17 .

[0098] In a second step 42 , the jumper connector 14 is connected between the command cable 16 and the transmission cable 17 .

[0099] In a third step 43 , the sensing cable 27 and the control cable 18 are disconnected from the transmission cable 17 .

[0100] In a fourth step 44 , the engine control unit 15 is installed in the engine compartment 22 .

[0101] In a fifth step 45 , the engine control unit 15 is connected on one side to the transmission cable 17 and on the other side to the sensing cable 27 and the control cable 18 .

[0102] In a sixth step 46 , an additional sensor 25 is added in the engine compartment 22 and connected to the engine control unit 15 by a cable or wirelessly.

[0103] This method allows obtaining an aircraft 1 according to the invention from an already existing aircraft.

[0104] The present invention is not limited to the specific embodiments disclosed herein as examples. The present invention also encompasses other embodiments not explicitly described herein, which may include different combinations of features described herein.

Claims

1. A method for modifying the installation configuration of an aircraft (1), said aircraft comprising a compartment known as an engine compartment (22) in which an engine (10) is installed, wherein: - disconnecting an engine control device (15) connected to a first end of a command cable (16) and a transmission cable (17), both of which are adapted to be connected to a command device (13) and which are adapted to transmit electrical signals in the aircraft, - connecting a jumper connector (14) between the command cable (16) and the transmission cable (17) instead of the engine control unit (15), - installing an engine control unit (15) in the engine compartment (22) and connecting the engine control unit (15) to the second end of the transmission cable (17) and a sensing cable (18) connected to sensors (24, 25).

2. The method according to claim 1, wherein Before the engine control device (15) is connected to the transmission cable (17) and the sensing cable (18), the transmission cable (17) is disconnected from the sensing cable (18).

3. The method according to claim 1 or 2, further comprising outputting a command from the command device (13) to the engine control device (15).

4. The method according to claim 1 or 2, further comprising: At least one sensor (24, 25) is added to the engine compartment (22) and connected to the input of the engine control unit (15).

5. The method according to claim 3, further comprising: At least one sensor (24, 25) is added to the engine compartment (22) and connected to the input of the engine control unit (15).

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