• 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:
    System for optimizing air conditioning of the interior of an aircraft, which has an air conditioning system comprising a control unit capable of regulating temperature and/or humidity and/or flow and/or air flow that emits said air equipment conditioning, said air conditioning system comprising means for acquiring temperature and/or humidity that capture the temperature and/or humidity of the interior of the aircraft and digitize the value of the temperature and/or humidity obtained; transmission means that transmit the digitized values of temperature and/or humidity obtained; and receiving means receiving the digitized values of temperature and/or humidity transmitted by the transmission means and configured to adapt to the air conditioning equipment such that the control unit regulates the temperature and/or humidity and/or flow and/or flow rate of the air that said air conditioning equipment emits according to the digitized values of temperature and/or humidity captured. (Machine-translation by Google Translate, not legally binding)
    公开号:ES2608528A1
    申请号:ES201730099
    申请日:2017-01-27
    公开日:2017-04-11
    发明作者:Oriol Puig Oliveras
    申请人:Adelte Airport Technologies SL；
    IPC主号:
    专利说明:

    Air conditioning optimization system of an aircraft Technical field
    The present invention refers to an air conditioning optimization system of an aircraft which, preferably, is applicable during the time in which the aircraft remains stopped at the boarding gate of an airport.
    Consequently, the scope of the present invention is within the industrial sector dedicated to the construction of airport equipment and, more specifically, to that which is intended to facilitate aircraft operations. Prior State of the Art
    In the aeronautical sector, when the aircraft are in a stop position at the corresponding boarding gates of an airport, the engines must be turned off.
    15 This means that, at that time, if the aircraft wish to receive a supply to provide any type of service, such as: air conditioning, external equipment and power systems are required inside the aircraft.
    So, to solve the problem of air conditioning supply
    20 when the aircraft is on the ground with the engines off, the prior art proposes to use an external air conditioning system that injects air. The main drawback of this solution is that the air that is finally injected inside the aircraft is not adjusted in flow or temperature depending on the temperature and humidity of the interior of the aircraft, so it cannot be equipped with a optimum comfort
    25 climatic inside the aircraft.
    An alternative solution posed by the state of the art is that the boarding / landing gateways have temperature probes which are connected by cable to the air conditioning system in such a way that the temperature of the
    The air supplied by said air conditioning system is set according to the temperature obtained by said probes. The main drawback of this solution is that its use is inconvenient due to the wiring for the connection of its elements.

    Explanation of the invention.
    The present invention has as its main purpose to solve all the aforementioned drawbacks.
    Consequently, the present invention has to solve the technical problem of the
    5 air conditioning inside an aircraft when said aircraft is stopped on the ground at the corresponding boarding gate and with the engines off, so that the air supplied by the corresponding air conditioning system is not too cold and / or hot and / or humid to lower or increase the temperature inside the aircraft to levels uncomfortable for the crew and / or passengers.
    10 For this, the present invention is based on an air conditioning optimization system of an aircraft where air conditioning equipment is provided and comprising a control unit capable of regulating the temperature and / or humidity and / or flow and / or air flow emitted by said air conditioning (or air conditioning) equipment, wherein said air conditioning system comprises:
    15 -means of acquisition of temperature and / or humidity configured to capture the temperature and / or humidity of the interior (passenger area and / or cockpit) of the aircraft and digitize the value of the temperature and / or humidity obtained;
    - transmission means capable of wirelessly transmitting the digitized temperature and / or humidity values obtained by the temperature and / or humidity acquisition means 20;
    - reception means capable of wirelessly receiving the digitized temperature and / or humidity values transmitted by the transmission medium and configured to adapt to the air conditioning equipment in such a way that the control unit regulates the temperature and / or humidity and / or air flow and / or flow that
    25 issues said air conditioning equipment inside the aircraft based on the digitized temperature and / or humidity values received by the reception means.
    Preferably, the air conditioning equipment is configured to operate when the aircraft's engines are turned off. 30 Brief description of the drawings
    The foregoing and other advantages and features will be more fully understood from the following detailed description of some embodiments with reference to the attached drawings, which should be considered by way of illustration and not limitation, in which:


    - Fig. 1 is a schematic view representing a first embodiment of the air conditioning optimization system of an aircraft according to the invention in which the temperature and / or humidity acquisition means is located inside the aircraft.
    - Fig. 2 is a schematic view showing a second embodiment of the air conditioning system of an aircraft according to the invention in which the temperature and / or humidity acquisition means is located at the entrance door to the aircraft.
    - fig. 3 is a schematic view illustrating a third embodiment of the air conditioning system of an aircraft according to the invention in which the means for acquiring temperature and / or humidity is located on the boarding / disembarking gateway of the aircraft. Detailed description of an embodiment example
    As can be seen in the 3 figures, the air conditioning optimization system of an aircraft (1) of each one includes:
    - temperature and / or humidity acquisition means (2) configured to capture the temperature and / or humidity of the interior of the aircraft (1) and / or of a peripheral area of the aircraft (1) and digitize the temperature value and / or moisture obtained;
    - transmission means (3) capable of wirelessly transmitting the digitized temperature and / or humidity values obtained by the temperature and / or humidity acquisition means (2);
    - reception means (4) capable of wirelessly receiving the digitized temperature and / or humidity values transmitted by the transmission medium (3) and configured to adapt to an air conditioner (5) of the aircraft (1) that it comprises a control unit (6) capable of regulating the temperature and / or humidity and / or flow and / or flow of the air emitted by said air conditioning equipment (5) such that the control unit (6) regulates the temperature and / or humidity and / or flow and / or flow of the air emitted by said air conditioning equipment (5) depending on the digitized values of temperature and / or humidity received by the receiving means (4).
    The difference between the air conditioning systems represented in the 3 figures is found in the location of the temperature and / or humidity acquisition means (3).


    Thus, in the case of the air conditioning system of Figure 1, the temperature and / or humidity acquisition means (3) is located inside the aircraft (1) in such a way that it is able to detect the temperature and / or humidity inside the aircraft (1). This allows the control unit (6) to regulate the temperature and / or humidity and / or flow and / or flow of the air emitted by the air conditioning equipment (5) depending on the temperature and / or humidity inside the aircraft (1).
    For example, if the temperature and / or humidity inside the aircraft (1) is too high or low for the crew and / or passengers, the control unit
    (6) it can regulate the temperature and / or humidity and / or air flow of the air conditioning equipment (5) to levels such that the temperature and / or humidity inside the aircraft (1) drops or increases to comfortable levels for said crew and / or passengers.
    In the preferred embodiment of the air conditioning system of Figure 2, the temperature and / or humidity acquisition means (2) is located at the entrance door
    (7) of the aircraft (1) in such a way that it is capable of detecting the temperature and / or humidity of a peripheral area to the entrance door (7). This allows the control unit (6) to regulate the temperature and / or humidity and / or flow and / or flow of the air emitted by the air conditioning equipment (5) depending on the temperature and / or humidity inside The aircraft.
    Thus, for example, in this preferred embodiment, if the temperature and / or humidity of the entrance door (7) is already suitable for the crew and / or passengers, the control unit (6) can regulate the temperature and / or humidity and / or air flow of the air conditioning equipment (5) at levels that allow the temperature and / or humidity of the interior of the aircraft (1) to be similar or not to those found at the entrance door ( 7) maintaining comfortable thermal conditions for the crew and / or passengers from the entrance door (7) to the interior of the aircraft (1). On the contrary, if the temperature and / or humidity of the entrance door (7) of the aircraft (1) is too high or low for the crew and / or passengers, the control unit (6) can regulate the temperature and / or humidity and / or air flow of the air conditioning equipment (5) at levels such that the temperature and / or humidity inside the aircraft (1) is within comfortable margins for said crew and / or passengers and , preferably, without implying a sharp change in the thermal conditions of the entrance door area (7).
    In the preferred embodiment of the air conditioning system of Figure 3, the means for acquiring temperature and / or humidity (2) is located on the gangway of


    boarding / disembarking (8) of the aircraft (1) in such a way that it is capable of detecting the temperature and / or humidity in the boarding / disembarking gateway (8). This allows the control unit (6) to regulate the temperature and / or humidity and / or flow and / or flow of the air emitted by the air conditioning equipment (5) depending on the temperature and / or humidity of the gangway embarkation / disembarkation (8).
    For example, in this preferred embodiment, if the temperature and / or humidity inside the aircraft is already suitable for the crew and / or passengers, the control unit (6) can regulate the temperature and / or humidity and / or air flow of the air conditioning equipment (5) at levels that allow the temperature and / or humidity of the interior of the aircraft (1) may or may not be similar to those found on the boarding / landing gateway ( 8) maintaining comfortable thermal conditions for the crew and / or passengers from the boarding / disembarking gangway (8) to the interior of the aircraft (1). On the contrary, if the temperature and / or humidity of the boarding / disembarking gangway (8) is too high or too low for the crew and / or passengers, the control unit (6) can regulate the temperature and / or humidity and / or air flow of the air conditioning equipment (5) at levels such that the temperature and / or humidity of the interior of the aircraft (1) is within comfortable ranges for said crew and / or passengers and, preferably , without implying a sudden change in thermal conditions from the area of the boarding / disembarking gateway (8) to the interior of the aircraft (1).
    In another preferred embodiment, the air conditioning system comprises means for acquiring temperature and / or humidity (2) located inside the aircraft (1) and / or at the entrance door (7) of the aircraft (1) and / or on the boarding / landing gateway (8) in such a way that it is able to detect the temperature and / or humidity inside the aircraft so that the control unit (6) can regulate the temperature and / or flow of the air from the air conditioning equipment (5) at levels such that the temperature and / or humidity of the interior of the aircraft (1) is within comfortable margins for said crew and / or passengers.
    Preferably, the temperature and / or humidity acquisition means (2) are sensors or probes.
    In a preferred embodiment, the transmission means (3) transmit the digitized temperature and / or humidity values periodically over time so that the control unit (6) can regulate the temperature and / or humidity and / or flow and / or flow of the air emitted by said air conditioning equipment (5) periodically in time.


    One skilled in the art will be able to make modifications and variations from the examples of embodiment shown and described without departing from the scope of the present invention as defined in the appended claims.

    权利要求:
    Claims (4)
    [1]
    1. System of optimization of air conditioning of the interior enclosure of an aircraft, where
    5 has an air conditioning equipment (5) comprising a control unit (6) capable of regulating temperature and / or humidity and / or flow and / or flow of the air emitted by said air conditioning equipment characterized in that said system of air conditioning includes:
    - temperature and / or humidity acquisition means (2) configured to capture the
    10 temperature and / or humidity inside the aircraft and digitize the value of the temperature and / or humidity obtained;
    - transmission means (3) capable of wirelessly transmitting the digitized temperature and / or humidity values obtained by the temperature and / or humidity acquisition means (2);
    15 -means of reception (4) capable of wirelessly receiving the digitized values of temperature and / or humidity transmitted by the transmission means (3) and configured to adapt to the air conditioning equipment (5) in such a way that the unit of control
    (6) regulate the temperature and / or humidity and / or flow and / or flow of the air emitted by said equipment
    air conditioning (5) depending on the digitized temperature and / or humidity values 20 received by the receiving means (4).
    [2]
    2. Air conditioning optimization system according to the preceding claim wherein the means for acquiring temperature and / or humidity (2) is prepared to be located on the boarding / disembarking gateway (8) of the aircraft.
    [3]
    3. Air conditioning optimization system according to any of the claims
    25 above in which the means of acquisition of temperature and / or humidity (2) are sensors or probes.
    [4]
    4. Air conditioning optimization system according to any one of the preceding claims wherein the transmission means (3) periodically transmit the digitized temperature and / or humidity values over time.



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    同族专利:
    公开号 | 公开日
    ES2608528B1|2017-10-27|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US20080029610A1|2006-08-01|2008-02-07|Honeywell International Inc.|A selective autodiscovery system|
    WO2009073034A1|2007-12-07|2009-06-11|Carrier Corporation|Control of conditioned environment by remote sensor|
    US20120042685A1|2009-03-20|2012-02-23|Axa Power Aps|Preconditioned air unit with self-contained cooling modules|
    US20120273581A1|2009-11-18|2012-11-01|Kolk Richard A|Controller For Automatic Control And Optimization Of Duty Cycled HVAC&R Equipment, And Systems And Methods Using Same|
    法律状态:
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