Classifications

• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
  • B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
  • B64D15/16—De-icing or preventing icing on exterior surfaces of aircraft by mechanical means, e.g. pulsating mats or shoes attached to, or built into, surface
  • B64D15/163—De-icing or preventing icing on exterior surfaces of aircraft by mechanical means, e.g. pulsating mats or shoes attached to, or built into, surface using electro-impulsive devices
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
  • B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
  • B64D33/02—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
  • F01D25/02—De-icing means for engines having icing phenomena
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
  • B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
  • B64D33/02—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
  • B64D2033/0233—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising de-icing means

Definitions

• the present invention relates to a system for de-icing a part of an aircraft, a nacelle of an aircraft equipped with such a system de-icing, an aircraft equipped with such a de-icing system, a method for de-icing a part of an aircraft and a corresponding computer program.
• Technological background [0002] The French patent application published under the number FR 3078948 A1 describes a system for de-icing a part of an aircraft, comprising: actuators fixed to the part; and - an actuator control device for vibrating the part.
• the part to be de-iced is an air inlet lip of an aircraft nacelle and the actuators are piezoelectric actuators distributed all along this air inlet lip. [0004] It may be desired to reduce the defrosting time.
• a system for de-icing a part of an aircraft comprising: actuators fixed to the part; and - an actuator control device for vibrating the part; in which the control device is designed for, the actuators being divided into several groups: - controlling the actuators of a first of the groups to determine a resonant frequency of the part; then - on the one hand, controlling the actuators of a second of the groups to determine a resonance frequency of the room and, on the other hand, in parallel, controlling the actuators of the first group to defrost the room by making it vibrate, using the resonance frequency determined with this first group.
• the part is a part of an aircraft nacelle.
• the part is an air inlet lip of the aircraft nacelle.
• the actuators are piezoelectric actuators.
• the control device is designed to, in parallel: - control the actuators of one group after the other according to the order of succession, to each time determining a resonant frequency of the part; and - controlling the actuators from one group to another according to the order of succession, each time to defrost the room by causing it to vibrate, using the resonance frequency determined with this group.
• control device is designed to: control the actuators of the first group to determine a resonant frequency of the part; then - for each of the other group(s) in turn: command the current group to determine a resonance frequency for the room and, in parallel, command the previous group to defrost the room by making it vibrate, using the frequency of determined resonance with this previous group; then - controlling the actuators of the last group to defrost the room by making it vibrate, using the resonance frequency determined with this last group.
• control device is designed to start determining a resonance frequency of the room with the next group, without waiting for the end of the defrosting of the room with the current group.
• control device comprises first and second computers, the first computer being designed to carry out the step(s) of determining the resonance frequency of the part and the second computer being designed to carry out the the steps for defrosting the room.
• first computer is also designed, once the resonance frequencies have been determined with all the groups, to carry out at least one of the defrosting steps or steps not yet carried out by the second computer.
• each computer is also designed to, in response to a failure of the other computer: - control the actuators of a first of the groups to determine a resonant frequency of the part; then - for successively, in an order of succession, each of the other group(s): control the actuators of the previous group to defrost the room by making it vibrate, using the resonance frequency determined with this previous group, then control the current group actuators to determine a resonant frequency of the part; then - controlling the actuators of the last group to defrost the room by making it vibrate, using the resonance frequency determined with this last group.
• An aircraft nacelle is also proposed, comprising: - an air inlet lip; and - a system according to the invention, for de-icing the lip.
• An aircraft is also proposed comprising: a part on which frost is likely to appear; and - a system according to the invention, for defrosting this room.
• a method for de-icing a part of an aircraft comprising: - controlling the actuators of a first group of actuators fixed to the part, to determine a resonant frequency of the part; then - on the one hand, the control of the actuators of a second group of actuators fixed to the part to determine a resonance frequency of the part and, on the other hand, in parallel, the control of the actuators of the first group to defrost the part by making it vibrate, using the resonance frequency determined with this first group.
• a computer program is also proposed comprising instructions for implementing the method according to the invention, when executed by a computer.
• Figure 1 is a three-dimensional view of an aircraft nacelle
• Figure 2 is a sectional view and a rear view of an air inlet lip of the nacelle of Figure 1
• Figure 3 is a functional view of an example of a system according to the invention for de-icing the air inlet lip of Figure 2
• Figure 4 is a block diagram of steps of a first example of a method according to the invention for defrosting the air inlet lip of Figure 2
• Figure 2 is a three-dimensional view of an aircraft nacelle
• Figure 3 is a functional view of an example of a system according to the invention for de-icing the air inlet lip of Figure 2
• Figure 4 is a block diagram of steps of a first example of a method according to the invention for defrosting the air inlet lip of Figure 2
• FIG. 1 is a three-dimensional view of an aircraft nacelle
• Figure 2 is a sectional view and a rear view of an air inlet lip of the nacelle of Figure 1
• Figure 3 is a functional
• Figure 5 is a timing diagram illustrating the sequence of steps of the method of Figure 4, [0026] [Fig.6]
• Figure 6 is a block diagram of steps of a second example of the method according to the fig air intake lip defrosting invention ure 2
• Figure 7 is a timing diagram illustrating the sequence of steps of the method of Figure 6
• Figure 8 is a block diagram of steps of an example of a process for de-icing the air inlet lip of figure 2, in the event of failure of a part of the system of figure 3
• Figure 9 is a timing diagram illustrating the sequence of steps of the method of Figure 8.
• FIG 1 illustrates a nacelle 100 of an aircraft with a turbine engine 102 inserted into it.
• the nacelle 100 comprises a tubular casing 104 surrounding the turbine engine 102 and, along a perimeter of a front end of the tubular casing 104, a lip 106 delimiting an air inlet 108.
• the lip 106 is generally folded into a "V" so as to present a central wall 202 and a peripheral wall 204 meeting in a front vertex 206.
• the lip 106 has in particular an internal face 208.
• the nacelle 100 further comprises actuators 210 attached to the inner face 208 of the lip 106.
• Actuators 210 are preferably piezoelectric. In FIG. 2, sixteen actuators 210 are represented but, in practice, they can be much fewer or more numerous, for example from four to more than one hundred. Still in the example described, the actuators 210 are distributed along the lip 106 so as to follow each other around the air inlet 108.
• the actuators 210 are for example arranged on a circle, of preferably evenly spaced from each other.
• the actuators 210 are divided into several groups, for example four groups G1, G2, G3, G4. In practice, many more groups could be expected.
• the groups G1-4 are distinct, which means that each actuator 210 belongs to only one of the groups G1-4. This arrangement makes it possible to optimize the number of interconnecting harnesses and their lengths.
• the groups G1-4 include substantially the same number of actuators 210 (to the nearest tolerance, for example to within 10%), so as to keep the same load for the converter on all groups and be able to detect the loss of one or more actuators.
• the groups G1-4 group together the actuators 210 located respectively in angular sectors S1, S2, S3, S4 of the lip 106. of the nacelle 100 will now be described in more detail.
• the term “de-icing” includes not only making the frost that has already formed disappear, but also the fight against the formation of frost before it appears (anti-icing).
• the term “defrosting” covers only partial defrosting of the defrosted part (the lip 106 in the example described).
• the de-icing system 300 firstly includes the actuators 210 described above.
• the de-icing system 300 further comprises a device 302 for controlling the actuators 210.
• the control device 302 comprises two computers 304A, 304B each having an output SA, SB, as well as a multiple switch 305 designed to selectively connect each group G1-4 to the SA output of the computer 304A or to the SB output of the computer 304B, or to disconnect this group G1-4.
• the computers 304A, 304B will now be described in more detail.
• Each computer 304A, 304B comprises an analysis module 306A, 306B and a de-icing module 308A, 308B.
• Each computer 304A, 304B further comprises a local switch 310A, 310B for selectively connecting the analysis module 306A, 306B and the defrosting module 308A, 308B, to its SA or SB output.
• each of the groups G1-4 either to the analysis module 306A of the computer 304A, or to the defrosting module 308A of the computer 304A, or to the module analysis 306B of the computer 304B, or to the de-icing module 308B of the computer 304B.
• Each analysis module 306A, 306B is designed to determine a resonance frequency of the lip 106 by controlling the group G1-4 to which it is connected. In the example described, this resonance frequency is substantially that of the sector S1-4 of the lip 106 comprising the actuators 210 of the group G1- G4 connected.
• the resonance frequency may be different depending on the length of the harnesses, the ambient temperature, the variation in the characteristics of the components linked to their heating, the quantity of ice present and the analysis module 306A, 306B makes it possible to update the resonant frequency.
• the desired resonance frequency is preferably a high frequency, for example between 10 kHz and 200 kHz.
• the analysis module 306A, 306B can use several analysis methods. In a first analysis method, the analysis module 306A, 306B is designed to find the resonant frequency by frequency sweep.
• the analysis module 306A, 306B is for example designed to apply to the actuators 210 of the connected group G1-4 a sinusoidal excitation voltage of frequency sweeping a predefined interval in one given time, for example between 10 kHz and 200 kHz. From the current measured in the piezoelectric actuators 210, the analysis module 306A, 306B is then designed to calculate the impedance as a function of the frequency and to determine the resonant frequency as the frequency where the impedance is minimum.
• the analysis module 306A, 306B is designed to determine the resonance frequency by frequency analysis.
• the analysis module 306A, 306B is for example designed to apply a periodic or pulsed excitation voltage, to obtain in response a frequency spectrum from the current measurement in piezoelectric actuators, for example by means of a Fourier transform and this for each frequency.
• each analysis module 306A, 306B is then designed to determine the frequency of the largest peak in the frequency spectrum, this frequency being the desired resonance frequency.
• each analysis module 306A, 306B is preferably designed to apply low voltage excitation voltages, for example between 0 and 50 V (peak to peak ).
• Each analysis module 306A, 306B comprises for example a field-programmable gate array (also designated by the acronym FPGA) or a digital signal processing unit ( from English "Digital Signal Processing", also referred to by the acronym DSP).
• Each defrost module 310A, 310B is designed to defrost the lip 106 by causing it to vibrate, by controlling the actuators 210 of the group G1-4 to which it is connected.
• the defrosting is carried out each time by vibrating mainly the sector S1-4 corresponding to the connected group G1-4, the other sectors possibly vibrating little or not at all.
• the defrost module 310A, 310B is designed to control the actuators 210 of the connected group by using the resonance frequency previously determined with this group by one of the analysis modules 306A, 306B.
• the de-icing module 310A, 310B is designed to excite the actuators 210 of the group G1-4 connected, for a predefined period, at an excitation frequency equal to the resonance frequency determined or else derived by the defrosting module 310A, 310B of the determined resonant frequency.
• the defrost module 310A, 310B is designed to begin to excite the actuators 210 of the connected group G1-4, at the resonance frequency (or else at a frequency derived by the defrost module 310A, 310B of the determined resonant frequency), then to vary the excitation frequency to follow the resonant frequency. Indeed, as the defrosting progresses, the quantity of frost on the lip 106 decreases, for example following the detachment of pieces of frost, which can modify the resonance frequency. The temperature rise of the converter components power during defrosting can also change the resonant frequency to be applied. For example, the defrost module 310A, 310B can use the maximum point tracking method.
• the principle of this method is to insert a small low frequency variation in the control around the high frequency operating point of the piezoelectric actuators.
• the goal is to control the phase between the injected low frequency signal and the low frequency variation of the output power.
• the output power supplied is calculated from a measurement of a current flowing through the actuators 210 of the connected G1-4 group and the voltage applied to the actuators 210 of the connected G1-4 group.
• a low pass filter makes it possible to preserve the low frequency power variation. If the injected signal is in phase with the calculated output power then the slope is positive and the power tends towards the maximum power. If the two variations are in phase opposition then the slope is negative and the output power decreases.
• the de-icing module 310A, 310B is for example designed to apply an excitation voltage at the excitation frequency.
• the excitation voltage is preferably high voltage, that is to say having a peak to peak value greater than that of the low voltage excitation voltage used by the analysis module. This peak-to-peak value is for example greater than 50 V, preferably greater than 100 V.
• each defrosting module 310A, 310B includes a power converter 312A, 312B and a power converter 312A, 312B.
• Each power converter 312A, 312B is for example designed to provide the sinusoidal excitation voltage from a DC voltage, for example coming from a rectifier autotransformer unit (from the English "Auto Transformer Rectifier Unit”, also referred to by the acronym ATRU) respectively.
• the control module 314A, 314B comprises for example a microcontroller or a network of programmable gates (FPGA).
• the control device 302 comprises a computing device provided with a data processing unit (such as a microprocessor) and with a main memory associated with the data processing unit.
• a computer program comprising instructions is intended to be loaded into the main memory, so that the data processing unit executes these instructions and thus implements one or more of the modules 305, 306A, 308A, 310A, 312A, 314A, 306B, 308B, 310B, 312B, 314B. These modules are thus software modules. [0062] With reference to FIG. 4, a first example 400 of a defrosting method will now be described. Furthermore, the groups G1-4 are assumed to be ordered according to an order of succession (G1, then G2, then G3, then G4 in the example described) in the control device 302.
• the multiple switch 314 and the local switches 310A, 310B connect the analysis module 306A to the actuators 210 of the first group G1 and for example disconnect from the control device 302 the actuators of the other groups G2-4.
• the analysis module 306A controls the actuators of the first group G1 to determine a resonance frequency of the lip 106, and transmits the resonance frequency to the de-icing module 308B. In the example described, the analysis module 306A transmits this resonance frequency to the control module 314A which retransmits it to the control module 314B. Steps 406 to 410 are then implemented for each of the other groups G2-4 successively.
• the multiple switch 314 and the local switches 308A, 308B connect the actuators 210 of the current group to the analysis module 306A and the actuators of the previous group to the defrost module 308B and for example disconnect the actuators of the other groups from the control device 302.
• the analysis module 306A controls the actuators 210 of the current group to determine a resonance frequency of the lip 106, and transmits the resonant frequency determined with the current group at defrost module 308B. In the example described, the analysis module 306A transmits this resonance frequency to the control module 314A which retransmits it to the control module 314B.
• the defrosting module 308B controls the actuators 210 of the previous group to defrost the lip 106 by causing it to vibrate, using the resonance frequency determined by the analysis module 306A with this previous group.
• the multiple switch 305 and the local switches 310A, 310B connect the actuators of the last group G4 to the defrost module 308B and for example disconnect from the control device 302 the actuators of the other groups G1- 3.
• the defrosting module 310B controls the actuators 210 of the last group G4 to defrost the lip 106 by making it vibrate, using the resonance frequency determined by the analysis module 306A with this last group G4.
• FIG. 5 illustrates the alternation over time (t) of the analysis (oval) and defrosting (rectangular) steps during the implementation of the defrosting method 400.
• the defrost process 400 does not use the modules 306B and 308A. Thus, they could be omitted from the control device 302.
• control device 302 is still designed to, in parallel: control the actuators 210 from one group after another according to the order of succession, for each time determining a resonance frequency of the lip 106, and controlling the actuators 210 from one group after another according to the order of succession to defrost the lip 106 by making it vibrate, using the resonance frequency determined with this group.
• this time controller 302 is designed to begin determining a resonant frequency of lip 106 with the next group, without waiting for lip 106 to finish defrosting with the current group. More specifically, in the example described, during a step 602, the multiple switch 305 and the local switches 310A, 310B connect the actuators 210 of the first group G1 to the analysis module 306A and for example disconnect from the control device 302 the actuators 210 of the other groups G2-4. During a step 604, the analysis module 306A controls the actuators 210 of the first group G1 to determine a resonance frequency of the lip 106, and transmits this resonance frequency to the de-icing module 308B.
• the step loops 600A on the one hand, and 600B on the other hand are made in parallel.
• the first step loop 600A is carried out successively for each group G2-G3 of actuators 210.
• the multiple switch 314 and the local switch 310A connect the actuators 210 of the in progress at the analysis module 306A.
• the analysis module 306A controls the actuators 210 of the group in progress to determine a resonance frequency of the lip 106, and transmits the determined resonance frequency to the defrosting modules 308A, 308B . In the example described, the analysis module 306A transmits this resonance frequency to the control module 314A which retransmits it to the control module 314B.
• the defrost module 308A controls the actuators of a group of actuators 210 that the defrost module 308B has not yet controlled, to defrost the lip 106 by causing it to vibrate.
• Step 610 can be carried out several times, as long as the actuators 210 of all the groups G1-4 have not been commanded to defrost the lip 106, either by the defrost module 308A or else by the defrost module 308B (see below).
• the second loop of steps 600B is carried out successively for each group G1-G4, unless this group has already been used in step 610 to defrost the lip 106.
• FIG. 7 illustrates the alternation over time (t) of the analysis (oval) and defrosting (rectangular) steps during the implementation of the method 600.
• the analysis steps can be shorter than the defrosting steps, so that the computer 304A can quickly finish the analysis for all the groups G1-4 and can then, at step 610, help the computer 304B to finish defrosting.
• the computer 304A can begin to defrost with the actuators 210 of the last group G4 while the computer 304A is still defrosting with the actuators of the group G3. Overall, defrosting therefore takes place more quickly.
• FIG. 8 a third example of a defrosting method will now be described.
• one of the computers 304A, 304B detects that the other is faulty.
• the computer 304B is faulty. If the computer 304A were faulty, the method 800 would be identical, reversing the suffixes A and B. 4. [0090] During a step 804, the multiple switch 314 and the local switch 310A connect the actuators 210 of the current group to the analysis module 306A. [0091] During a step 806, the analysis module 306A controls the actuators 210 of the current group to determine a resonance frequency of the lip 106. [0092] During a step 808, the multiple switch 314 and the local switch 310A connect the actuators 210 of the current group to the defrost module 308A.
• the defrosting module 308A controls the actuators of the current group to defrost the lip 106 by causing it to vibrate, using the resonance frequency determined with this current group.
• complete defrosting can be obtained with only the computer 304A or 304B still healthy.
• FIG. 9 illustrates the alternation over time (t) of the analysis (oval) and defrosting (rectangular) steps during the implementation of the defrosting method 800.
• the steps of the methods described above can be carried out according to any possible sequence (which may include steps carried out in parallel).
• the actuators could be divided into several sets of groups such as the groups G1-G4 described previously. Each set would then comprise several groups of actuators. The groups of the same set would be controlled as described previously. For example, there could be four sets of sixteen groups each, or sixty-four groups in total.

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• Engineering & Computer Science (AREA)
• Aviation & Aerospace Engineering (AREA)
• Mechanical Engineering (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• General Engineering & Computer Science (AREA)
• Measurement Of Mechanical Vibrations Or Ultrasonic Waves (AREA)
• Apparatuses For Generation Of Mechanical Vibrations (AREA)
• Vibration Prevention Devices (AREA)
• Wind Motors (AREA)
• Air Conditioning Control Device (AREA)

Applications Claiming Priority (2)

Publications (1)

Family

ID=77317101

Family Applications (1)

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Family Cites Families (6)

• 2021
  • 2021-06-15 FR FR2106335A patent/FR3123941A1/fr active Pending
• 2022
  • 2022-06-15 US US18/567,329 patent/US12583591B2/en active Active
  • 2022-06-15 WO PCT/FR2022/051150 patent/WO2022263770A1/fr not_active Ceased
  • 2022-06-15 CN CN202280041629.3A patent/CN117480094A/zh active Pending
  • 2022-06-15 EP EP22741346.5A patent/EP4355656A1/de active Pending

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