Device and method for remotely controlling an air-conditioning unit for an aircraft

Abstract

The invention relates to a control module (30) for remotely controlling an air-conditioning unit for an aircraft, the control module (30) being configured to be mounted on a connector (230) of a duct (20) suitable for connecting the air-conditioning unit to the aircraft, the connector (230) being configured to be connected to a low-pressure air inlet of the aircraft, the control module (30) comprising at least one piezoelectric element (310) configured to generate an electric charge when the piezoelectric element (310) is subjected to mechanical deformation, the electric charge defining a voltage representative of control information for the air-conditioning unit, and a transmitter (320) configured to transmit, on the basis of the electric charge, a radio-frequency signal comprising the control information to a receiver of the air-conditioning unit in order to control the air-conditioning unit.

Description

Device and method for remotely controlling an aircraft air conditioning unit

[0001] The present invention relates to the field of aircraft and more particularly concerns a module and a method for remotely controlling an aircraft air conditioning unit.

[0002] When a passenger aircraft is parked between flights on the tarmac of an airport, it is known to use an air conditioning unit called an ACU (for "Air Conditioning Unit") or PCA (for "Pre Condition Air") to provide cabin air conditioning from the ground.

[0003] The air conditioning unit generates a flow of cooled or heated air that is delivered to the aircraft via an insulated flexible duct. The duct terminates in a connector that provides a connection to the aircraft's low-pressure air system.

[0004] The air conditioning unit includes a control interface usable by an operator, which may be in the form of buttons and a screen or directly a touch screen.

[0005] To operate the air conditioning unit, one operator pulls the duct towards the aircraft and connects the connector. Then, a second operator controls the air conditioning unit via the control interface to air-condition the aircraft. Once the air conditioning process is complete, the first operator disconnects the connector and removes the duct. A single operator can perform all the steps, but this requires multiple trips back and forth between the aircraft and the air conditioning unit, which is time-consuming and tedious.

[0006] Therefore, there is a need for a simple and effective solution to remedy at least some of these drawbacks.

[0007] To this end, the invention first relates to a remote control module for an aircraft air conditioning unit, said control module being configured to be mounted on a connector of a duct adapted to connect said air conditioning unit to said aircraft, said connector being configured to be connected to a low-pressure air inlet of the aircraft, said control module comprising:

[0008] - at least one piezoelectric element configured to generate an electrical charge when said piezoelectric element is subjected to mechanical deformation, said electrical charge defining an electrical voltage representative of a control information of the air conditioning unit,

[0009] - a transmitter configured to emit from said electrical load a radio frequency signal, for example in the form of a pulse, containing said control information to a receiver of the air conditioning unit in order to control said air conditioning unit.

[0010] The control module according to the invention constitutes a command transmitter enabling simple, efficient, and rapid remote control of an air conditioning unit. By using the electrical energy generated by the mechanical deformation of the piezoelectric element to create a voltage representing a control signal and transmitting said signal as a radio frequency signal, the remote control does not require an onboard battery or an external power supply (e.g., a power cable connected to mains electricity or an external battery) to operate (i.e., the control module does not have a battery to transmit the signals containing the control information), thus avoiding the inconveniences associated with recharging or replacing such a battery, which is advantageous in an airport environment.

[0011] In one embodiment, the control module includes at least one switch, each switch being connected to at least one piezoelectric element and being configured to mechanically switch between a first position and a second position, said switching causing a deformation of said at least one piezoelectric element and the emission of the radio frequency signal corresponding to the activation of the switch.

[0012] Preferably, the signal sent is an on / off command: for example, switching the air conditioning unit on or off, starting or stopping the air conditioning, switching to a "hot air" or "cold air" mode, lighting a status beacon to inform the aircraft pilot, etc.

[0013] For example, in one embodiment, activating a switch on the control module corresponds to either switching the air conditioning unit on or switching it off. In other words, in this case, the same command, and therefore the same control information, triggers either switching the air conditioning unit on or switching it off, depending on whether the air conditioning unit was previously off or running.

[0014] For example, in one embodiment, activating a switch on the control module corresponds to either starting or stopping the air conditioning. In other words, in this case, the control signal triggers either the start or the stop of the air conditioning, depending on whether the air conditioning was previously inoperative or activated.

[0015] For example, in one embodiment, activating a switch on the control module corresponds to switching between a "hot" mode or a "cold air" mode. In other words, in this case, the control information triggers the activation of a "hot air" mode or a "cold air" mode.

[0016] For example, in one embodiment, the activation of a control module switch causes a flow rate and air pressure setpoint to be switched on or off at the outlet of the air conditioning unit, said setpoint corresponding to the flow rate and air pressure characteristics of the aircraft (or family of aircraft) having the same flow rate and air pressure setpoints.

[0017] For example, in one embodiment, the activation of a control module switch causes a temperature setpoint at the output of the air conditioning unit to be switched on or off.

[0018] For example, in one embodiment, activating a switch on the control module triggers the illumination of a visual and / or audible status beacon, for instance, to inform the control module operator and / or the aircraft pilot of the ongoing action, or deactivates the illumination of said status beacon. In other words, in this case, the control signal triggers the activation or deactivation of the status beacon.

[0019] Activating the switch may trigger one or more consecutive functions. For example, activating the switch may successively cause the air conditioning unit to start, followed by the air conditioning itself starting, followed by a warning light illuminating to indicate that the air conditioning is in operation.

[0020] Alternatively or in addition, at least one piezoelectric element is positioned within the internal space defined by the connector so as to be placed in the airflow circulating in the duct and is configured to be mechanically deformed when said at least one piezoelectric element is subjected to a variation in a parameter of the air circulating in the duct. In other words, in this case, the at least one piezoelectric element is a sensor mounted in the airflow at the connector, and the control information is a measurement.

[0021] The variation of a parameter of the air circulating in the duct, and therefore through the connector, can, for example, be a variation in air pressure, a variation in the pressure exerted on at least one piezoelectric element by increasing or decreasing the airflow to measure dynamic and / or static pressure, or a variation in air temperature, for example, by measuring the change in the sensor's volume. In other words, in this case, the control information relates respectively to the air pressure of the flow, the airflow rate, or the airflow temperature, so as to allow control of the air conditioning unit, for example, to reduce or increase the airflow rate or the air temperature.

[0022] In any embodiment, the activation of a function at the level of the air conditioning unit may result in the activation of a light or sound signal to the operator so that he knows remotely in which mode the air conditioning unit is operating.

[0023] The invention also relates to an aircraft air conditioning duct assembly, said assembly comprising a duct and a control module as previously described, said duct comprising a first end configured to be connected to an air conditioning unit and a second end comprising a connector configured to be connected to a low-pressure air inlet of said aircraft, said control module being mounted on said connector.

[0024] The invention also relates to a system comprising an aircraft air conditioning unit, an aircraft air conditioning duct and a control module as previously described, said duct comprising a first end connected to said air conditioning unit and a second end comprising a connector configured to be connected to a low pressure air inlet of said aircraft, the control module being mounted on said connector.

[0025] In one embodiment, the system further comprises an aircraft and the second end of the duct is connected to a low-pressure air inlet of said aircraft.

[0026] The invention also relates to a method for remotely controlling an aircraft air conditioning unit by means of a control module as described above, said control module being configured to be mounted on a connector of a duct adapted to connect said air conditioning unit to said aircraft, said connector being configured to be connected to a low-pressure air inlet of the aircraft, said method comprising the steps of:

[0027] - mechanical deformation of at least one piezoelectric element of the control module,

[0028] - generation, as a result of said mechanical deformation, by said at least one piezoelectric element, of an electric charge, said electric charge defining an electric voltage representative of a control information of the air conditioning unit,

[0029] - emission by the transmitter, from said electrical charge, of a radio frequency signal containing said control information to a receiver of the air conditioning unit in order to control said air conditioning unit.

[0030] According to one aspect of the invention, the method comprises the receiver receiving the emitted signal, extracting the control information, and controlling the air conditioning unit from said extracted control information.

[0031] For example, in one embodiment, the extracted control information triggers the starting or stopping of the air conditioning unit.

[0032] For example, in one embodiment, the extracted control information triggers the start or stop of the air conditioning.

[0033] For example, in one embodiment, the extracted control information leads to the activation of a "hot air" mode or the activation of a "cold air" mode.

[0034] For example, in one embodiment, the extracted control information causes a light and / or sound status beacon to be switched on or off to inform the aircraft operator and / or pilot.

[0035] For example, in one embodiment, the extracted control information causes the switching on or off of an air flow and pressure setpoint at the outlet of the air conditioning unit, corresponding to the characteristics of an aircraft or a family of aircraft having the same air flow and pressure setpoints.

[0036] For example, in one embodiment, the extracted control information causes a temperature setpoint to be switched on or off at the outlet of the air conditioning unit.

[0037] Other features and advantages of the invention will become apparent upon reading the following description. This description is purely illustrative and should be read in conjunction with the accompanying drawings, in which:

[0038] The diagram schematically illustrates one embodiment of the system according to the invention.

[0039] The diagram schematically illustrates an example of a sheath in which a connector includes a control module according to the invention.

[0040] The diagram schematically illustrates a first embodiment of the control module according to the invention.

[0041] The diagram schematically illustrates a second embodiment of the control module according to the invention.

[0042] The diagram schematically illustrates a third embodiment of the control module according to the invention.

[0043] Laillust schematically illustrates a first embodiment of the process according to the invention.

[0044] Laillust schematically illustrates a second embodiment of the process according to the invention.

[0045] The diagram schematically illustrates an example of an aircraft air conditioning system 1 for aircraft 2 according to the invention.

[0046] System 1

[0047] System 1 includes an air conditioning unit 10, a duct 20 and a control module 30 ().

[0048] Air conditioning unit 10

[0049] The air conditioning unit 10, known as the ACU (Air Conditioning Unit), is configured to generate an airflow at a predefined temperature to cool, heat, or ventilate the cabin of aircraft 2 when said aircraft 2 is on the ground.

[0050] With reference to the, the air conditioning unit 10 includes a management module 110 and a receiver 120.

[0051] The control module 110 is configured to receive commands enabling the generation of airflow. These commands can be received directly from buttons activated by an operator on the air conditioning unit 10 via a control interface (not shown for clarity) or from the receiver 120.

[0052] Sheath 20

[0053] With further reference to the, the duct 20 is in the form of a long flexible or semi-rigid sleeve, for example between 10 and 30 meters, allowing the airflow generated by the air conditioning unit 10 to be conveyed to the aircraft 2.

[0054] The duct 20 is connected at one end 210 to the air conditioning unit 10 and includes at its other end 220 a connector 230, visible on the, configured to be connected to a low pressure air inlet (not visible) of the aircraft 2, in a manner known per se.

[0055] Control Module 30

[0056] With reference to the, the control module 30 is mounted on the connector 230 of the sheath 20 and includes at least one piezoelectric element 310 and one emitter 320.

[0057] Each piezoelectric element 310 is configured to generate an electrical charge when said piezoelectric element 310 is subjected to mechanical deformation.

[0058] The electrical charge defines an electrical voltage representative of a control information of the air conditioning unit 10.

[0059] The transmitter 320 is configured to emit, from the electrical charge generated by a piezoelectric element 310 to which it is connected, a radio frequency signal containing the control information to the receiver 120 of the air conditioning unit 10 in order to control said air conditioning unit 10.

[0060] Three examples of control module 30 will now be described.

[0061] First form of implementation of the control module 30

[0062] In this embodiment, illustrated on the, the control module 30 includes a switch 330 connected to a piezoelectric element 310 (but could include several switches 330 connected to as many piezoelectric elements 310).

[0063] The switch 330 is configured to mechanically toggle between a first position and a second position, said toggle causing a deformation of said at least one piezoelectric element 310 corresponding to the activation of the switch 330.

[0064] Preferably, the transition from the first position to the second position results in the emission of the radio frequency signal and the automatic return of switch 330 to the first position, for example by means of a spring-type return means.

[0065] In this case, each activation of switch 330 (i.e., each press of switch 330) generates the same deformation of the piezoelectric element 310, and therefore the same voltage and radio frequency signal. Switch 330 can then be used in an "on / off" mode, in which it activates or deactivates a function. The air conditioning unit 10 always receives the same radio frequency signal and activates the function (for example, switching it on) if it was previously deactivated, or deactivates the function if it was previously activated.

[0066] Alternatively, switch 330 can remain locked in the second position and a new activation of switch 330 (i.e. a new press on switch 330), which would cause it to return to the first position, could trigger the same function or another function, for example by generating a different deformation of the piezoelectric element 310 and therefore a different voltage and a different radio frequency signal.

[0067] Activating switch 330 can correspond to switching on the air conditioning unit 10 or switching off the air conditioning unit depending on whether the air conditioning unit 10 was respectively off or in operation.

[0068] Activating switch 330 can correspond to starting or stopping the air conditioning depending on whether the air conditioning was respectively off or in operation.

[0069] Activating switch 330 can correspond to switching to a "hot" mode or switching to a "cold air" mode depending on whether the cold or hot mode was previously switched on.

[0070] In addition to the implementation of an on / off function, the activation of switch 330 may also cause a light and / or sound status beacon to be activated, for example to inform the operator and / or pilot of aircraft 2 of the activated state of the air conditioning unit 10 (i.e. generation of an airflow), or to the deactivation of said status beacon.

[0071] Second embodiment of control module 30

[0072] In this embodiment, illustrated in the figure, the control module 30 includes a piezoelectric element 310 disposed in the internal space defined by the connector 230 so as to be placed in the airflow circulating in the duct 20 and configured to be mechanically deformed when said piezoelectric element 310 is subjected to a variation of a parameter of the air circulating in the duct 20, the variations in the deformation of the piezoelectric element 310 being representative of the variations of said parameter, the transition from the inactive state to the active state being representative of a first command to be sent and the transition from the active state to the inactive state being representative of a second command to be sent.

[0073] The parameter variation may be a variation in air pressure, a variation in pressure exerted on at least one piezoelectric element by increasing or decreasing an air flow rate to measure dynamic pressure and / or static pressure, or a variation in air temperature.

[0074] The control module 30 could include several piezoelectric elements 310 arranged in the internal space defined by the connector 230 to measure several different parameters.

[0075] Third embodiment of control module 30

[0076] This form of realization, illustrated on the, corresponds to a combination of the first form of realization and the second form of realization.

[0077] In this embodiment, the control module 30 includes a switch 330 (but could include several switches 330), a first piezoelectric element 310 and a second piezoelectric element 330.

[0078] The switch 330 is connected to the first piezoelectric element 310 and is configured to switch mechanically between a first position, corresponding to an inactive state in which the first piezoelectric element 310 is undeformed, and a second position, corresponding to an active state in which the first piezoelectric element 310 is deformed and which is representative of a command to be sent.

[0079] The second piezoelectric element 330 is arranged in the internal space defined by the connector 230 so as to be placed in the airflow circulating in the duct 20 and configured to be mechanically deformed when said second piezoelectric element 330 is subjected to a variation of a parameter of the air circulating in the duct 20, the variations in the deformation of the second piezoelectric element 330 being representative of the variations of said parameter.

[0080] Examples of implementation

[0081] Example implementing the first form of realization()

[0082] In this example, switch 330 allows the air conditioning unit 10 to be switched on or off to generate an airflow.

[0083] First, with reference to the diagram, an operator located at the connector activates switch 330 to start the air conditioning unit 10 in step E0. This activation causes, in step E1, a mechanical deformation of the piezoelectric element 310, which generates an accumulation of electrical charge in the piezoelectric element 310 in step E2. The electrical charge defines an electrical voltage representing an activation command for the air conditioning unit 10.

[0084] The transmitter 320 transmits in a step E3, using the voltage defined by the electrical charge generated by the switching of the switch 330, a radio frequency signal including the activation command to the receiver 120 of the air conditioning unit 10.

[0085] The receiver 120 receives the signal emitted in a step E4 then extracts the activation command in a step E5 and transmits it in a step E6 to the management module 110 which then activates the generation of an airflow to aircraft 2 in a step E7.

[0086] Activating the generation of an airflow, or any other function, preferably leads in a step E8 to the activation of light or sound beacons enabling the operator and / or pilot of aircraft 2 to know that the air conditioning unit 10 has activated the function and preferably to know which function is activated at the level of the air conditioning unit 10.

[0087] Example implementing the second form of realization()

[0088] In this example, the piezoelectric element 310 allows the air pressure variations in the duct 20 to be measured.

[0089] In reference to step E1, a variation in the pressure of the air circulating in the duct 20 causes a mechanical deformation of the piezoelectric element 310, which generates the accumulation of an electrical charge at the piezoelectric element 310 in step E2. The electrical charge defines an electrical voltage representing an activation command of the air conditioning unit 10.

[0090] The transmitter 320 emits in a step E3, using the voltage defined by the electrical charge generated by the switching of the switch 330, a radio frequency signal containing information on pressure variation proportional to the mechanical deformation to the receiver 120 of the air conditioning unit 10.

[0091] The receiver 120 receives the signal emitted in a step E4 then extracts the information in a step E5 and transmits it in a step E6 to the management module 110 which can then adapt the speed or flow rate of the airflow generated for aircraft 2 in a step E7, this adaptation being proportional to the observed pressure variation.

[0092] The adaptation of the speed or flow rate of the generated airflow, or of any other function, preferably in a step E8 triggers the activation of light or sound beacons enabling the operator and / or pilot of aircraft 2 to know that the air conditioning unit 10 has activated the function and preferably to know which function is activated at the level of the air conditioning unit 10.

[0093] An example of the implementation of the third form of realization corresponds to a combination of the example of the first form of realization and the example of the second form of realization.

[0094] The control module 30 according to the invention thus enables the remote control of an air conditioning unit 10 in a simple, fast, reliable, and efficient manner, thereby eliminating the need for an operator at the air conditioning unit 10 and saving time. Furthermore, the control module 30 is inexpensive and does not require a battery for power storage, since the energy needed to send commands via radio frequency signal is supplied by the mechanical deformation of the piezoelectric element(s) 310.

Claims

Remote control module (30) of an air conditioning unit (10) for an aircraft (2), said control module (30) being configured to be mounted on a connector (230) of a duct (20) adapted to connect said air conditioning unit (10) to said aircraft (2), said connector (230) being configured to be connected to a low-pressure air inlet of the aircraft (2), said control module (30) comprising: - at least one piezoelectric element (310) configured to generate an electrical charge when said piezoelectric element (310) is subjected to mechanical deformation, said electrical charge defining an electrical voltage representative of a control information of the air conditioning unit (10),- a transmitter (320) configured to transmit from said electrical load a radio frequency signal containing said control information to a receiver (120) of the air conditioning unit (10) in order to control said air conditioning unit (10). Control module (30) according to claim 1, said control module (30) comprising at least one switch (330), each switch (330) being connected to at least one piezoelectric element (310) and being configured to mechanically switch between a first position and a second position, said switching causing a deformation of said at least one piezoelectric element (310) corresponding to the activation of the switch (330). Control module (30) according to the preceding claim, wherein the activation of at least one switch (330) corresponds to the switching on of the air conditioning unit (10) or to the switching off of the air conditioning unit (10). Control module (30) according to any one of claims 2 or 3, wherein the activation of at least one switch (330) corresponds to the starting or stopping of the air conditioning. Control module (30) according to any one of claims 2 to 4, wherein the activation of at least one switch (330) corresponds to the activation of a "hot" mode or the activation of a "cold air" mode. Control module (30) according to any one of claims 2 to 4, wherein the activation of at least one switch (330) causes the switching on or off of an air flow and pressure setpoint at the outlet of the air conditioning unit (10), said setpoint corresponding to the air flow and pressure characteristics of the aircraft (2). Control module (30) according to any one of claims 2 to 6, wherein the activation of at least one switch (330) causes the switching on or off of a temperature setpoint at the output of the air conditioning unit (10). Control module (30) according to any one of claims 2 to 7, wherein the activation of at least one switch (330) causes a light and / or sound status beacon to be switched on or a light and / or sound status beacon to be switched off. Control module (30) according to any one of claims 1 to 8, wherein at least one piezoelectric element (310) is disposed in the internal space defined by the connector (230) so as to be placed in the airflow circulating in the duct (20) and is configured to be mechanically deformed when said at least one piezoelectric element (310) is subjected to a variation of a parameter of the air circulating in the duct (20). Control module (30) according to the preceding claim, wherein the variation of the parameter is a variation of air pressure, a variation of a pressure exerted on at least one piezoelectric element (310) by increasing or decreasing an air flow rate to measure dynamic pressure and / or static pressure, or a variation of air temperature. Aircraft air conditioning duct assembly (2), said assembly comprising a duct (20) and a control module (30) according to any one of the preceding claims, said duct (20) comprising a first end (210) configured to be connected to an air conditioning unit (210) and a second end (220) comprising a connector (230) configured to be connected to a low-pressure air inlet of said aircraft (2), said control module (30) being mounted on said connector (230). A method for remotely controlling an aircraft (2) air conditioning unit (10) by means of a control module (30) according to any one of the preceding claims, said control module (30) being configured to be mounted on a connector (230) of a sheath (20) adapted to connect said air conditioning unit (10) to said aircraft (2), said connector (230) being configured to be connected to a low-pressure air inlet of the aircraft (2), said method comprising the steps of: - mechanical deformation (E1) of at least one piezoelectric element (310) of the control module (30), - generation (E2), as a result of said mechanical deformation, by said at least one piezoelectric element (310), of an electrical charge, said electrical charge defining an electrical voltage representative of a control signal of the air conditioning unit (10), - emission (E3) by the transmitter (310), from said electrical charge,of a radio frequency signal containing said control information intended for a receiver (120) of the air conditioning unit (10) in order to control said air conditioning unit (10).

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