• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
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    • 专利摘要:
    Systems and methods for improving engine performance based on atmospheric precipitation conditions are provided. For example, a method may include selecting one or more points (420) on a flight path (410) of an aircraft (102) and receiving a radar reflectivity measurement for the point / each of the points (420), obtained by means of a radar device placed on the aircraft (102). The method may further include determining a frozen water presence estimate for the point / each of the points (420) at least partially from the reflectivity measurements; and controlling at least one part of the aircraft engine (eg variable rate discharge valve) at least partially according to the frozen water presence estimate for at least one point of the plurality of points (420).
    公开号:FR3043139A1
    申请号:FR1660117
    申请日:2016-10-19
    公开日:2017-05-05
    发明作者:Nicholas Race Visser；Sridhar Adibhatla；David Michael Lax
    申请人:GE Aviation Systems LLC；
    IPC主号:
    专利说明:

    Improved engine performance to reduce fuel consumption based on ice particles in the atmosphere
    The present invention relates generally to improving the performance of aircraft engines.
    An aircraft may include an engine such as a gas turbine engine for the propulsion of the aircraft. A gas turbine engine may include a blower and a gas generator in flow communication with each other. The gas turbine engine gas generator generally comprises an air flow path having, in series on the air flow path, a compressor section, a combustion section, a turbine section and an exhaust section. The compressor section may include one or more compressors for compressing air. The compressed air can be supplied to the combustion section where it is mixed with fuel and burned to produce flue gases. The combustion gases can be used to operate the compressor section and turbine section of the gas turbine engine.
    In flight, an aircraft may encounter solid water in the form of ice crystals (eg from cirrus clouds) on its flight path. The large amounts of frozen water ingested by the engine of an aircraft can be problematic, as energy is expended to convert water into steam during the combustion process. This can cause an increase in the specific fuel consumption by the engine when frozen water in the form of ice crystals is present in the flight path of the aircraft.
    Variable discharge valves associated with the aircraft engine may be opened in response to ice crystal detection. The opening of the variable-rate discharge valves can cause an increase in fuel consumption by the aircraft engine. Existing processes using ice-content estimates using one or more temperature sensors may cause variable-rate discharge valves to open longer than necessary because of the uncertainty in the estimate ice. Opening the variable flow relief valves can have a big effect on fuel consumption.
    Aspects and advantages of embodiments of the present invention will be partially set forth in the description below, or may be learned from the description, or may be apparent from the practice of the embodiments.
    A first exemplary aspect of the present invention relates to an aircraft engine control method. The method includes identifying, by one or more processor (s), one or more points on a flight path of an aircraft. The method further comprises receiving, by the processor (s), a reflectivity measurement for the point / each of the points, obtained using a device placed on the aircraft. The method further comprises determining, by the processor (s), an estimate of the presence of frozen water for the point / each of the points, at least partially according to the reflectivity measurement for the point; and controlling, by the processor (s), at least one part of the aircraft engine at least partially according to the estimate of the presence of frozen water for the point (s). Other exemplary aspects relate to control systems, devices, aircraft, apparatuses and other systems designed to control at least one part of an engine at least partially according to the estimate of the presence of water jelly. Variations and modifications can be made to these exemplary aspects of the present invention.
    These features, aspects and advantages of various embodiments will become more apparent with reference to the following description and the appended claims. The accompanying drawings, which form an integral part of this specification, illustrate embodiments of the present invention and, together with the description, serve to explain the related principles. The invention will be better understood from the detailed study of some embodiments taken as non-limiting examples and illustrated by the appended drawings in which: FIG. 1 represents a general view of an exemplary system according to examples embodiments of the present invention; FIG. 2 represents an example of a computing device used in a control system according to exemplary embodiments of the present invention; FIG. 3 represents a flowchart of an exemplary method according to exemplary embodiments of the present invention; FIG. 4 illustrates the example of determination of the presence of solid water for a plurality of points by means of reflectivity measurements according to examples of embodiments of the present invention; and FIG. 5 represents an exemplary flowchart of an exemplary solid water presence estimation algorithm according to exemplary embodiments of the present invention.
    Embodiments of the invention will now be discussed in detail, of which one or more examples are illustrated in the drawings. Each example is presented as an explanation of the invention, without limiting the invention. In fact, it will be apparent to those skilled in the art that various modifications and variations can be made to the present invention without departing from the scope and spirit of the invention. For example, details illustrated or described in connection with one embodiment may be used with another embodiment to provide yet another embodiment. Thus, the present invention covers these modifications and variations as being within the scope of the appended claims and their equivalents.
    Examples of aspects of the present invention relate to systems and methods for improving engine performance by detecting the presence of ice on the flight path of the aircraft. More particularly, solid water in the form of ice crystals on the flight path of the aircraft can be detected using reflectivity measurements obtained by a device (eg a radar device) placed on the aircraft. An algorithm for estimating the presence of frozen water can be used to estimate the presence of frozen water (eg in units such as grams per cubic meter, g / m3) based on a reflectivity measurement for points on the flight path of the aircraft. One or more pieces (eg, variable relief valves) of the aircraft engine can be controlled from the estimate of the presence of frozen water to improve the flow of fuel from the aircraft.
    More particularly, the systems and methods according to exemplary aspects of the present invention can estimate the presence of frozen water for points on the flight path of the aircraft based on reflectivity measurements. For example, points on the flight path, which the aircraft must encounter during a given period of time (eg points through which the aircraft must pass during the following minute), may be identified at a particular resolution. Reflectivity measurements can be obtained for the identified points.
    An estimate of the presence of solid water for each of the points identified can be determined from the reflectivity measurements using an algorithm for estimating the presence of frozen water. In some embodiments, the estimated presence of frozen water is determined for the point / each of the points at least partially from the reflectivity measurement and an ambient temperature measurement obtained from an ambient temperature sensor placed on the aircraft. For example, a model correlating the presence of frozen water with reflectivity measurements and with ambient temperature can be used and used to determine the estimated presence of frozen water.
    In some embodiments, a plurality of estimated values for each point may be obtained as the aircraft traverses the flight path. Each estimated value can be associated with a particular reflectivity measurement. The frozen water presence estimate can be refined as the aircraft travels the flight path from the plurality of estimated values using a weighted averaging function. The weighted averaging function may assign greater weight to estimated values associated with reflectivity measurements for points closer to the aircraft, since reflectivity measurements are usually more accurate. In this way, the estimate of the presence of frozen water can be continuously improved as the aircraft approaches the point.
    Once the estimate of the presence of frozen water is obtained, the estimate can be used to control one or more parts associated with the aircraft engine, for example, to improve fuel consumption. For example, the opening and closing of one or more variable rate relief valves associated with the aircraft engine can be controlled at least partially according to the estimate of the presence of frozen water in the aircraft. aim to improve fuel consumption by the aircraft engine.
    In this way, examples of aspects of the present invention may have the technical effect of ensuring an improvement in the performance of an aircraft engine when the aircraft encounters ice on the flight path of the aircraft. Providing more efficient aircraft engine control (eg more efficient control of variable-rate discharge valves) based on estimates of the presence of frozen water can result in more efficient fuel consumption leading to potentially save fuel for the operation of the aircraft. Moreover, the estimation of the presence of frozen water according to exemplary aspects of the present invention can be effected by means of devices placed on many different types of aircraft, so it may lend itself to all kinds of applications to help improve the performance of aircraft engines.
    Figure 1 illustrates an exemplary system 100 for controlling one or more parts of an aircraft engine to improve engine performance according to exemplary aspects of the present invention. As shown, the system 100 may include a control system having one or more computer device (s) 200 (eg, a computer-based control system) or other associated control equipment, for example, an avionics system of the aircraft 102. The computer device (s) 200 can be coupled to various systems of the aircraft 102 via a communication network 140. The communication network 140 can include a data bus and / or combination of wired and / or radio communication links.
    The system 100 may include a radar device 112 associated with the aircraft 102. The radar device 112 may be designed to obtain radar reflectivity measurements. The radar device 112 may emit a radar beam 114 (eg, radio waves) and measure the reflectivity of the radar beam 114 reflected by objects (eg, frozen water particles) located on the flight path of the aircraft 102. The radar device 112 may emit a radar beam 114 having a radar beam width W as shown in FIG. 1. The radar device 112 may obtain reflectivity measurements in dBZ (e.g. in decibels with respect to Z). These reflectivity measurements can compare the equivalent reflectivity (Z) of a radar signal with the return of a rain droplet of 1 mm in diameter. In some embodiments, the radar device 112 may be associated with an on-board weather system 110 for the aircraft 102. In some embodiments, the radar device 112 may be an X-band radar device (e.g. associated with a frequency range of 7.0 to 11.2 Gigahertz (GHz)). For illustrative and explanatory purposes, the present invention is set forth with reference to performing reflectivity measurements using a radar device on the aircraft. Those of ordinary skill in the art will appreciate, using the explanations provided herein, that other types of devices can be used to obtain the reflectivity measurements. For example, a lidar device or other reflectivity-based technology may be used to obtain the reflectivity measurements.
    The system 100 may further include a temperature sensor 116 associated with the aircraft 102. The temperature sensor 116 may measure the ambient temperature around the aircraft 102 while the aircraft is in flight. In the same way as the radar device 112, the ambient temperature sensor 116 may be associated with the onboard weather system 110 for the aircraft 102.
    According to exemplary embodiments of the present invention, the computer device (s) 200 can access data from the on-board weather system 110 (e.g. radar reflectivity measurements and ambient temperature data) and use the data to control one or more parts of the aircraft to save more fuel. More particularly, the computer device (s) 200 can / can control parts associated with aircraft engines 104 (eg variable-rate discharge valves), in order to save more fuel. after the data extracted, for example, from the onboard weather system 110.
    More particularly, as illustrated in FIG. 1, the computer device (s) 200 can communicate with engine control systems 120 associated with aircraft engines 104. Aircraft engines 104 may be, for example, gas turbine engines. The motor control systems 120 may be designed to control parts of the aircraft engines 104 in response to instructions provided by the computer device (s) 200. In one embodiment, the control systems 120 of FIG. Engines may control variable flow relief valves associated with aircraft engines 104 to open and close them according to instructions from the computer device (s). The instructions from the computer device (s) 200 can be determined at least partially from the radar reflectivity measurements obtained by the radar device 112, as explained in more detail below.
    In some embodiments, the computer device (s) 200 may communicate with other on-board systems via the communication network 140. On-board systems may include, for example, a display system 130 comprising one or more display devices that can be designed to display or otherwise present to the operators of the aircraft 102 information generated or received by the system 100. The display system 130 may include a main flight screen, a unit multifunction control display or other suitable flight screen commonly present in a cabin of the aircraft 102. By way of non-limiting example, the display system 130 may be used to display flight information such as speed the altitude, attitude and azimuth of the aircraft 102.
    The computer device (s) can also communicate with a flight control computer 132. The flight control computer 132 can, among other things, automate the tasks of piloting and tracking the flight plan. of the aircraft 102. The flight control computer 132 may include or be associated with any number of individual members such as microprocessors, power sources, storage devices, interface cards, autopilots, flight management computers and other conventional devices. The flight control computer 132 can understand or cooperate with any number of software (eg flight management programs) or instructions designed to implement the various processes, process tasks, calculations. and control / display functions necessary for the operation of the aircraft 102. The flight control computer 132 is shown as being separate from the computer device (s) 200. Those skilled in the art, using the present invention will understand that the flight control computer 132 may also be included in the computer device (s) 200 or be implemented by them.
    The computer device (s) 200 may also communicate with various other onboard systems 134. The shipboard systems 134 may include, for example, digital control systems, throttle control systems, inertial reference platforms, flight instrument systems, auxiliary groups, fuel control systems, aircraft vibration control systems, communication systems, flap control systems, flight control systems acquisition of flight data and other systems.
    Figure 2 shows various members of the computer device (s) 200 according to exemplary embodiments of the present invention. As shown, the at least one computer device (s) 200 may comprise one or more processor (s) 212 and one or more memory devices 214. The processor (s) 212 may may include any suitable processing device such as a microprocessor, a microcontroller, an integrated circuit, a logic device or other suitable processing device. The memory device (s) 214 may include one or more computer-usable data, including, but not limited to, non-transitory computer-readable media, RAMs, ROMs, hard disk drives, flash memory keys or other memory devices.
    The memory device (s) 214 may / may store information accessible to the processor (s) 212, including computer-readable instructions 216 that may be executed by the processor (s) 212. The instructions 216 may be any set of instructions that, when executed by the processor (s) 212, cause the processor (s) 212 to perform operations. The instructions 216 may be implemented by software written in any suitable programming language or may be implemented in hardware. In some embodiments, the instructions 216 may be executed by the processor (s) 212 to cause the processor (s) to perform operations such as operations to determine the presence of frozen water and to control one or more several parts of an aircraft engine (eg variable-rate discharge valves), as described with reference to Figure 3.
    Referring to Figure 2, the memory devices 214 may further store data 218 accessible to the processors 212. The data 218 may include, for example, radar reflectivity data, ambient temperature measurements, water presence estimates. jelly and other data. The data 218 may also include data associated with models and algorithms for executing the exemplary methods according to exemplary aspects of the present invention, such as models and algorithms for estimating the presence of frozen water.
    The computer device (s) 200 may / may further comprise a communication interface 220. The communication interface 220 may be designed to communicate with on-board systems via a communication network such as the communication network. For example, the communication interface 220 may receive, from an onboard weather system 110, radar reflectivity measurements and ambient temperature measurements. The communication interface 220 may provide control instructions to the motor control systems 120. The communication interface 220 may include any suitable organs for interfacing with one or more other devices including, for example, transmitters, receivers, ports, controllers, antennas or other suitable organs.
    The technology explained here provides computer-based systems, as well as actions taken and information sent to and from these systems. It will be understood by one of ordinary skill in the art that the flexibility inherent in computer-based systems allows a wide variety of possibilities for configurations, combinations and distribution of tasks and functions between and among organs. For example, the processes discussed herein may be implemented using a single computing device or multiple computing devices cooperating with each other. Databases, memory, instructions, and applications can be implemented on a single system or distributed across multiple systems. The distributed members can operate in series or in parallel.
    Figure 3 shows a flowchart of an exemplary method 300 according to exemplary embodiments of the present invention. The method 300 may be implemented using one or more computer device (s) such as the computer device (s) 200 of FIGS. 1 and 2. method or part of the method may be implemented at least partially by other devices such as processors associated with the radar device 112 or one or more other device (s) without departing from the scope of the present invention. In addition, Figure 3 presents, for purposes of illustration and explanation, steps performed in a particular order. It will be understood by those of ordinary skill in the art utilizing the present invention that various steps of any of the methods set forth herein may be modified, rearranged, omitted, developed and / or adapted in a variety of ways without departing from the scope of the present invention.
    In 302, the method comprises obtaining a measurement of ambient temperature using an ambient temperature sensor. For example, an ambient temperature measurement provided by the ambient temperature sensor 116 installed on the aircraft 102 may be accessible. The ambient temperature measurement can be obtained from other suitable sources without departing from the scope of the present invention. For example, the ambient temperature measurement may be based on data stored in an onboard weather system for the aircraft.
    In 304, the method determines whether or not it is appropriate to start the frozen water presence detection mode according to the ambient temperature measurement. For example, if the measured ambient temperature is below an ambient temperature threshold, the method may comprise the initiation of the frozen water presence detection mode in order to control the aircraft as a function of the presence of frozen water detected, such as explained in more detail below. Otherwise, the process may continue to control the ambient temperature until the measured ambient temperature is below the ambient temperature threshold.
    As explained above, an aircraft is likely to encounter solid water in the atmosphere at an altitude where the ambient temperature is 0 ° C or below. Thus, in one embodiment, the method may include launching the ice detection mode if the measured ambient temperature is less than about 0 ° C. Other suitable thresholds may be used without departing from the scope of the present invention. For example, the threshold may be about -10 ° C, -5 ° C, -2.5 ° C or other suitable value without departing from the scope of the present invention. For the purpose of this description, the use of the term "about" assigned to a numerical value is intended to evoke a margin of 30% with respect to the numerical value.
    When the frozen water detection mode is launched, the method may comprise the identification of one or more points on the flight path of the aircraft, as indicated at 306 in FIG. 3. More particularly, on the trajectory current flight, one or more points (eg each associated with a latitude / longitude / altitude) can / may be chosen on the flight path of the aircraft to an arbitrary resolution value. The resolution value may be an indication of the number of points and / or the spacing of the points to be identified on the flight path.
    The points identified may be within the radar beamwidth associated with the radar device equipped with the aircraft. The points may be chosen in an interval corresponding to a period of time during which the minimum is associated with the nearest point for which a radar reflectivity measurement can be obtained and the maximum is a point which is considered to be the aircraft encounter it at a given point in time on the flight path (eg the aircraft will encounter within 1 minute on the flight path) provided that the point is within the beam width radar.
    For example, Figure 4 shows a plurality of identified points 420 on a flight path 410. The plurality of points 420 is represented as points on the curve corresponding to the flight path 410. Each of the points 420 may be associated with a latitude / longitude / altitude. The resolution of the dots 420 can be identified according to any appropriate resolution value. The points 420 may lie within the limits of the radar beam width W associated with the radar beam 114 emitted by the radar device 112 with which the aircraft 102 is equipped. For example, the point 422 on the flight path is beyond the width limits W of the radar beam 114 emitted by the radar device 112 of which the aircraft is equipped and, in some embodiments, is not identified to be included in the plurality of points.
    Considering FIG. 3, in 308 the method may comprise the reception of radar reflectivity measurements for the point / each of the points on the flight path of the aircraft. For example, a radar reflectivity measurement (eg in dBZ) can be obtained for each of the points 420 on the flight path 410 of the aircraft 102.
    In 310 of Figure 3, the method includes determining a frozen water presence estimate for the at least one point (s) based on the radar reflectivity measurements for the points. The frozen water presence estimate may also be based on other data, including reflectivity measurements obtained from other sources (eg other aircraft) and / or meteorological data obtained from a data source. meteorological service. In an exemplary embodiment, the radar reflectivity measurement for each point can be provided to a frozen water presence estimation algorithm that can generate a value estimate for the point. Details of an example of an algorithm for estimating the presence of frozen water will be discussed later with reference to Figure 5.
    In a particular implementation, the determination of the presence of frozen water for each of the points of the plurality of points can be carried out continuously to give a table, on the right of way of the trajectory, the presence of solid water in the air mass at the front of the aircraft. For example, a set of estimated values for the point / each of the points can be obtained as the aircraft traverses the flight path. Each estimated value may be associated with a particular radar reflectivity measure for the point and may be determined using the frozen water presence estimation algorithm. It can construct a set of estimated values for the point on the flight path, with the nearest point having most of the estimated values and the farthest point having only one value.
    For example, as shown in FIG. 4, the closest point 420.1 may have estimated values IWCi, IWC2, ... IWCn of frozen water presence. The next nearest point 420.2 may have an estimated value of less than the nearest point 420.1. More particularly, the next nearest point 420.2 may have estimated values of frozen water presence IWCi, IWC2, ... IWCn-ι- The next nearest point 420.3 may have an estimated value of less than the point the Closer 420.2. More particularly, the next nearest point 420.2 may have estimated IWCi, IWC2, IWCn-2 values of frozen water presence. The next nearest point may have an estimated value of less than the nearest point 420.3, and so on. The farthest point 420.n can have a single estimated value IWCi.
    For each point, a weighted average setting function can be applied to the estimated values to determine the estimated frozen water presence for the point. For example, as shown in Figure 4, the estimated values IWCi, IWC2, ... IWCn can be provided to a weighted averaging function 430 to determine an IWCe estimate of the presence of frozen water for 420.1 . The weighted averaging function 430 can assign the greatest weight to estimated values associated with the most accurate radar reflectivity measurements. For example, the weighted averaging function 430 may assign the greatest weight to estimated values for given radar reflectivity measurements obtained for points closest to the aircraft.
    Considering FIG. 3 at 312, the method may comprise the control of at least one part of the aircraft engine at least partially according to the estimate of the presence of frozen water for the points. For example, in one embodiment, one or more variable flow relief valve (s) associated with the aircraft engine can be adjusted based on the estimate of the presence of frozen water. to adjust the airflow pressure in the aircraft engine to cope with the presence of solid water in the air flow path and improve fuel consumption. For example, a variable rate discharge valve associated with the aircraft engine may be set to be opened when the frozen water presence estimate exceeds a threshold. The variable flow relief valve can be controlled to close when the estimate of the presence of frozen water falls below the threshold.
    Figure 5 is a general view of an exemplary frozen water presence estimation algorithm according to exemplary aspects of the present invention. As shown, it is possible to access a model 510 for estimating the presence of frozen water. Model 510 can correlate the presence of frozen water 512 for a point with the radar reflectivity metric 502 for the point and with a 504 measurement of ambient temperature. In some embodiments, the model 510 may take the following form: log (IWC) = a * Z + b * T + c where IWC is the estimate of the presence of frozen water, Z is the radar reflectivity measure ( eg in dBZ) and T is the ambient temperature measurement (eg in ° C). a, b and c are constants. The values for a, b and c can be determined, for example, using a polynomial equation of best fit for a set of theoretical data of frozen water presence. In some embodiments, the model can be determined in the form: log (IWC) = 0.03403 * Z - 0.01799 * T - 2.661 As shown in Figure 5, the radar reflectivity measurements 502 and the ambient temperature measurements 510 can be used to evaluate model 510 to determine the estimated presence of frozen water.
    Although specific details of various embodiments may be shown in some drawings and not others, it is only for convenience. According to the principles of the present invention, any detail of a drawing may be cited and / or claimed in combination with any detail of any other drawing.
    List of marks 100 System 102 Aircraft 104 Aircraft engine 110 On-board weather system 112 Radar device 114 Radar beam 116 Temperature sensor 120 Engine control system 130 Display system 132 Flight control computer 134 On-board systems 140 Network communication 200 Computer device (s) 212 Processor (s) 214 Memory device (s) 216 Instructions 218 Data 220 Communication interface 300 Process 302 Process step 304 Process step 306 Process step 308 Step 310 Process Step 312 Process Step 410 Flight Path 420 Points 420.n Farthest Point 420.1 Nearest Point 420.2 Next Closest Point 420.3 Next Closest Point 422 Point 430 Weighted Average Setting Function 502 Radar reflectivity measurement 504 Ambient temperature measurement 510 Frozen water presence estimation model 512 Presence of water g Elea
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    A method of controlling an aircraft engine (104), comprising: identifying, by one or more processor (s) (212), one or more point (s) (420) on a flight path (410) an aircraft (102); the access of the processor (s) (212) to a reflectivity measurement for the point / each point (420), the reflectivity measurement being obtained from a device disposed on the aircraft (102); determining, by the processor (s) (212), an estimate of the presence of frozen water for the point / each of the points (420) at least partially according to the reflectivity measurement for the point; and controlling, by the processor (s) (212), at least one part of the aircraft engine (104) at least partially according to the frozen water presence estimate for the point (s) (s) (420).
    [2" id="c-fr-0002]
    The method of claim 1, wherein the part (s) comprises / comprises a variable rate discharge valve associated with the aircraft engine (104).
    [3" id="c-fr-0003]
    The method of claim 1, wherein the reflectivity measurement for the point / each of the points (420) comprises a radar reflectivity metric (502) obtained from a radar device (112).
    [4" id="c-fr-0004]
    4. The method of claim 1 comprising receiving, by the at least one computer device (s), an ambient temperature measurement provided by a room temperature sensor (116).
    [5" id="c-fr-0005]
    The method according to claim 1, wherein the frozen water presence estimate (512) is determined for the point / each of the points (420) at least partially according to the reflectivity measurement and the ambient temperature measurement. .
    [6" id="c-fr-0006]
    6. Method according to claim 1, wherein the frozen water presence estimate (512) is determined from the reflectivity measurement using an algorithm for estimating the presence of frozen water. Frozen water presence estimation algorithm comprising: accessing the computer device (s) (200) to a model correlating the presence of frozen water with reflectivity measurements and the ambient temperature; and determining, by the control device (s), the estimate of the presence of frozen water at least partially according to the model.
    [7" id="c-fr-0007]
    The method of claim 1, wherein determining a frozen water presence estimate (512) for the point / each of the points (420) comprises: determining, by the at least one computing device (s) ( s) (200), of a set of estimated values for the point / each of the points (420) as the aircraft (102) traverses the flight path (410), each estimated value in the set of values estimated being associated with a given measure of reflectivity for the point; and determining, by the computing device (s) (200), the frozen water presence estimate (512) at least partially from the set of estimated values.
    [8" id="c-fr-0008]
    The method of claim 7, wherein the frozen water presence estimate is determined at least partially from the set of estimated values using a weighted average setting function (430). , the weighted averaging function (430) assigning greater weight to estimated values associated with given reflectivity measurements obtained for the points (420) closest to the aircraft (102).
    [9" id="c-fr-0009]
    9. The method of claim 1, the method comprising: obtaining, by the / the computer device (s) (200), a measurement of ambient temperature using a temperature sensor ( 116); and activating, by the computer device (s) (200), the frozen water presence detection mode at least partially according to the ambient temperature.
    [10" id="c-fr-0010]
    A system for controlling an engine (104) of an aircraft (102), comprising: a radar device (112) located on the aircraft (102), the radar device (112) being adapted to obtain radar reflectivity (502) for a volume of air within the width of a radar beam (114) associated with the radar device (112); a control system comprising one or more processor (s) (212) and one or more memory devices (214), the memory device (s) (214) storing instructions (216) operable by computer which, when executed by the processor (s) (212), causes the processor (s) (212) to perform operations, the operations comprising: selecting a plurality of points (420) ) on a flight path (410) of the aircraft (102) within the width of the radar beam (114); accessing a radar reflectivity measurement (502) for each point of the plurality of points (420), obtained using a radar device (112) placed on the aircraft (102); determining a frozen water presence estimate (512) for each point of the plurality of points (420) at least partially based on the radar reflectivity measurement (502) for the point; and controlling at least one part of the aircraft engine (104) at least partially according to the frozen water presence estimate (512) for at least one point of the plurality of points (420).
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    同族专利:
    公开号 | 公开日
    FR3043139B1|2020-12-25|
    GB2544876A|2017-05-31|
    GB201617856D0|2016-12-07|
    US20170121028A1|2017-05-04|
    US10106267B2|2018-10-23|
    GB2544876B|2018-03-21|
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    法律状态:
    2017-10-25| PLFP| Fee payment|Year of fee payment: 2 |
    2018-09-19| PLFP| Fee payment|Year of fee payment: 3 |
    2019-01-25| PLSC| Search report ready|Effective date: 20190125 |
    2019-09-19| PLFP| Fee payment|Year of fee payment: 4 |
    2020-09-17| PLFP| Fee payment|Year of fee payment: 5 |
    2021-09-22| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    US14/927,788|US10106267B2|2015-10-30|2015-10-30|Enhancing engine performance to improve fuel consumption based on atmospheric ice particles|
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