• 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 a method for detecting a Pitot tube lock including measuring a Pitot tube temperature by means of one or more temperature sensors positioned inside a Pitot tube, the measurement of a temperature outside ambient air, the comparison of the Pitot tube temperature measured at a Pitot tube minimum temperature threshold for the measured outdoor ambient air temperature, and the determination that the Pitot tube exhibits a blocking condition when the measured Pitot tube temperature is below the pitot tube minimum temperature threshold. Figure for Abstract: Figure 1
    公开号:FR3076612A1
    申请号:FR1872464
    申请日:2018-12-06
    公开日:2019-07-12
    发明作者:Divakara Rao Vadada；Divya Rajan Pillai
    申请人:Rosemount Aerospace Inc；
    IPC主号:
    专利说明:

    Description
    Title of the invention: DETECTION SYSTEM AND METHOD
    FOR LOCKING A PITOT TUBE
    The invention relates to the field of Pitot type tubes, and more particularly a method and a system using a connected Pitot tube.
    The embodiments cited in example belong to the technique of anemometric circuits, and more particularly, to the detection of blockage of Pitot tubes of anemometric circuits.
    An air flow circuit as used in an aircraft is a system of pressure sensitive instruments which is most often used in aviation to determine an aerodynamic speed of an aircraft, a Mach number, an altitude and an altitude trend. An airspeed circuit generally includes a Pitot tube, a static outlet and airspeed instruments. Other instruments that could be connected are aerodynamic control units, flight data recorders, altitude encoders, cabin pressurization regulators and various aerodynamic speed switches. Errors in the airspeed reading values can be extremely dangerous since information obtained from the airspeed circuit, such as altitude, is potentially critical to safety.
    A source of error in the air flow circuit relates to a blockage or obstruction inside the Pitot tube. The blockage can be caused by icing, volcanic ash, dirt, foreign bodies (such as insects), tape, Pitot caches, etc. Blocking or obstructing the Pitot tube results in the reporting of incorrect aerodynamic speed, altitude, or the like on the instruments. This leads to crew confusion, spatial disorientation and possibly catastrophic breakdowns. Summary of the invention [0005] In one embodiment, a method for detecting blockage of a Pitot tube is proposed, which includes measuring a temperature of the Pitot tube using one or more temperature sensors positioned at inside a Pitot tube, measuring an outside ambient air temperature, comparing the measured Pitot tube temperature to a minimum Pitot tube temperature threshold for the measured outside ambient air temperature , and determining whether the Pitot tube has a blocking condition when the measured Pitot tube temperature is below the minimum Pitot tube temperature threshold.
    In addition or as a variant, in this embodiment or other embodiments, the method includes determining whether a Pitot tube heater is or is not operational, and selecting the threshold minimum Pitot tube temperature based on the measured outside ambient air temperature and an operational state of the Pitot tube heater.
    In addition or alternatively, in this embodiment or other embodiments, the method includes warning a flight crew regarding the blocking condition.
    In addition or alternatively, in this embodiment or other embodiments, the warning is a visual and / or audible warning.
    In addition or as a variant, in this embodiment or other embodiments, the minimum temperature threshold for Pitot tube is obtained from a temperature calibration database.
    Additionally or alternatively, in this or other embodiments, measuring a Pitot tube temperature includes measuring three or more Pitot tube temperatures using three or more temperature sensors positioned at three or more longitudinal positions of the Pitot tube.
    In addition or alternatively, in this embodiment or other embodiments, the three or more temperature sensors are positioned at three or more circumferential positions of the Pitot tube.
    It also proposed a Pitot tube system which includes a Pitot tube and a blockage detection system operatively connected to the Pitot tube. The blockage detection system includes a plurality of Pitot tube temperature sensors positioned within the Pitot tube configured to measure a Pitot tube temperature, and a system controller operatively connected to the plurality of Pitot tube temperature sensors . The system controller is configured to compare the measured Pitot tube temperature to a minimum Pitot tube temperature threshold for a measured outside ambient air temperature, and determine that the Pitot tube has a blocking condition when the tube temperature Pitot measured is below the minimum Pitot tube temperature threshold.
    Additionally or alternatively, in this embodiment or other embodiments, a Pitot tube heater selectively heats the Pitot tube and the system controller is configured to determine whether a Pitot tube heater is operational. The minimum Pitot tube temperature threshold is selected based on the measured outside ambient air temperature and an operational state of the Pitot tube heater.
    In addition or alternatively, in this embodiment or in other embodiments, a warning system provides a warning to a flight crew in the event of detection of a blocking condition.
    In addition or alternatively, in this embodiment or in other embodiments, the warning is one or more of a visual warning or an audible warning.
    In addition or alternatively, in this embodiment or in other embodiments, the plurality of temperature sensors is three or more temperature sensors positioned at different longitudinal positions along the pitot tube.
    In addition or alternatively, in this embodiment or in other embodiments, the plurality of temperature sensors includes sensors positioned at different circumferential positions around the Pitot tube.
    In addition or as a variant, in this embodiment or in other embodiments, one or more outdoor ambient air temperature sensors make it possible to obtain the temperature of the outdoor ambient air.
    In addition or alternatively, in this embodiment or in other embodiments, the Pitot tube includes one or more total pressure openings and one or more static pressure openings.
    In addition or alternatively, in this embodiment or in other embodiments, the operation of the system is started by user input at any time during the operation of the Pitot tube.
    Brief description of the drawings The following description should in no way be considered as limiting. In the accompanying drawings, the similar elements have the same number: [0022] [fig.l]
    Figure 1 is a schematic representation of an embodiment of an airspeed circuit; [Fig.2]
    Figure 2 is a schematic representation of an embodiment of a module warning of a Pitot tube blockage; [Fig.3]
    Figure 3 is a sectional view of an embodiment of a Pitot tube; and [fig. 25]
    FIG. 4 is a schematic representation of a method for determining Pitot tube blockage and for announcing a Pitot tube condition.
    Detailed description Here we will present a detailed description of one or more embodiments of the apparatus and method disclosed by way of example and not by limitation with reference to the figures.
    Figure 1 shows a schematic representation of an embodiment of an airflow circuit 10. The airflow circuit 10 includes a Pitot tube 12, which is connected to one or more flight instruments 14, such as an altimeter , an aerodynamic speedometer and / or a vertical speedometer. The flight instrument or instruments 14 use data collected using the Pitot tube 12 to provide indications at the level of the flight instrument or instruments 14 concerning, for example, altitude, aerodynamic speed and / or vertical speed of an aircraft on which the airspeed circuit 10 is installed.
    In some embodiments, such as that shown in Figure 1, the Pitot tube 12 includes a total pressure opening 16, which is positioned at a distal end 18 of the Pitot tube 12 so that a flow of air 20 enters the total pressure opening 16 in the direction of movement 22. The Pitot tube 12 further includes one or more static pressure openings 24 oriented substantially perpendicular to the direction of movement 22. In certain embodiments, the static pressure openings 24 are positioned at an external peripheral surface 26 of the Pitot tube 12. An air flow 20 entering the total pressure opening 16 and the static pressure openings 24 is directed towards a transducer. pressure 28, at which a difference between the measured static pressure and the total measured pressure is determined, and is indicative, for example, of the aerodynamic speed namique, altitude and / or vertical speed of the aircraft. In addition, the Pitot tube 12 includes a Pitot tube heater 52 for heating the Pitot tube 12, when the Pitot tube heater 52 is operating.
    If we now look at Figure 2, the airflow circuit 10 further includes a blockage detection system 30 connected to the Pitot tube 12 for the detection and indication of blockage of the Pitot tube 12 by an accumulation of ice for example . The blockage detection system 30 provides feedback to an aircraft flight crew that indications from one or more flight instruments 14 may be erroneous.
    The blockage detection system 30 includes a plurality of tube temperature sensors 32 disposed along the length of the Pitot tube 12, which are configured to measure an internal temperature of the Pitot tube 12. The tube temperature sensors 32 can be positioned in defined longitudinal zones of the Pitot tube 12, defining different parts of the length of the Pitot tube 12. For example, in the embodiment of FIG. 2, a first tube temperature sensor 32a is positioned in a first Pitot tube region 34a, a second tube temperature sensor 32b is positioned in a second Pitot tube region 34b and a third tube temperature sensor 32c is positioned at a third Pitot tube region 34c, so that tube temperatures at different parts of the tube length can be measured by the tube temperature sensors 32 and the system blockage detection 30. In addition, if we look at FIG. 3, the tube temperature sensors 32a, 32b and 32c can be positioned at different circumferential positions of the Pitot tube 12. While three tube temperature sensors 32a, 32b , 32c are used in the illustrated embodiment, a person skilled in the art will readily understand that other quantities of tube temperature sensors 32 can be used.
    If we look again at Figure 2, the tube temperature sensors 32 are connected to a system controller 54 through one or more lines of sensors 36. In some embodiments, each tube temperature sensor 32 is connected to the system controller through a separate sensor line 36, while in other embodiments, a shared sensor line 36 can be used by the tube temperature sensors 32 to transmit data to the system controller 54. A data acquisition module 38 collects the data transmitted by the tube temperature sensors 32 to the system controller 54.
    The system controller 54 further includes a temperature calibration database 40. The temperature calibration database 40 includes a minimum temperature threshold for a given outside ambient air temperature for each tube temperature sensors 32. In addition, the minimum temperature threshold is determined for the condition in which the Pitot tube heater 52 is operating and for the condition in which the Pitot tube heater 52 is not operating. The condition of the Pitot tube heater 52, whether the Pitot tube heater 52 is working or not working, is used at the system controller 54 as Pitot tube temperature information 58. The calibration database temperature 40 can be established for example, by computer modeling and / or testing in a wind tunnel or in other conditions. An outside air temperature sensor 42 is configured to detect an outside ambient air temperature. A blockage detection module 44 uses the collected tube temperatures, Pitot tube temperature information 58, outside ambient air temperature, and the temperature calibration database 40 to determine if there is a condition. blocking in the Pitot tube 12.
    An announcement module 46 signals to one or more of a visual warning system 48 or an audible warning system 50 to produce a visual warning, such as a light or a visual message and / or an oral message such as a tone signal or a spoken alert message intended for the flight crew in the event of detection of a blocking condition in the Pitot tube 12.
    Referring now to Figure 4, we will describe an operating method of the blocking detection system 30. It should be understood that in some embodiments, the blocking detection system 30 is automatically switched on. continuous or periodic operation by the system controller 54.
    In addition, the operation of the blocking detection system 30 can be initiated by a signal from a user 60 (shown in FIG. 2) during any operating phase of the airspeed circuit 10, such as during any operating phase of flight.
    In the flow diagram of FIG. 4, the block or step 100 corresponds to a step of collecting the Pitot tube temperature data detected, these being representative of temperatures Tz recovered from each tube temperature sensor 32 (from each corresponding zone), while the outside ambient air temperature or a Range Text value representative of the outside temperature conditions is retrieved in step 102 from the outside air temperature sensor 42 (or sensors 42) to be supplied to the blocking detection module 44.
    In step 104, the blocking detection module 44 obtains an operational state of the Pitot tube heater 52. It is understood that information (summary information) representative of the temperature conditions of the Pitot tube is obtained, this which makes it possible to determine a state of the Pitot tube which can represent a heating state (YES case which can be determined in a sub-step 104a).
    In step 106 of obtaining the threshold, if the Pitot 52 tube heater is operating, a corresponding minimum temperature threshold (T MTThRange (with heating)) corresponding to the temperature of the detected outside ambient air (or Text Range value) is obtained from the temperature calibration database. In step 108 which follows, here a comparison step in the nonlimiting example illustrated, the Pitot tube temperatures detected are compared with the minimum temperature threshold. If the Pitot tube temperatures detected (typically all or part of these temperatures) are below the minimum temperature threshold with here a YES response, the module 46 announcement mode is activated at communication step 110 for warn the flight crew of the Pitot tube 12 blocking, indicating that the Pitot tube heating provided by the Pitot tube heater 52 is insufficient.
    Alternatively, if the pitot tube temperatures detected are above the minimum temperature threshold (entirely above, without falling into the low reference range bounded by the minimum temperature threshold), the detection system of blocking 30 determines that no Pitot tube blocking is present, and continues to operate. In certain embodiments, the announcement module 46 can provide a signal indicating that the Pitot tube 12 is free from blockage, for example in step 112.
    Similarly, if the Pitot tube heater 52 does not operate with the consequence of determining NO after sub-step 104a, a corresponding minimum temperature threshold (T MTThRange (withoutHeating)) corresponding to the temperature of the detected outside ambient air (or Text Range value) is obtained from the temperature calibration database in step 114 for obtaining the threshold. In step 116, the Pitot tube temperatures detected are compared with the minimum temperature threshold. If the Pitot tube temperatures detected are below the minimum temperature threshold, the module 46 announcement mode is activated in communication step 118 to warn the flight crew of the Pitot tube 12 blockage, indicating that the Pitot 52 tube heater does not work.
    As a variant, if the Pitot tube temperatures detected are above the minimum temperature threshold (with the result NO at the end of the comparison step 116), the blockage detection system 30 determines that no Pitot tube blockage is present, and continues to operate. In certain embodiments, the announcement module 46 can provide a signal indicating that the Pitot tube 12 is free from blockage, for example in step 120.
    The terminology used here is only intended to describe particular embodiments and is in no way intended to limit the present disclosure. As used herein, the singular forms "one", "one", "the" and "the" are intended to also include plural forms, unless the context clearly specifies otherwise. It should be understood that the terms "includes" and / or "comprising" when used in this Memorandum, specify the presence of characteristics, integers, steps, operations, elements and / or components stated, but do not exclude the presence or addition of one or more other characteristics, integers, steps, operations, elements, components and / or groups thereof.
    While the present disclosure has been described with reference to one or more example (s) of embodiment, it should be understood by those skilled in the art that various changes can be made to it and that equivalents can replace elements thereof without departing from the scope of this disclosure. Furthermore, numerous modifications can be made to the teachings of this disclosure, for example to adapt to a particular situation or subject, without departing from its essential scope. Therefore, this disclosure is not intended to be limited to the particular embodiment disclosed as the best mode contemplated for implementing this disclosure. On the contrary, it should be obvious to those skilled in the art that the present invention allows embodiments in many other specific forms without departing from the scope of the invention as claimed.
    权利要求:
    Claims (1)
    [1" id="c-fr-0001]
    Claims [Claim 1] Method for detecting blockage of a Pitot tube (12), comprising: - measuring a Pitot tube temperature using one or more temperature sensors (32) arranged inside a Pitot tube (12); - the measurement of an outside ambient air temperature; - comparing (108; 116) the Pitot tube temperature measured with a minimum Pitot tube temperature threshold for the measured temperature of the outside ambient air; and - determining that the Pitot tube (12) has a blocking condition when the measured Pitot tube temperature is below the minimum Pitot tube temperature threshold. [Claim 2] The method of claim 1, further comprising: - determining (104, 104a) whether a Pitot tube heater (52) is or is not operational; and - selecting (106; 114) the minimum Pitot tube temperature threshold based on the measured outside ambient air temperature and an operational state of the Pitot tube heater (52). [Claim 3] The method of claim 1 or 2, further comprising warning (108; 116) of a flight crew regarding the stall condition. [Claim 4] The method of claim 3, wherein the warning (108; 116) is a visual and / or audible warning. [Claim 5] A method according to any preceding claim, wherein the minimum pitot tube temperature threshold (12) is obtained from a temperature calibration database. [Claim 6] A method according to any one of the preceding claims, in which the measurement of a Pitot tube temperature (12) comprises the measurement of three or more Pitot tube temperatures by means of three or more temperature sensors (32a, 32b, 32c) positioned at three or more longitudinal positions of the Pitot tube. [Claim 7] The method of claim 6, wherein the three or more temperature sensors (32a, 32b, 32c) are positioned at three or more circumferential positions of the Pitot tube (12). [Claim 8] Pitot tube system (10), comprising: - a Pitot tube (12); and - a blockage detection system (30) operatively connected to the Pitot tube (12), including: a plurality of Pitot tube temperature sensors (32) positioned inside the Pitot tube (12) configured to measure a temperature Pitot tube; and a system controller (54) operatively connected to the plurality of Pitot tube temperature sensors (32), wherein the system controller (54) is configured to: - compare the measured Pitot tube temperature to a temperature threshold minimum Pitot tube for a measured outside ambient air temperature; and - determining that the Pitot tube (12) has a blocking condition when the measured Pitot tube temperature is below the minimum Pitot tube temperature threshold. [Claim 9] Pitot tube system according to claim 8, further comprising a Pitot tube heater (52) for selectively heating the Pitot tube (12); wherein the system controller (54) is configured to determine whether a Pitot tube heater (52) is operational; and wherein the minimum Pitot tube temperature threshold is selected based on the measured outside ambient air temperature and an operational state of the Pitot tube heater (52). [Claim 10] The system of claim 8 or 9, further comprising a warning system (48, 50) for providing a warning (108; 116) to a flight crew upon detection of the lockout condition. [Claim 11] The system of claim 10, wherein the warning (108; 116) is one or more of a visual warning or an audible warning. [Claim 12] A system according to any of claims 8 to 11, wherein the plurality of sensors (32) consists of three or more temperature sensors (32a, 32b, 32c) positioned at different longitudinal positions along the pitot tube (12). [Claim 13] A system according to any of claims 8 to 12, wherein the plurality of temperature sensors (32) includes sensors (32a, 32b, 32c) positioned at different circumferential positions around the pitot tube. [Claim 14] Pitot tube system according to any of claims 8 to 13, further comprising one or more outdoor ambient air temperature sensors to obtain the temperature of the outdoor ambient air. [Claim 15] Pitot tube system according to any of claims 8 to 14, wherein the Pitot tube (12) includes one or more total pressure openings (16) and one or more static pressure openings (24).
    类似技术:
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    同族专利:
    公开号 | 公开日
    FR3076612B1|2021-02-12|
    US10527640B2|2020-01-07|
    US20190178906A1|2019-06-13|
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    法律状态:
    2019-11-20| PLFP| Fee payment|Year of fee payment: 2 |
    2020-05-01| PLSC| Publication of the preliminary search report|Effective date: 20200501 |
    2020-11-20| PLFP| Fee payment|Year of fee payment: 3 |
    2021-11-17| PLFP| Fee payment|Year of fee payment: 4 |
    优先权:
    申请号 | 申请日 | 专利标题
    IN201711044821|2017-12-13|
    IN201711044821|2017-12-13|
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