• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to an environmental control system for an aircraft cabin (5) comprising a device for withdrawing compressed air from at least one engine of the aircraft; an air cycle turbine engine (20) comprising at least one compressor (21) connected to said compressed air sampling device by an air sampling pipe (7) and a turbine (22) connected to the cabin (5) by a cabin inlet duct (8) for the supply of air at controlled pressure and temperature, characterized in that it further comprises: a fixed blade with variable injection section (23) mounted on said turbine (22) said air cycle turbine engine (20) so as to be able to modify on command the flow rate and / or the air pressure supplying an air inlet of said turbine (22); and a second compressor (22) mounted on said air cycle turbine engine (20) connected to an external air sampling device and said sampling line.
    公开号:FR3068005A1
    申请号:FR1755806
    申请日:2017-06-23
    公开日:2018-12-28
    发明作者:Fabrice Laborde；Cyril Vaucoret；Laurent Fayolle；David Lavergne
    申请人:Liebherr Aerospace Toulouse SAS；
    IPC主号:
    专利说明:

    SYSTEM AND METHOD FOR ENVIRONMENTAL CONTROL OF AN AIRCRAFT CABIN AND AIRCRAFT EQUIPPED WITH SUCH A CONTROL SYSTEM
    1. Technical field of the invention
    The invention relates to a system and method for environmental control of an aircraft cabin and extends to an aircraft equipped with such an environmental control system.
    2. Technological background
    Throughout the text, the term "cabin" means any interior space of an aircraft whose air pressure and / or temperature must be controlled. It can be a passenger cabin, the cockpit, a hold, and generally any area of the aircraft that requires air at controlled pressure and / or temperature.
    Environmental control of the cabins of an aircraft is currently commonly carried out using a combination of pneumatic and electrical means. However, in certain aircraft, the environmental control of the cabins is carried out entirely pneumatically, that is to say only by the implementation of systems operating on the basis of air taken from the compressors of the aircraft propulsion engines. and outside ambient air when the aircraft is in flight, and / or from air taken from an auxiliary engine, better known under the name of APU.
    Such a cabin environmental control system typically comprises a device for removing compressed air from at least one compressor of an aircraft propulsion engine and an air cycle turbomachine comprising at least one compressor and one turbine. , the compressor being supplied with air by the compressed air sampling device after passage through a flow or pressure regulation valve, and the turbine comprising an air outlet supplying the cabin with controlled temperature and flow. The system also includes various heat exchangers, control valves and a water extraction loop.
    Throughout the text, the term “turbine” designates a rotary device intended to use the kinetic energy of the air to rotate a shaft supporting the blades of the turbine. By compressor, we mean a rotary device intended to increase the pressure of the air it receives at the inlet.
    One of the difficulties of fully pneumatic solutions lies in the fact that an air intake on the compressors of propulsion engines impacts the energy performance of these engines. In particular, this removal of air from the compressors of the engines significantly increases fuel consumption.
    Also, different solutions have already been proposed to limit as much as possible this air intake on the aircraft propulsion engines.
    For example, the applicant has already proposed to recover part of the energy from the stale air in the cabin which must be renewed to drive a turbine of an intermediate turbocharger mechanically coupled to a compressor, itself connected in fluid communication to the air sampling device on the propulsion engine. It is thus possible to limit the sampling on the propulsion engine, in certain phases of the flight, and to use instead the energy of the stale air recovered at the cabin exit to drive the compressor of the turbocharger, which supplies the air conditioning pack turbomachine.
    The inventors have sought to propose a new architecture making it possible to further limit the intake of air from the propulsion engines of aircraft.
    3. Objectives of the invention
    The invention aims to provide an environmental control system for an aircraft cabin which minimizes the intake of air from the compressor of propulsion engines.
    The invention also aims to provide a method for environmental control of an aircraft cabin.
    The invention also aims to propose an aircraft having the same advantages. It aims in particular to propose an aircraft in which environmental control can be carried out exclusively pneumatically (the environmental control device can be, according to certain embodiments, free of electric motor), and of reduced fuel consumption.
    4. Statement of the invention
    To do this, the invention relates to an environmental control system for an aircraft cabin comprising:
    - a device for removing compressed air from at least one engine compressor of the aircraft, known as an engine air sampling device,
    - An air cycle turbomachine comprising at least a first compressor and a turbine mechanically coupled to each other, said first compressor comprising an air inlet connected to said engine air sampling device, by a pipe, called air sampling pipe, and said turbine comprising an air outlet connected to the cabin by a pipe, called cabin inlet pipe, in order to be able to supply the cabin with air at controlled pressure and temperature.
    An environmental control system for an aircraft cabin according to the invention is characterized in that it further comprises:
    a blade with a variable injection section mounted on said turbine of said air cycle turbomachine so as to be able to modify, on command, the air flow supplying an air inlet to this turbine,
    - a second compressor mounted on said air cycle turbomachine comprising an air inlet connected to an external air intake device and an outlet in fluid communication with said cabin inlet pipe.
    A system according to the invention therefore makes it possible to limit the drawbacks linked to the sampling of air from the aircraft propulsion engine (mainly energy losses) by recovering part of the energy of this air sampled from the engine.
    The recovery of the energy of the air taken from the engine, known by the English name of air bleed, results from the absence of a flow control valve at the outlet of the air intake device, this regulation being according to the invention obtained by means of a vane with variable injection section mounted on the turbine of the air cycle turbomachine. In other words, all the power of the air taken from the propulsion engine is sent to the turbine of the air conditioning system and the flow variation is done directly by a turbine with variable injection section.
    The recovery of this energy also allows the drive of a second compressor mounted on the air cycle turbomachine which is used to compress air which comes from an external air sampling device.
    Thus, for the same output flow rate from the air conditioning pack, the system according to the invention makes it possible to limit the intake of air from the compressor of the aircraft engine, and therefore to limit fuel consumption.
    On the ground or in low altitude flight phases, the second compressor, driven in rotation by the turbine of the air cycle turbomachine, can compress the air taken from outside the aircraft by taking a air (better known by the English name of scoop). This sampled air is injected upstream of the air conditioning pack, for example to circulate in a water extraction circuit.
    The combined air flow (i.e. the air flow taken from the aircraft engine compressor and the flow of scoop air compressed by the second compressor) is regulated by a section vane variable injection mounted on the turbine of the air cycle turbomachine, using flow measurements from, for example, a flow measurement system arranged upstream of the cabin.
    Advantageously, a system according to the invention further comprises a bypass pipe arranged between the outlet of the second compressor of the air cycle turbomachine and said cabin inlet pipe equipped with an altitude valve configured to allow the compressor directly supplying said cabin entry pipe when the aircraft reaches and / or exceeds a predetermined altitude.
    Thus, according to this advantageous variant, at altitude, the air compressed by the second compressor of the air cycle turbomachine is directly supplied to the outlet of the air conditioning pack.
    In all cases, the output of the second compressor is in fluid communication with the cabin inlet pipe. This fluid communication with the cabin inlet pipe is either direct, at altitude, or indirect, on the ground or in low altitude phases, after passing through the turbine.
    Advantageously, a system according to the invention further comprises an intermediate turbocharger comprising a compressor and a turbine mechanically coupled to each other, said turbine comprising an air inlet connected to said cabin by a pipe, called outlet pipe cabin, and said compressor comprising an air inlet connected to an external air intake device and an air outlet connected to said cabin inlet pipe by means of a heat exchanger, said heat exchanger being further in fluid communication with said cabin exit pipe.
    Preferably, the heat exchanger is in fluid communication with the bypass pipe, upstream of the altitude valve. This bypass pipe opens into the outlet pipe.
    According to this advantageous embodiment, part of the air evacuated from the pressurized cabin is recovered. Energy recovery is obtained by the presence of the intermediate turbocharger comprising at least one compression stage and at least one turbine mechanically coupled to each other. The turbine air inlet is connected to the cabin by a cabin outlet pipe to recover stale air which is exhausted from the cabin. The compressor includes an air inlet connected to an external air intake device and an air outlet connected to the cabin inlet pipe via a heat exchanger, which is itself in communication fluidic with the cabin exit pipe.
    Thus, the heat exchanger makes it possible to recover the thermal energy leaving the compressor to increase the temperature, and therefore the energy entering the turbine. The inventors have determined that this architecture makes it possible to recover on the order of 15% of additional power. In addition, this heat exchanger makes it possible to obtain an air temperature at the outlet of this energy recovery pack which is close to the cabin temperature, to within 5 ° C.
    This energy recovery pack supplies the air thus conditioned at the outlet of the air conditioning pack which adapts the engine flow and the air intake of the second compressor according to the flow of this compressor.
    Also, at altitude, the flow of scoop air compressed by the second compressor and the flow of scoop air compressed by the compressor of the intermediate turbocharger, pass through the altitude valve and are directly injected into the cabin inlet line. , and mixed with the air flow taken from the compressor of the aircraft engine and regulated by the blading with variable injection section mounted on the turbine of the air cycle turbomachine.
    Advantageously and according to this advantageous variant, the system further comprises a heat exchanger in fluid communication with said air intake line and a supply line for the turbine of the intermediate turbocharger.
    This advantageous variant makes it possible to recycle the temperature of the air taken from the aircraft engine in the expansion turbine of the intermediate turbocharger, for the benefit of cabin compression, while reducing the need for pre-cooling of the air taken from the engine before injection into the air conditioning pack.
    Advantageously and according to the invention, said outlet of the compressor of the air cycle turbomachine is connected to the inlet of said turbine by means of at least one heat exchanger, itself in fluid communication with an air intake. exterior dynamics.
    This cools the compressed and heated air which is supplied by the compressor before it is introduced into the air inlet of the turbine of the air cycle turbomachine.
    Advantageously and according to the invention, said air sampling pipe is equipped with at least one heat exchanger in fluid communication with a dynamic outside air intake.
    According to this advantageous variant, an air / air cooling heat exchanger is arranged on the sampling line upstream of the air inlet in the compressor of the air cycle turbomachine. This exchanger is also crossed by dynamic pressure air from an air intake, known under the name of RAM air intake, so as to cool the air before it enters the compressor. This heat exchanger allows heat transfer between a first flow of air flowing in the air intake pipe to the inlet of the compressor, and a second circuit formed by a flow of air flowing between the intake RAM air and compressor inlet.
    Advantageously, a system according to the invention comprises a motor fan configured to be able to ensure the circulation of air through said heat exchangers.
    According to this variant, the circulation of air in the heat exchangers is ensured by a motor-fan, which makes it possible to conserve the maximum of pneumatic energy to compress the outside air coming from the device for taking off outside air. In particular, in prior systems, the circulation of air in the exchangers is ensured by a fan wheel mounted on the shaft of the air cycle turbomachine. The invention according to this variant makes it possible to free the shaft of the turbomachine, and therefore to use the mechanical energy recovered to, in particular, drive the second compressor.
    The air coming from the cabin can be recirculating air. In this case, the turbine outlet of the intermediate turbocharger is connected to the cabin inlet or to a mixing chamber.
    Advantageously and according to the invention, the air outlet of the turbine of the turbocharger is connected to an air outlet outside of the aircraft so as to reject the expanded air outside.
    According to this variant, the air outlet of the turbine of the intermediate turbocharger is connected to an air outlet outside the aircraft so as to be able to evacuate the relaxed air outside. In this case, at least part of the air to be evacuated from the cabin for air renewal is used to drive the turbine of the intermediate turbocharger.
    Advantageously and according to the invention, said turbocharger is a turbocharger with two stages turbines in parallel.
    The invention also relates to a method for environmental control of an aircraft cabin comprising:
    - a compressed air sample from at least one aircraft engine compressor by an air sample device,
    - a routing by a sampling line of this sampled air towards an inlet of a compressor of an air cycle turbomachine mechanically coupled to a turbine,
    - a routing of the air leaving the turbine to said cabin by a cabin inlet pipe, said air being supplied at a controlled pressure and temperature.
    A method according to the invention is characterized in that it comprises:
    - A regulation of the air flow supplying said turbine of the turbomachine by a vane with variable injection section mounted on said turbine of said turbomachine so as to be able to modify on command the air flow supplying an air inlet of said turbine,
    - A routing of air sampled by an external air sampling device to an inlet of a second compressor mounted on said turbomachine, one outlet of which is in fluid communication with said cabin inlet pipe.
    Advantageously, a method according to the invention further comprises direct routing of the air leaving the second compressor to said cabin inlet pipe by a bypass pipe equipped with an altitude valve configured to allow the compressor directly supplying said cabin entry pipe when the aircraft reaches a predetermined altitude.
    Advantageously, a method according to the invention further comprises:
    - a routing of air at the outlet of the cabin, through a cabin outlet pipe towards an air inlet of a turbine of a turbocharger mechanically coupled to a compressor,
    - a flow of air taken by an external air sampling device to an inlet of the compressor,
    - a flow of air at the outlet of the compressor to said cabin inlet pipe by means of a heat exchanger, said heat exchanger being also in fluid communication with said cabin outlet pipe.
    Preferably, the heat exchanger is in fluid communication with the bypass pipe, upstream of the altitude valve. This bypass pipe opens into the outlet pipe.
    A system according to the invention advantageously implements a method according to the invention, and a method according to the invention is advantageously implemented by a system according to the invention.
    The invention also relates to an aircraft comprising at least one propulsion engine and one cabin, characterized in that it comprises an environmental control system for this cabin according to the invention.
    The invention also relates to an environmental control system, an environmental control method and an aircraft characterized in combination by all or some of the characteristics mentioned above or below.
    5. List of figures
    Other objects, characteristics and advantages of the invention will appear on reading the following description given by way of non-limiting example and which refers to the appended FIG. 1 which is a schematic view of an environmental control system according to one mode for carrying out the invention implementing an environmental control method according to the invention in an aircraft according to the invention.
    6. Detailed description of an embodiment of the invention
    An aircraft according to the invention comprises, as shown diagrammatically in FIG. 1, a passenger cabin 5, and at least one main engine 3. This main engine 3 dedicated to the propulsion of the aircraft comprises for example a compressor 11 and a turbine not shown in FIG. 1.
    The environmental control system according to the invention comprises at least one pack 55 of air conditioning, better known by the acronym ECS. This packaging pack 55 can have different embodiments. The embodiment shown in FIG. 1 is schematic and comprises an air cycle turbomachine 20, three heat exchangers 17, 18, 19 in fluid communication with a dynamic air circulation channel (better known under the name of RAM) , and a water extraction loop 42, which is not shown in detail for clarity.
    The air conditioning pack 55 is supplied with air taken from the compressor 11 of the engine 3 via an air sampling pipe 7, and the pack 55 supplies the cabin 5 via a cab entry line 8.
    The air cycle turbomachine 20 comprises at least one rotary compressor 21 and one rotary turbine 22 mechanically coupled to each other. The compressor 21 and the turbine 22 each include an air inlet and an air outlet.
    A first circuit of an air / air heat exchanger 17 is interposed between the outlet of the compressor 21 and the inlet of the turbine 22 so as to be able to cool the compressed and heated air supplied by the compressor 21 before it is introduced into the turbine air inlet 22. Downstream of the heat exchanger 17, the flow of cooled compressed air passes through a water extraction loop 42. This water extraction loop 42 includes example a heater formed by an air / air heat exchanger, a condenser also formed by an air / air heat exchanger and a water extractor. The cold expanded air at the outlet of the turbine 22 passes through the condenser of the water extraction loop 42 to cool the air flow upstream of the turbine 22, then feeds a mixing chamber 46 , which is connected to cabin 5.
    The heat exchanger 17 comprises a second circuit traversed by air at dynamic pressure coming from at least one mouth 72 for extracting air for the cooling of the compressed air heated between the compressor 21 and the turbine 22.
    In addition, a first circuit of an air / air cooling heat exchanger 18 is interposed between the inlet of the air conditioning system 55 and the air inlet of the compressor 21. The second circuit of this heat exchanger 18 is crossed by air at dynamic pressure coming from the air sampling mouth 72.
    Finally, a first circuit of an air / air cooling heat exchanger 19 is interposed between the air outlet of a second compressor 24 mounted on the air cycle turbomachine 20, supplied with air by a device for taking off air. outside air 71, and the cabin inlet pipe 8. The second circuit of this heat exchanger 19 is crossed by air at dynamic pressure coming from the air sampling mouth 72.
    As described below, the air cooled by this heat exchanger 19 is either directly injected into the cabin inlet pipe 8 in the flight phases at altitude, or injected into the cabin inlet pipe 8 after passing through the water extraction loop 42 and the turbine 22.
    The air circulation in the second circuits of the heat exchangers 17, 18 and 19 is ensured by a 4L motor-fan
    A system according to the invention is remarkable in that it comprises a vane with variable injection section 23 mounted on the turbine 22 of the air cycle turbomachine 20 so as to be able to modify on command the air flow supplying l 'air inlet of the turbine 22. This blading with variable injection section 23 can be of any known type. Such a blading is configured to modify the section of air passage in the turbine 22 and therefore to modify the air flow rate at the turbine inlet 22.
    Such a blading comprises for example two air guide faces arranged one with respect to the other so as to form therebetween an air injection passage capable of supplying a movable blading of the turbine. It further comprises a plurality of blades interposed between the two guide faces in said injection passage, arranged so as to form, in the injection passage between them two by two and between the two guide faces, a plurality of channels, each blade being rotatably mounted along an axis of rotation intersecting the guide faces, so that a change in the angular position of a blade results in a modification of the geometric characteristics of each channel delimited by this blade, and a mechanism angular position control of the blades.
    A system according to the invention also comprises a bypass line 6 arranged between the outlet of the second compressor 24 of the air cycle turbomachine 20 and the cabin inlet line 8. This bypass line 6 is equipped with a valve altitude 77 configured to allow the compressor to directly supply the cabin inlet line 8 when the aircraft reaches a predetermined altitude. A non-return valve 15 makes it possible to control the circuit according to the flight. At altitude, the air compressed by the compressor 24 is directly conveyed by the bypass line 6 to the cabin inlet line 8 and on the ground or at low altitude, the air passes through the non-return valve 15 and joins the water extraction loop 42 and the turbine 15.
    The system according to the embodiment of the figure also comprises an intermediate turbocharger 30 comprising a compressor 31 and a turbine 32 mechanically coupled to each other. This intermediate turbocharger aims to recover part of the energy from the stale air expelled from cabin 5.
    To do this, the turbine 32 comprises an air inlet connected to the cabin 5 by an outlet pipe 9 from the cabin, and the compressor 31 comprises an air inlet connected to an external air intake device 70 and a air outlet connected to said cabin inlet pipe 8 via a heat exchanger 75. This heat exchanger 75, better known by the English name of intercooler, is in fluid communication with the outlet pipe 9 of cabin.
    According to this architecture, the air recovered from the cabin is first used to cool the flow of compressed air by the compressor 31. The heat exchanger 75 makes it possible to self-stabilize the temperature of the air compressed by the compressor 31.
    The air flow is then injected into the air conditioning pack, upstream of the altitude valve 77 of the bypass line 6.
    Thus, according to this embodiment, when the pressurization conditions of cabin 5 allow it, part of the energy of the air expelled from cabin 5 is recovered for the benefit of the air conditioning system.
    In addition, a control system according to the invention comprises a control logic 10 associated with valves and regulating devices not shown in the figures making it possible to adapt the air samples from the various organs as a function of the pressurization objectives of the cabin.
    权利要求:
    Claims (13)
    [1" id="c-fr-0001]
    1. Environmental control system for an aircraft cabin (5) comprising:
    a device for removing compressed air from at least one compressor (11) of the aircraft engine (3), an air cycle turbomachine (20) comprising at least one compressor (21) and a turbine (22) mechanically coupled to each other, said compressor (21) comprising an air inlet connected to said device for withdrawing compressed air from at least one compressor (11) by a pipe, called a sampling pipe (7) , and said turbine (22) comprising an air outlet connected to the cabin (5) by a pipe, called cabin inlet pipe (8), in order to be able to supply the cabin (5) with air at controlled pressure and temperature , characterized in that it further comprises:
    a fixed vane with variable injection section (23) mounted on said turbine (22) of said air cycle turbomachine (20) so as to be able to modify, on command, the air flow supplying an air inlet of said turbine (22), a second compressor (24) mounted on said air cycle turbomachine (20) comprising an air inlet connected to an external air intake device (71) and an outlet in fluid communication with said line d 'cabin entrance (8).
    [2" id="c-fr-0002]
    2. System according to claim 1, characterized in that it further comprises a bypass pipe (6) arranged between the outlet of the second compressor (24) of the air cycle turbomachine (20) and said inlet pipe cabin (8) equipped with an altitude valve (77) configured to allow the compressor to directly supply said cabin inlet pipe (8) when the aircraft reaches a predetermined altitude.
    [3" id="c-fr-0003]
    3. System according to one of claims 1 or 2, characterized in that it further comprises an intermediate turbocharger (30) comprising a compressor (31) and a turbine (32) mechanically coupled to each other, said turbine (32) comprising an air inlet connected to the cabin (5) by a pipe, called an outlet pipe (9) of the cabin, and said compressor (31) comprising an air inlet connected to a sampling device outside air (70) and an air outlet connected to said cabin inlet pipe (8) via a heat exchanger (75), said heat exchanger (75) being further in fluid communication with said cabin outlet pipe (9).
    [4" id="c-fr-0004]
    4. System according to claim 3, characterized in that said air outlet from the turbine (32) of the turbocharger (30) is connected to an air outlet (43) outside the aircraft so as to reject the relaxed air outside.
    [5" id="c-fr-0005]
    5. System according to one of claims 3 or 4, characterized in that said turbocharger (30) is a turbocharger with two stages turbines in parallel.
    [6" id="c-fr-0006]
    6. System according to one of claims 3 to 5, characterized in that it further comprises a heat exchanger in fluid communication with said air intake line and a supply line for the turbine of the intermediate turbocharger.
    [7" id="c-fr-0007]
    7. System according to one of claims 1 to 6, characterized in that said outlet of the compressor (21) of the air cycle turbomachine (20) is connected to the inlet of said turbine (22) by means of at least one heat exchanger (19), itself in fluid communication with an intake (72) of dynamic outside air.
    [8" id="c-fr-0008]
    8. System according to one of claims 1 to 7, characterized in that said pipe (7) for air sampling is equipped with at least one heat exchanger (18) in fluid communication with an intake (72) of dynamic air. outside.
    [9" id="c-fr-0009]
    9. System according to one of claims 7 or 8, characterized in that it further comprises a motor-fan (41) configured to be able to ensure the circulation of air through said heat exchangers (17, 18, 19).
    [10" id="c-fr-0010]
    10. Method for environmental control of an aircraft cabin (5) comprising:
    a sampling of compressed air from at least one compressor (11) of the aircraft engine by an air sampling device, a routing by a pipe (7) of sampling of this sampled air to an inlet of a compressor (21) of an air cycle turbomachine (20) mechanically coupled to a turbine (22), a supply of air from the turbine outlet (22) to said cabin (5) by an inlet pipe ( 8) cabin, said air being delivered at a controlled pressure and temperature, characterized in that it further comprises:
    a regulation of the air flow supplying said turbine (22) of the turbomachine (20) by a fixed blade with variable injection section (23) mounted on said turbine (22) of said turbomachine (20) so as to be able to modify on command the air flow supplying an air inlet of said turbine (22), a routing of air taken by an external air intake device (71) to an inlet of a second compressor (22) mounted on said turbomachine (20), one outlet of which is in fluid communication with said cabin inlet pipe.
    [11" id="c-fr-0011]
    11. Method according to claim 10, characterized in that it further comprises direct routing of the air leaving the second compressor (22) to said cabin inlet pipe (8) by a bypass pipe ( 6) equipped with an altitude valve (77) configured to allow the compressor to directly supply said cabin inlet pipe (8) when the aircraft reaches a predetermined altitude.
    [12" id="c-fr-0012]
    12. Method according to one of claims 10 or 11, characterized in that it further comprises:
    a routing of air at the outlet of the cabin, via an outlet pipe (9) from the cabin to an air inlet of a turbine (32) of a turbocharger (30) mechanically coupled to a compressor (31), a supply of air taken from an external air intake device to an inlet to the compressor (31), a supply of air from the compressor (31) to said cabin inlet pipe (8) by via a heat exchanger (75), said heat exchanger (75) also being in fluid communication with said cabin outlet pipe (9).
    [13" id="c-fr-0013]
    13. Aircraft comprising at least one propulsion engine and one cabin, characterized in that it comprises an environmental control system for this cabin according to one of claims 1 to 9.
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    同族专利:
    公开号 | 公开日
    FR3068005B1|2019-07-26|
    EP3418194A1|2018-12-26|
    US20180370636A1|2018-12-27|
    EP3418194B1|2019-11-27|
    US11046440B2|2021-06-29|
    引用文献:
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    法律状态:
    2018-12-28| PLSC| Search report ready|Effective date: 20181228 |
    2020-06-20| PLFP| Fee payment|Year of fee payment: 4 |
    2021-06-30| PLFP| Fee payment|Year of fee payment: 5 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1755806|2017-06-23|
    FR1755806A|FR3068005B1|2017-06-23|2017-06-23|SYSTEM AND METHOD FOR ENVIRONMENTALLY CONTROLLING A CABIN OF AN AIRCRAFT AND AN AIRCRAFT EQUIPPED WITH SUCH A CONTROL SYSTEM|FR1755806A| FR3068005B1|2017-06-23|2017-06-23|SYSTEM AND METHOD FOR ENVIRONMENTALLY CONTROLLING A CABIN OF AN AIRCRAFT AND AN AIRCRAFT EQUIPPED WITH SUCH A CONTROL SYSTEM|
    EP18179230.0A| EP3418194B1|2017-06-23|2018-06-22|System and method for environmental control of an aircraft cabin and aircraft provided with such a control system|
    US16/016,573| US11046440B2|2017-06-23|2018-06-23|Aircraft cabin environmental control system and method and aircraft equipped with such control system|
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